SBIR/STTR 2005-1 National Aeronautics and Space Administration SMALL BUSINESS INNOVATION RESEARCH (SBIR) & SMALL BUSINESS TECHNOLOGY TRANSFER (STTR) Program Solicitations Opening Date: July 7, 2005 Closing Date: September 7, 2005 An electronic version of this document is located at: http://sbir.nasa.gov TABLE OF CONTENTS 1. Program Description 1 1.1 Introduction 1 1.2 Program Authority and Executive Order 1 1.3 Program Management 1 1.4 Three-Phase Program 2 1.5 Eligibility Requirements 3 1.6 General Information 4 2. Definitions 5 2.1 Commercialization 5 2.2 Cooperative Research or Research and Development (R/R&D) Agreement 5 2.3 Cooperative Research or Research and Development (R/R&D) 5 2.4 Essentially Equivalent Work 5 2.5 Funding Agreement 5 2.6 HUBZone-Owned SBC 5 2.7 Innovation 6 2.8 Intellectual Property (IP) 6 2.9 Principal Investigator (PI) 6 2.10 Research Institution (RI) 6 2.11 Research or Research and Development (R/R&D) 6 2.12 SBIR/STTR Technical Data 6 2.13 SBIR/STTR Technical Data Rights 6 2.14 Small Business Concern (SBC) 6 2.15 Socially and Economically Disadvantaged Individual 7 2.16 Socially and Economically Disadvantaged Small Business Concern 7 2.17 Subcontract 7 2.18 United States 7 2.19 Women-Owned Small Business 7 3. Proposal Preparation Instructions and Requirements 8 3.1 Fundamental Considerations 8 3.2 Phase 1 Proposal Requirements 8 3.3 Phase 2 Proposal Requirements 13 3.4 SBA Data Collection Requirement 17 4. Method of Selection and Evaluation Criteria 18 4.1 Phase 1 Proposals 18 4.2 Phase 2 Proposals 19 4.3 Debriefing of Unsuccessful Offerors 21 5. Considerations 22 5.1 Awards 22 5.2 Phase 1 Reporting 22 5.3 Payment Schedule for Phase 1 23 5.4 Release of Proposal Information 23 5.5 Access to Proprietary Data by Non-NASA Personnel 23 5.6 Final Disposition of Proposals 23 5.7 Proprietary Information in the Proposal Submission 23 5.8 Limited Rights Information and Data 24 5.9 Cost Sharing 25 5.10 Profit or Fee 25 5.11 Joint Ventures and Limited Partnerships 25 5.12 Similar Awards and Prior Work 25 5.13 Contractor Commitments 25 5.14 Additional Information 26 5.15 Property and Facilities 27 5.16 False Statements 27 6. Submission of Proposals 28 6.1 Submission Requirements 28 6.2 Submission Process 28 6.3 Deadline for Phase 1 Proposal Receipt 29 6.4 Acknowledgment of Proposal Receipt 29 6.5 Withdrawal of Proposals 30 6.6 Service of Protests 30 7. Scientific and Technical Information Sources 31 7.1 NASA SBIR/STTR Homepage 31 7.2 NASA Commercial Technology Network 31 7.3 NASA Technology Utilization Services 31 7.4 United States Small Business Administration 32 7.5 National Technical Information Service 32 8. Submission Forms and Certifications 33 Form A – SBIR Cover Sheet 34 Guidelines for Completing SBIR Cover Sheet 35 Form B – SBIR Proposal Summary 36 Guidelines for Completing SBIR Proposal Summary 37 Form C – SBIR Budget Summary 38 Guidelines for Preparing SBIR Budget Summary 39 SBIR Check List 41 Form A – STTR Cover Sheet 42 Guidelines for Completing STTR Cover Sheet 43 Form B – STTR Proposal Summary 45 Guidelines for Completing STTR Proposal Summary 46 Form C – STTR Budget Summary 47 Guidelines for Preparing STTR Budget Summary 48 Model Cooperative R/R&D Agreement 50 Model Allocation of Rights Agreement 51 STTR Check List 55 Example Format for Briefing Chart 56 NASA SBIR/STTR Technology Taxonomy 57 9. Research Topics for SBIR and STTR 58 9.1 SBIR Research Topics 58 9.1.1 Aeronautics Research 59 9.1.2 Exploration Systems 73 9.1.3 Science 125 9.1.4 Space Operations 169 9.2 STTR Research Topics 183 2005 NASA SBIR/STTR Program Solicitations 1. Program Description 1.1 Introduction This document includes two NASA program solicitations with separate research areas under which small business concerns (SBCs) are invited to submit proposals: the Small Business Innovation Research (SBIR) program and the Small Business Technology Transfer (STTR) program. Program background information, eligibility requirements for participants, the three program phases, and information for submitting responsive proposals is contained herein. The 2005 Solicitation period for Phase 1 proposals begins July 7, 2005, and ends September 7, 2005. The purposes of the SBIR/STTR programs, as established by law, are to stimulate technological innovation in the private sector; to strengthen the role of SBCs in meeting Federal research and development needs; to increase the commercial application of these research results; and to encourage participation of socially and economically disadvantaged persons and women-owned small businesses. To be eligible for selection, a proposal must be based on an innovation having high technical or scientific merit that is responsive to a NASA need described herein and which offers potential commercial application. Proposals must be submitted via the Internet (http://sbir.nasa.gov) and include all relevant documentation. Unsolicited proposals will not be accepted. NASA plans to select for award those proposals offering the best value to the Government and the Nation. Subject to the availability of funds, approximately 300 SBIR and 40 STTR Phase 1 proposals will be selected for negotiation of fixed-price contracts in November 2005. Historically, the ratio of Phase 1 proposals to awards is approximately 8:1 for SBIR and 5:1 for STTR, and approximately 40% of the selected Phase 1 contracts are selected for Phase 2 follow-on efforts. 1.2 Program Authority and Executive Order SBIR: This Solicitation is issued pursuant to the authority contained in P.L. 106-554. Government wide SBIR policy is provided by the Small Business Administration (SBA) through its Policy Directive. The current law authorizes the program through September 30, 2008. STTR: This Solicitation is issued pursuant to the authority contained in P.L. 107-50. Government wide STTR policy is provided by the SBA through its Policy Directive. The current law authorizes the program through September 30, 2009. Executive Order: President Bush issued an Executive Order 13329 on February 24, 2004 directing Federal agencies that administer the SBIR and STTR programs to encourage innovation in manufacturing related research and development consistent with the objectives of each agency and to the extent permitted by law. 1.3 Program Management The Exploration Systems Mission Directorate provides overall policy direction for the NASA SBIR/STTR programs. The Program Management Office is hosted at Goddard Space Flight Center. The Procurement Management Office is hosted at Glenn Research Center. The SBIR Program Solicitation is aligned with NASA’s Mission Directorates (http://www.nasa.gov). The research development interests of all Mission Directorates are reflected in the subtopics identified in Section 9. The STTR Program Solicitation research areas correspond to the central underlying technological competencies of each participating NASA Center. The Jet Propulsion Laboratory (JPL) does not participate in the management of the STTR Program. Information regarding the Mission Directorates and the NASA Centers can be obtained at the following web sites: NASA Mission DirectoratesAeronautics Researchhttp://www.aerospace.nasa.gov/Exploration Systemshttp://www.exploration.nasa.gov/Sciencehttp://science.hq.nasa.gov/Space Operationshttp://www.hq.nasa.gov/osf/ NASA InstallationsAmes Research Center (ARC)http://www.nasa.gov/centers/ames/home/index.htmlDryden Flight Research Center (DFRC)http://www.nasa.gov/centers/dryden/home/index.htmlGlenn Research Center (GRC)http://www.nasa.gov/centers/glenn/home/index.htmlGoddard Space Flight Center (GSFC)http://www.nasa.gov/centers/goddard/home/index.htmlJet Propulsion Laboratory (JPL)http://www.nasa.gov/centers/jpl/home/index.htmlJohnson Space Center (JSC)http://www.nasa.gov/centers/johnson/home/index.htmlKennedy Space Center (KSC)http://www.nasa.gov/centers/kennedy/home/index.htmlLangley Research Center (LaRC)http://www.nasa.gov/centers/langley/home/index.htmlMarshall Space Flight Center (MSFC)http://www.nasa.gov/centers/marshall/home/index.htmlStennis Space Center (SSC)http://www.nasa.gov/centers/stennis/home/index.html 1.4 Three-Phase Program Both the SBIR and STTR programs are divided into three funding and development stages. 1.4.1 Phase 1. The purpose of Phase 1 is to determine the scientific, technical, and commercial merit and feasibility of the proposed innovation, and the quality of the SBC’s performance with a relatively small NASA investment before consideration of further Federal support in Phase 2. Successful completion of Phase 1 objectives is a prerequisite to Phase 2 consideration. Phase 1 must concentrate on establishing the scientific or technical merit and feasibility of the proposed innovation and on providing a basis for continued development in Phase 2. Proposals must conform to the format described in Section 3.2. Evaluation and selection criteria are described in Section 4.1. NASA is solely responsible for determining the relative merit of proposals, their selection for award, and judging the value of Phase 1 results. Maximum value and period of performance for Phase 1 contracts: Phase 1 ContractsSBIRSTTRMaximum Contract Value$ 70,000$ 100,000Maximum Period of Performance6 months12 months 1.4.2 Phase 2. The objective of Phase 2 is to continue the Research or Research and Development (R/R&D) effort from Phase 1. Only SBCs awarded Phase 1 contracts are eligible for Phase 2 funding agreements. Phase 2 projects are chosen as a result of competitive evaluations based on selection criteria provided in Section 4.2. The maximum value for SBIR/STTR Phase 2 contracts is $600,000 with a maximum period of performance of 24 months. 1.4.3 Phase 3. NASA may award Phase 3 contracts for products or services with non-SBIR/STTR funds. The competition for SBIR Phase 1 and Phase 2 awards satisfies any competition requirement of the Armed Services Procurement Act, the Federal Property and Administrative Services Act, and the Competition in Contracting Act. Therefore, an agency that wishes to fund an SBIR Phase 3 project is not required to conduct another competition in order to satisfy those statutory provisions. Phase 3 work may be for products, production, services, R/R&D, or any combination thereof. A Federal agency may enter into a Phase 3 SBIR agreement at any time with a Phase 1 or Phase 2 awardee. There is no limit on the number, duration, type, or dollar value of Phase 3 awards made to a business concern. There is no limit on the time that may elapse between a Phase 1 or Phase 2 award and Phase 3 award. The small business size limits for Phase 1 and Phase 2 awards do not apply to Phase 3 awards. 1.5 Eligibility Requirements 1.5.1 Small Business Concern. Only firms qualifying as SBCs, as defined in Section 2.14, are eligible to participate in these programs. Socially and economically disadvantaged and women-owned SBCs are particularly encouraged to propose. STTR: To be eligible, SBCs must submit a cooperative research agreement with a Research Institution (RI). 1.5.2 Place of Performance. For both Phase 1 and Phase 2, the R/R&D must be performed in the United States (Section 2.18). However, based on a rare and unique circumstance, for example, if a supply or material or other item or project requirement is not available in the United States, NASA may allow that particular portion of the research or R&D work to be performed or obtained in a country outside of the United States. Proposals must clearly indicate if any work will be performed outside the United States. Approval by the Contracting Officer for such specific condition(s) must be in writing. 1.5.3 Principal Investigator. The primary employment of the Principal Investigator (PI) must be with the SBC under the SBIR Program, while under the STTR Program the PI may be employed by either the SBC or RI. Primary employment means that more than half of the PI’s total employed time (including all concurrent employers, consulting, and self-employed time) is spent with the SBC. Primary employment with a small business concern precludes full-time employment at another organization. If the PI does not currently meet these primary employment requirements, the offeror must explain how these requirements will be met if the proposal is selected for contract negotiations that may lead to an award. U.S. Citizenship is not a requirement for selection. REQUIREMENTSSBIRSTTRPrimary EmploymentPI must be with the SBCPI must be employed with the RI or SBCEmployment CertificationThe offeror must certify in the proposal that the primary employment of the PI will be with the SBC at the time of award and during the conduct of the project. If the PI is not an employee of the SBC, the offeror must describe the management process to ensure SBC control of the project.Co-Principal InvestigatorsNot AcceptableNot AcceptableMisrepresentation of QualificationsWill result in rejection of the proposal or termination of the contractWill result in rejection of the proposal or termination of the contractSubstitution of PIsMust receive advanced written approval from NASAMust receive advanced written approval from NASA 1.6 General Information 1.6.1 Solicitation Distribution. This 2005 SBIR/STTR Program Solicitation is available via the NASA SBIR/STTR homepage (http://sbir.nasa.gov). SBCs are encouraged to check the SBIR/STTR homepage for program updates. Any updates or corrections to the Solicitation will be posted there. If the SBC has difficulty accessing the Solicitation, contact the Help Desk (Section 1.6.2). 1.6.2 Means of Contacting NASA SBIR/STTR Program (1) NASA SBIR/STTR Homepage: http://sbir.nasa.gov (2) Each of the NASA field installations has its own homepage, including strategic planning and program information. Please consult these homepages as noted in Section 1.3 for more details on the technology requirements within the subtopic areas. (3) Help Desk. For inquiries, requests, and help-related questions, contact via: e-mail: sbir@reisys.com telephone: 301-937-0888 between 8:00 a.m.-5:00 p.m. (Mon.-Fri., Eastern Time) facsimile: 301-937-0204 The requestor must provide the name and telephone number of the person to contact, the organization name and address, and the specific questions or requests. (4) NASA SBIR/STTR Program Manager. Specific information requests that could not be answered by the Help Desk should be mailed or e-mailed to: Paul Mexcur, Program Manager NASA SBIR/STTR Program Management Office Code 408, Goddard Space Flight Center Greenbelt, MD 20771-0001 Winfield.P.Mexcur@nasa.gov 1.6.3 Questions About This Solicitation. To ensure fairness, questions relating to the intent and/or content of research topics in this Solicitation cannot be answered during the Phase 1 solicitation period. Only questions requesting clarification of proposal instructions and administrative matters will be answered. 2. Definitions 2.1 Commercialization Commercialization is a process of developing markets and producing and delivering products or services for sale (whether by the originating party or by others). As used here, commercialization includes both Government and non-Government markets. 2.2 Cooperative Research or Research and Development (R/R&D) Agreement A financial assistance mechanism used when substantial Federal programmatic involvement with the awardee during performance is anticipated by the issuing agency. The Cooperative R/R&D Agreement contains the responsibilities and respective obligations of the parties. 2.3 Cooperative Research or Research and Development (R/R&D) For purposes of the NASA STTR Program, cooperative R/R&D is that which is to be conducted jointly by the SBC and the RI in which at least 40 percent of the work (amount requested, including cost sharing if any, less fee if any) is performed by the SBC and at least 30 percent of the work is performed by the RI. 2.4 Essentially Equivalent Work The “scientific overlap,” which occurs when (1) substantially the same research is proposed for funding in more than one contract proposal or grant application submitted to the same Federal agency; (2) substantially the same research is submitted to two or more different Federal agencies for review and funding consideration; or (3) a specific research objective and the research design for accomplishing an objective are the same or closely related in two or more proposals or awards, regardless of the funding source. 2.5 Funding Agreement Any contract, grant, cooperative agreement, or other funding transaction entered into between any Federal agency and any entity for the performance of experimental, developmental, research and development, services, or research work funded in whole or in part by the Federal Government. 2.6 HUBZone-Owned SBC "HUBZone" is an area that is located in one or more of the following: * A qualified census tract (as defined in section 42(d)(5)(C)(i)(1) of the Internal Revenue Code of 1986); * A qualified "non-metropolitan county" that is: not located in a metropolitan statistical area (as defined in section 143(k)(2)(B) of the Internal Revenue Code of 1986), and - in which the median household income is less than 80 percent of the non-metropolitan State median household income, or - that based on the most recent data available from the Secretary of Labor, has an unemployment rate that is not less than 140 percent of the statewide average unemployment rate for the State in which the county is located; * Lands within the external boundaries of an Indian reservation. To participate in the HUBZone Empowerment Contracting Program, a concern must be determined to be a "qualified HUBZone small business concern." A firm can be found to be a qualified HUBZone concern, if: * It is small, * It is located in a "historically underutilized business zone" (HUBZone) * * It is owned and controlled by one or more U.S. Citizens, and * At least 35% of its employees reside in a HUBZone. 2.7 Innovation Something new or improved, having marketable potential, including (1) development of new technologies, (2) refinement of existing technologies, or (3) development of new applications for existing technologies. 2.8 Intellectual Property (IP) The separate and distinct types of intangible property that are referred to collectively as “intellectual property,” including but not limited to: patents, trademarks, copyrights, trade secrets, SBIR/STTR technical data (as defined in Section 2.12), ideas, designs, know-how, business, technical and research methods, and other types of intangible business assets, and including all types of intangible assets either proposed or generated by the SBC as a result of its participation in the SBIR/STTR Program. 2.9 Principal Investigator (PI) The one individual designated by the applicant to provide the scientific and technical direction to a project supported by the funding agreement. 2.10 Research Institution (RI) A U.S. research institution is one that is: 1) a contractor-operated Federally funded research and development center, as identified by the National Science Foundation in accordance with the Government wide Federal Acquisition Regulation issued in Section 35(c)(1) of the Office of Federal Procurement Policy Act (or any successor legislation thereto), or 2) a nonprofit research institution as defined in Section 4(5) of the Stevenson-Wydler Technology Innovation Act of 1980, or 3) a nonprofit college or university. 2.11 Research or Research and Development (R/R&D) Any activity that is (1) a systematic, intensive study directed toward greater knowledge or understanding of the subject studied, (2) a systematic study directed specifically toward applying new knowledge to meet a recognized need, or (3) a systematic application of knowledge toward the production of useful materials, devices, systems, or methods, including the design, development, and improvement of prototypes and new processes to meet specific requirements. 2.12 SBIR/STTR Technical Data Technical data includes all data generated in the performance of any SBIR/STTR funding agreement. 2.13 SBIR/STTR Technical Data Rights The rights an SBC obtains for data generated in the performance of any SBIR/STTR funding agreement that an awardee delivers to the Government during or upon completion of a federally funded project, and to which the Government receives a license. 2.14 Small Business Concern (SBC) An SBC is one that, at the time of award of Phase 1 and Phase 2 funding agreements, meets the following criteria: (1) Is organized for profit, with a place of business located in the United States, which operates primarily within the United States or which makes a significant contribution to the United States economy through payment of taxes or use of American products, materials or labor; (2) is in the legal form of an individual proprietorship, partnership, limited liability company, corporation, joint venture, association, trust or cooperative; except that where the form is a joint venture, there can be no more than 49 percent participation by business entities in the joint venture; (3) is at least 51 percent owned and controlled by one or more individuals who are citizens of, or permanent resident aliens in, the United States: except in the case of a joint venture, where each entity to the venture must be 51 percent owned and controlled by one or more individuals who are citizens of, or permanent resident aliens in, the United States; and (4) has, including its affiliates, not more than 500 employees. The terms “affiliates” and “number of employees” are defined in greater detail in 13 CFR Part 121. 2.15 Socially and Economically Disadvantaged Individual A member of any of the following groups: African American, Hispanic American, Native American, Asian-Pacific American, Subcontinent-Asian American, other groups designated from time to time by SBA to be socially disadvantaged, or any other individual found to be socially and economically disadvantaged by SBA pursuant to Section 8(a) of the Small Business Act, 15 U.S.C. 637(a). 2.16 Socially and Economically Disadvantaged Small Business Concern A socially and economically disadvantaged SBC is one that is: (1) at least 51 percent owned by (i) an Indian tribe or a native Hawaiian organization: or, (ii) one or more socially and economically disadvantaged individuals; and (2) whose management and daily business operations are controlled by one or more socially and economically disadvantaged individuals. See 13 CFR Parts 124.103 and 124.104. 2.17 Subcontract Any agreement, other than one involving an employer-employee relationship, entered into by an awardee of a funding agreement calling for supplies or services for the performance of the original funding agreement. 2.18 United States Means the 50 States, the territories and possessions of the Federal Government, the Commonwealth of Puerto Rico, the District of Columbia, the Republic of the Marshall Islands, the Federated States of Micronesia, and the Republic of Palau. 2.19 Women-Owned Small Business A women-owned SBC is one that is at least 51 percent owned by a woman or women who also control and operate it. "Control" in this context means exercising the power to make policy decisions. "Operate" in this context means being actively involved in the day-to-day management. 3. Proposal Preparation Instructions and Requirements 3.1 Fundamental Considerations Multiple Proposal Submissions. Each proposal submitted must be based on a unique innovation, must be limited in scope to just one subtopic and may be submitted only under that one subtopic within each program. An offeror may submit any number of proposals, and may submit more than one proposal to the same subtopic; however, an offeror should not submit the same (or substantially equivalent) proposal to more than one subtopic. Submitting substantially equivalent proposals to several subtopics may result in all such proposals being rejected without evaluation. STTR: All Phase 1 proposals must provide sufficient information to convince NASA that the proposed SBC/RI cooperative effort represents a sound approach for converting technical information resident at the RI into a product or service that meets a need described in a Solicitation research topic. End Deliverables. The deliverable item at the end of a Phase 1 contract shall be a comprehensive report that justifies, validates, and defends the experimental and theoretical work accomplished and may include delivery of a product or service. Deliverable items for Phase 2 contracts include products or services in addition to required reporting of further developments or applications of the Phase 1 results. These deliverables may include prototypes, models, software, or complete products or services. The reported results of Phase 2 must address and provide the basis for validating the innovation and the potential for implementation of commercial applications. Reporting shall be submitted electronically via the SBIR/STTR homepage. NASA requests that all deliverable items be submitted in PDF format. Other acceptable formats are MS Word, MS Works, and WordPerfect. 3.2 Phase 1 Proposal Requirements 3.2.1 General Requirements Page Limitation. A Phase 1 proposal shall not exceed a total of 25 standard 8 1/2 x 11 inch (21.6 x 27.9 cm) pages inclusive of the technical content and the required forms. Proposal items required in Section 3.2.2 will be included within this total. Forms A, B, and C count as one page each. Each page shall be numbered consecutively at the bottom. Margins should be 1.0 inch (2.5 cm). Proposals exceeding the 25-page limitation will be rejected during administrative screening. Web site references, product samples, videotapes, slides, or other ancillary items will not be considered during the review process. Offerors are requested not to use the entire 25-page allowance unless necessary. Type Size. No type size smaller than 10 point shall be used for text or tables, except as legends on reduced drawings. Proposals prepared with smaller font sizes will be rejected without consideration. Header/Footer Requirements. Header must include firm name, proposal number, and project title. Footer must include the page number and proprietary markings if applicable. Margins can be used for header/footer information. Classified Information. NASA does not accept proposals that contain classified information. 3.2.2 Format Requirements. All required items of information must be covered in the proposal. The space allocated to each part of the technical content will depend on the project chosen and the offeror's approach. Each proposal submitted must contain the following items in the order presented: (1) Cover Sheet (Form A), electronically endorsed, (2) Proposal Summary (Form B), (3) Budget Summary (Form C), (4) Technical Content (11 parts in order as specified in Section 3.2.4, not to exceed 22 pages), including all graphics, with a table of contents, (5) Briefing Chart (Optional – not included in the 25-page limit and must not contain proprietary data). STTR: Each STTR proposal must also contain a Cooperative R/R&D Agreement between the SBC and RI following the required items listed above. The agreement is included as part of the 25-page limit. 3.2.3 Forms 3.2.3.1 Cover Sheet (Form A). A sample Cover Sheet form is provided in Section 8. The offeror shall provide complete information for each item and submit the form as required in Section 6. The proposal project title shall be concise and descriptive of the proposed effort. The title should not use acronyms or words like "Development of" or "Study of." The NASA research topic title must not be used as the proposal title. 3.2.3.2 Proposal Summary (Form B). A sample Proposal Summary form is provided in Section 8. The offeror shall provide complete information for each item and submit Form B as required in Section 6. Technical Abstract: Summary of the offeror’s proposed project is limited to 200 words and shall summarize the implications of the approach and the anticipated results of both Phase 1 and Phase 2. If the technical abstract is judged to be non responsive to the subtopic, the proposal will be rejected without further evaluation. Technology Taxonomy: Selections for the technology taxonomy are limited to technologies supported or relevant to the specific proposal. The listing of technologies for the taxonomy is provided in Section 8. Potential NASA and non-NASA commercial applications of the technology should also be presented. Note: The Cover Sheet (Form A) and the Proposal Summary (Form B), including the Technical Abstract, are public information and may be disclosed. Do not include proprietary information. 3.2.3.3 Budget Summary (Form C). The offeror shall complete the Budget Summary, following the instructions provided with the form (Section 8). A text box is provided on the electronic budget form for additional explanation. Information shall be submitted to explain the offeror’s plans for use of the requested funds to enable NASA to determine whether the proposed budget is fair and reasonable. The government is not responsible for any monies expended by the applicant before award of any contract. Property. Proposed costs for materials may be included. "Materials" means property that may be incorporated or attached to a deliverable end item or that may be consumed or expended in performing the contract. It includes assemblies, components, parts, raw materials, and small tools that may be consumed in normal use. Any purchase of equipment or products under an SBIR/STTR contract using NASA funds should be American-made to the extent possible. NASA will not fund the purchase of equipment, instrumentation, or facilities under SBIR/STTR contracts as a direct cost (Section 5.15). Travel. Travel during Phase 1 is not normally allowed to prove technical merit and feasibility of the proposed innovation. However, where the offeror deems travel to be essential for these purposes, it is necessary to limit it to one person, one trip to the sponsoring NASA installation. Proposed travel must be described as to purpose and benefits in proving feasibility, and is subject to negotiation and approval by the Contracting Officer. Trips to conferences are not allowed under the Phase 1 contract. Profit. A profit or fee may be included in the proposed budget as noted in Section 5.10. Cost Sharing. See Section 5.9. 3.2.4 Technical Content. This part of the submission shall not contain any budget data and must consist of all eleven parts listed below in the given order. All parts must be numbered and titled; parts that are not applicable must be noted as “Not Applicable.” Part 1: Table of Contents. The technical content shall begin with a brief table of contents indicating the page numbers of each of the parts of the proposal. The required table of contents is provided below: Phase 1 Table of Contents Part 1: Table of Contents……………………………………………………………………………Page # Part 2: Identification and Significance of the Innovation Part 3: Technical Objectives Part 4: Work Plan Part 5: Related R/R&D Part 6: Key Personnel and Bibliography of Directly Related Work Part 7: Relationship with Phase 2 or Future R/R&D Part 8: Company Information and Facilities Part 9: Subcontracts and Consultants Part 10: Potential Post Applications Part 11: Similar Proposals and Awards Part 2: Identification and Significance of the Innovation. The first paragraph of Part 2 shall contain: (1) A clear and succinct statement of the specific innovation proposed, and why it is an innovation, and (2) A brief explanation of how the innovation is relevant and important to meeting the technology need described in the subtopic. The initial paragraph shall contain no more than 200 words. NASA will reject proposals that lack explanation of the innovation. In subsequent paragraphs, Part 2 may also include appropriate background and elaboration to explain the proposed innovation. Part 3: Technical Objectives. State the specific objectives of the Phase 1 R/R&D effort including the technical questions that must be answered to determine the feasibility of the proposed innovation. Part 4: Work Plan. Include a detailed description of the Phase 1 R/R&D plan. The plan should indicate what will be done, where it will be done, and how the R/R&D will be carried out. The plan should address the objectives and the questions cited in Part 3 above. Discuss in detail the methods planned to achieve each objective or task. Task descriptions, schedules, resource allocations, estimated task hours for each key personnel, and planned accomplishments including project milestones shall be included. STTR: In addition, the work plan will specifically address the percentage and type of work to be performed by the SBC and the RI. The plan will provide evidence that the SBC will exercise management direction and control of the performance of the STTR effort, including situations in which the PI may be an employee of the RI. At least 40 percent of the work (amount requested including cost sharing, less fee, if any) is to be performed by the SBC as the prime contractor, and at least 30 percent of the work is to be performed by the RI. Part 5: Related R/R&D. Describe significant current and/or previous R/R&D that is directly related to the proposal including any conducted by the PI or by the offeror. Describe how it relates to the proposed effort and any planned coordination with outside sources. The offeror must persuade reviewers of his or her awareness of key recent R/R&D conducted by others in the specific subject area. At the offeror's option, this section may include concise bibliographic references in support of the proposal if they are confined to activities directly related to the proposed work. Part 6: Key Personnel and Bibliography of Directly Related Work. Identify key personnel involved in Phase 1 activities whose expertise and functions are essential to the success of the project. Provide bibliographic information including directly related education and experience. The PI is considered key to the success of the effort and must make a substantial commitment to the project. The following requirements are applicable: Functions. The functions of the PI are: planning and directing the project; leading it technically and making substantial personal contributions during its implementation; serving as the primary contact with NASA on the project; and ensuring that the work proceeds according to contract agreements. Competent management of PI functions is essential to project success. The Phase 1 proposal shall describe the nature of the PI's activities and the amount of time that the PI will personally apply to the project. The amount of time the PI proposes to spend on the project must be acceptable to the Contracting Officer. Qualifications. The qualifications and capabilities of the proposed PI and the basis for PI selection are to be clearly presented in the proposal. NASA has the sole right to accept or reject a substitute PI based on factors such as education, experience, demonstrated ability and competence, and any other evidence related to the specific assignment. Eligibility. This part shall also establish and confirm the eligibility of the PI (Section 1.5.3), and indicate the extent to which other proposals recently submitted or planned for submission in 2005 and existing projects commit the time of the PI concurrently with this proposed activity. Any attempt to circumvent the restriction on PIs working more than half time for an academic or a nonprofit organization by substituting an ineligible PI will result in rejection of the proposal. Part 7: Relationship with Phase 2 or Future R/R&D. State the anticipated results of the proposed R/R&D effort if the project is successful (through Phase 1 and Phase 2). Discuss the significance of the Phase 1 effort in providing a foundation for the Phase 2 R/R&D continuation. Part 8: Company Information and Facilities. Provide adequate information to allow the evaluators to assess the ability of the offeror to carry out the proposed Phase 1 and projected Phase 2 and Phase 3 activities. The offeror should describe the relevant facilities and equipment, their availability, and those to be acquired, to support the proposed activities. NASA will not fund the purchase of equipment, instrumentation, or facilities under Phase 1 contracts as a direct cost. Special tooling may be allowed. (Section 5.15) The capability of the offeror to perform the proposed activities and bring a resulting product or service to market must be indicated. Qualifications of the offeror in marketing related products or services or in raising capital should be presented. Note: Government wide SBIR and STTR policies prohibit the use of any SBIR/STTR award funds for the use of Government equipment and facilities. This does not preclude an SBC from utilizing a Government facility or Government equipment, but any charges for such use cannot be paid for with SBIR/STTR funds (SBA SBIR Policy Directive, Section 9 (f)(3)). In rare and unique circumstances, the SBA may issue a case-by-case waiver to this provision after review of an agency’s written justification. NASA cannot guarantee that a waiver from this policy can be obtained from SBA. If a proposed project or product demonstration requires the use of unique Government facilities or equipment that will be funded with SBIR dollars, the offeror must provide a) an explanation of why the SBIR/STTR research project requires the use of the Federal facility or personnel, including data that verifies the absence of non-Federal facilities or personnel capable of supporting the research effort, and b) a statement, signed by the appropriate Government official at the facility, verifying that it will be available for the required effort. The proposal should also include relevant information on the funding source(s) private, internal, or other Government. Failure to provide this explanation and the site manager’s written authorization of use may invalidate any proposal selection. If the offeror proposes the use of SBIR/STTR funds for Government equipment or facilities, this explanation will be provided to SBA during the Agency waiver process. Part 9: Subcontracts and Consultants. Subject to the restrictions set forth below, the SBC may establish business arrangements with other entities or individuals to participate in performance of the proposed R/R&D effort. The offeror must describe all subcontracting or other business arrangements, and identify the relevant organizations and/or individuals with whom arrangements are planned. The expertise to be provided by the entities must be described in detail, as well as the functions, services, number of hours and labor rates. Offerors are responsible for ensuring that all organizations and individuals proposed to be utilized are actually available for the time periods required. Documentation of subcontract costs must be made available during negotiations to substantiate the budget estimate. Subcontractors' and consultants' work must be performed in the United States. The following restrictions apply to the use of subcontracts/consultants: SBIRSTTRThe proposed business arrangements must not exceed one-third of the research and/or analytical work (amount requested including cost sharing if any, less fee, if any). The proposed business arrangements with individuals or organizations other than the RI must not exceed 30 percent of the work (amount requested including cost sharing if any, less fee, if any). Part 10: Potential Post Applications (Commercialization). The Phase 1 proposal shall forecast both the NASA and the non-NASA commercial potential of the project assuming success through Phase 2. The offeror, in the Phase 2 proposal, will be required to provide more detailed information regarding product development and potential markets (Section 3.3.4). Part 11: Similar Proposals and Awards. A firm may elect to submit proposals for essentially equivalent work to other Federal program solicitations (Section 2.4). Firms may also choose to resubmit previously unsuccessful proposals to NASA. However, it is unlawful to receive funding for essentially equivalent work already funded under any Government program. The Office of Inspector General has full access to all proposals submitted to NASA. The offeror must inform NASA of related proposals and awards and clearly state whether the SBC has submitted currently active proposals for similar work under other Federal Government program solicitations or intends to submit proposals for such work to other agencies. For all such cases, the following information is required: (a) The name and address of the agencies to which proposals have been or will be submitted, or from which awards have been received (including proposals that have been submitted to previous NASA SBIR Solicitations); (b) Dates of such proposal submissions or awards; (c) Title, number, and date of solicitations under which proposals have been or will be submitted or awards received; (d) The specific applicable research topic for each such proposal submitted or award received; (e) Titles of research projects; (f) Name and title of the PI/project manager for each proposal that has been or will be submitted, or from which awards have been received; (g) If resubmitting to NASA, please briefly describe how the proposal has been changed and/or updated since it was last submitted. Note: All eleven (11) parts of the technical proposal must be included. Parts that are not applicable must be included and marked “Not Applicable.” A proposal omitting any part will be considered non responsive to this Solicitation and will be rejected during administrative screening. 3.2.5 Cooperative R/R&D Agreement (Applicable for STTR proposals only). The Cooperative R/R&D Agreement (not to be confused with the Allocation of Rights Agreement, Section 4.1.4) is a single-page document electronically submitted and endorsed by the SBC and RI. A model agreement is provided, or firms can create their own custom agreement. The Cooperative R/R&D Agreement should be submitted as required in Section 6. This agreement counts toward the 25-page limit. 3.2.6 Prior Awards Addendum (Applicable for SBIR awards only). If the SBC has received more than 15 Phase 2 awards in the prior 5 fiscal years, submit name of awarding agency, date of award, funding agreement number, amount, topic or subtopic title, follow-on agreement amount, source, and date of commitment and current commercialization status for each Phase 2. The addendum is not included in the 25-page limit and content should be limited to information requested above. Offerors are encouraged to use spreadsheet format. 3.2.7 Briefing Chart (Optional). All technically meritorious proposals will be advocated to NASA senior management prior to selection. To assist NASA personnel in preparing information to advocate your proposal, a single-page briefing chart, as described in the on-line electronic handbook, is strongly encouraged. Submission of the briefing chart is optional, is not counted against the 25-page limit, and must not contain any proprietary data. An example chart has been provided in Appendix B. 3.3 Phase 2 Proposal Requirements 3.3.1 General Requirements. The Phase 1 contract will serve as a request for proposal (RFP) for the Phase 2 follow-on project. Phase 2 proposals are more comprehensive than those required for Phase 1. Submission of a Phase 2 proposal is in accordance with Phase 1 contract requirements and is voluntary. NASA assumes no responsibility for any proposal preparation expenses. Page Limitation. A Phase 2 proposal shall not exceed a total of 50 standard 8 1/2 x 11 inch (21.6 x 27.9 cm) pages. All items required in Section 3.3.2 will be included within this total. Forms A, B, and C count as one page each. Each page shall be numbered consecutively at the bottom. Margins should be 1.0 inch (2.5 cm). Proposals exceeding the 50-page limitation may be rejected during administrative screening. Type Size. No type size smaller than 10 point shall be used for text or tables, except as legends on reduced drawings. Proposals prepared with smaller font sizes will be rejected without consideration. Header/Footer Requirements. Header must include firm name, proposal number, and project title. Footer must include the page number and proprietary markings if applicable. Margins can be used for header/footer information. Classified Information. NASA does not accept proposals that contain classified information. 3.3.2 Format Requirements. All required items of information must be covered in the proposal. The space allocated to each part of the technical content will depend on the project and the offeror's approach. Each proposal submitted must contain the following items in the order presented: (1) Cover Sheet (Form A), electronically endorsed, (2) Proposal Summary (Form B), (3) Budget Summary (Form C), (4) Technical Content (11 Parts in order as specified in Section 3.3.4), including all graphics, and starting with a table of contents, (5) Briefing Chart (Optional – not included in the 50-page limit and must not contain proprietary data). STTR: Each STTR proposal must also contain a Cooperative R/R&D Agreement between the SBC and RI following the required items listed above. The agreement is included as part of the 50-page limit. 3.3.3 Forms 3.3.3.1 Cover Sheet (Form A). A sample copy of the Cover Sheet is provided in Section 8. The offeror shall provide complete information for each item and submit the form as required in Section 6. The proposal project title shall be concise and descriptive of the proposed effort. The title should not use acronyms or words like "Development of" or "Study of." The NASA research topic title must not be used as the proposal title. 3.3.3.2 Proposal Summary (Form B). A sample Proposal Summary form is provided in Section 8. The offeror shall provide complete information for each item and submit Form B as required in Section 6. Technical Abstract: Summary of the offeror’s proposed project is limited to 200 words and shall summarize the implications of the approach and the anticipated results of both Phase 1 and Phase 2. If the technical abstract is judged to be non responsive to the subtopic, the proposal will be rejected without further evaluation. Technology Taxonomy: Selections for the technology taxonomy are limited to technologies supported or relevant to the specific proposal. The listing of technologies for the taxonomy is provided in Section 8. Potential NASA and non-NASA commercial applications of the technology should also be presented. Note: The Cover Sheet (Form A) and the Proposal Summary (Form B), including the Technical Abstract, are public information and may be disclosed. Do not include proprietary information. 3.3.3.3. Budget Summary (Form C). The offeror shall complete the Budget Summary, following the instructions provided with the form (Section 8). A text box is provided on the electronic budget form for additional explanation. Information shall be submitted to explain the offeror’s plans for use of the requested funds to enable NASA to determine whether the proposed budget is fair and reasonable. The Government is not responsible for any monies expended by the applicant before award of any funding agreement. Property. Proposed costs for materials may be included. "Materials" means property that may be incorporated or attached to a deliverable end item or that may be consumed or expended in performing the contract. It includes assemblies, components, parts, raw materials, and small tools that may be consumed in normal use. Any purchase of equipment or products under an SBIR/STTR contract using NASA funds should be American-made to the extent possible. NASA will not fund the purchase of equipment, instrumentation, or facilities under SBIR/STTR contracts as a direct cost (Section 5.15). Travel. Travel during Phase 2 is not normally allowed to prove technical merit and feasibility of the proposed innovation. However, where the offeror deems travel to be essential for these purposes, it is necessary to limit it to one person, one trip to the sponsoring NASA installation. Proposed travel must be described as to purpose and benefits in proving feasibility, and is subject to negotiation and approval by the Contracting Officer. Trips to conferences are not allowed under the Phase 2 contract. Profit. A profit or fee may be included in the proposed budget as noted in Section 5.10. Cost Sharing. See Section 5.9. Requirement for Approved Accounting System. Offerors should note that in order to receive progress payments under a Phase 2 contract, an offeror must have in place, prior to award, an accounting system that in the Defense Contract Audit Agency’s (DCAA) opinion is adequate for accumulating costs. An approved accounting system can track costs to final cost objectives and segregate costs between direct and indirect. If you currently do not have an adequate accounting system, it is recommended that you take action to implement such a system. The lack of an adequate accounting system may preclude you from receiving a Phase 2 contract or may cause extended delays in award. For more information about cost proposals and accounting standards, please see the DCAA publication entitled “Information for Contractors” which is available at http://www.dcaa.mil/dcaap7641.90.pdf. 3.3.4 Technical Proposal. This part of the submission shall not contain any budget data and must consist of all eleven parts listed below in the given order. All parts must be numbered and titled; parts that are not applicable must be noted as “Not Applicable.” Part 1: Table of Contents. The technical content shall begin with a brief table of contents indicating the page numbers of each of the parts of the proposal. The required table of contents is provided below: Phase 2 Table of Contents Part 1: Table of Contents……………………………………………………………………………Page # Part 2: Identification and Significance of the Innovation and Results of the Phase 1 Proposal Part 3: Technical Objectives Part 4: Work Plan Part 5: Related R/R&D Part 6: Key Personnel Part 7: Phase 3 Efforts, Commercialization and Business Planning Part 8: Company Information and Facilities Part 9: Subcontracts and Consultants Part 10: Potential Post Applications Part 11: Similar Proposals and Awards Part 2: Identification and Significance of the Innovation and Results of the Phase 1 Proposal. Provide a brief explanation of the specific innovation and describe how it is relevant to meeting NASA’s technology needs. In addition, describe how the Phase 1 effort has proven the feasibility of the innovation, provided a rationale for both NASA and commercial applications, and demonstrated the ability of the offeror to conduct the required R/R&D. Part 3: Technical Objectives. Define the specific objectives of the Phase 2 research and technical approach. Part 4: Work Plan. Provide a detailed work plan defining specific tasks, performance schedules, project milestones, and deliverables. Part 5: Related R/R&D. Describe R/R&D related to the proposed work and affirm that the stated objectives have not already been achieved and that the same development is not presently being pursued elsewhere under contract to the Federal Government. Part 6: Key Personnel. Identify the key technical personnel for the project, confirm their availability for Phase 2, and discuss their qualifications in terms of education, work experience, and accomplishments relevant to the project. Part 7: Phase 3 Efforts, Commercialization and Business Planning. Describe plans for Phase 3 commercialization (including applications/sales back to NASA) in terms of each of the following areas: (1) Market Feasibility and Competition: Describe the target market of the product or service, the unique competitive advantage of the product, the potential market size (Government and/or non Government), the offeror’s estimated market share after first year of sales and after 5 years, and, competition from similar and alternative technologies and/or competing domestic or foreign entities. (2) Strategic Relevance to the Offeror: Describe the role the product or service has in the company’s current business plan and in its strategic planning for the next 5 years. (3) Key Management, Technical Personnel and Organizational Structure: Describe (a) the skills and experiences of key management and technical personnel in bringing innovative technology to the market, (b) current organizational structure, and (c) plans and timelines for obtaining needed business development expertise and other necessary personnel. (4) Production and Operations: Describe product development to date as well as milestones and plans for reaching production level, including plans for obtaining necessary physical resources. (5) Financial Planning: Delineate private financial resources dedicated to development of product or service (both business development and technical development) to date. Describe the expected financial needs and potential sources to meet those needs that will be necessary to bring product or service to market. Provide evidence of current financial condition, e.g., standard financial statements including a current cash flow statement. (6) Intellectual Property: Describe patent status, technology lead, trade secrets or other demonstration of a plan to achieve sufficient IP protection to realize the commercialization stage and attain at least a temporal competitive advantage. Part 8: Company Information and Facilities. Describe the capability of the firm to carry out Phase 2 and Phase 3 activities, including its organization, operations, number of employees, R/R&D capabilities, and experience relevant to the work proposed. This section shall also provide adequate information to allow the evaluators to assess the ability of the SBC to carry out the proposed Phase 2 activities. The offeror should describe the relevant facilities and equipment currently available, and those to be purchased, to support the proposed activities. NASA will not fund the acquisition of equipment, instrumentation, or facilities under Phase 2 contracts as a direct cost. Special tooling may be allowed. (Section 5.15) Note: Government-wide SBIR and STTR policies prohibit the use of any SBIR/STTR award funds for the use of Government equipment and facilities. This does not preclude an SBC from utilizing a Government facility or Government equipment, but any charges for such use cannot be paid for with SBIR/STTR funds (SBA SBIR Policy Directive, Section 9 (f)(3)). In rare and unique circumstances, SBA may issue a case-by-case waiver to this provision after review of an agency’s written justification. NASA cannot guarantee that a waiver from this policy can be obtained from SBA. If a proposed project or product demonstration requires the use of unique Government facilities or equipment that will be funded with SBIR dollars, the offeror must provide a) an explanation of why the SBIR/STTR research project requires the use of the Federal facility or personnel, including data that verifies the absence of non-Federal facilities or personnel capable of supporting the research effort, and b) a statement, signed by the appropriate Government official at the facility, verifying that it will be available for the required effort. The proposal should also include relevant information on the funding source(s) private, internal, or other Government. Failure to provide this explanation and the site manager’s written authorization of use may invalidate any proposal selection. If the offeror proposes the use of SBIR/STTR funds for Government equipment or facilities, this explanation will be provided to SBA during the Agency waiver process. Part 9: Subcontracts and Consultants. Subject to the restrictions set forth below, the SBC may establish business arrangements with other entities or individuals to participate in performance of the proposed R/R&D effort. The offeror must describe all subcontracting or other business arrangements, and identify the relevant organizations and/or individuals with whom arrangements are planned. The expertise to be provided by the entities must be described in detail, as well as the functions, services, number of hours and labor rates. Offerors are responsible for ensuring that all organizations and individuals proposed to be utilized are actually available for the time periods required. Documentation of subcontract costs must be made available during negotiations to substantiate the budget estimate. Subcontractors' and consultants' work must be performed in the United States. The following restrictions apply to the use of subcontracts/consultants: SBIR Phase 2 ProposalSTTR Phase 2 ProposalA minimum of one-half of the work (contract cost less profit) must be performed by the proposing SBC. A minimum of 40 percent of the work must be performed by the proposing SBC and 30 percent by the RI. Part 10: Potential Post Applications (Commercialization). Describe both the potential NASA and non-NASA commercial applications of the project assuming successful development of the proposed objectives. Part 11: Similar Proposals and Awards. If applicable, provide updated material (Reference Phase 1 Proposal Requirements, Part 11). 3.3.5 Capital Commitments Addendum Supporting Phase 2 and Phase 3. Describe and document capital commitments from non-SBIR/STTR sources or from internal SBC funds for pursuit of Phase 2 and Phase 3. Offerors for Phase 2 contracts are strongly urged to obtain non-SBIR/STTR funding support commitments for follow-on Phase 3 activities and additional support of Phase 2 from parties other than the proposing firm. Funding support commitments must show that a specific, substantial amount will be made available to the firm to pursue the stated Phase 2 and/or Phase 3 objectives. They must indicate the source, date, and conditions or contingencies under which the funds will be made available. Alternatively, self-commitments of the same type and magnitude that are required from outside sources can be considered. If Phase 3 will be funded internally, offerors should describe their financial position. Evidence of funding support commitments from outside parties must be provided in writing and should accompany the Phase 2 proposal. Letters of commitment should specify available funding commitments, other resources to be provided, and any contingent conditions. Expressions of technical interest by such parties in the Phase 2 research or of potential future financial support are insufficient and will not be accepted as support commitments by NASA. Letters of commitment should be added as an addendum to the Phase 2 proposal. This addendum will not be counted against the 50-page limitation. 3.3.6 Briefing Chart (Optional). All technically meritorious proposals will be advocated to NASA senior management prior to selection. To assist NASA personnel in preparing information to advocate your proposal, a single-page briefing chart, as described in the on line electronic handbook is strongly encouraged. Submission of the briefing chart is optional, is not counted against the 50-page limitation, and must not contain any proprietary data. An example chart has been provided in Appendix B. 3.4 SBA Data Collection Requirement Each SBC applying for a Phase 2 award is required to update the appropriate information in the Tech-Net database for any of its prior Phase 2 awards. In addition, upon completion of Phase 2, the SBC is required to update the appropriate information in the Tech-Net database and is requested to voluntarily update the information annually thereafter for a minimum period of five years. For complete information on what to enter, go to http://technet.sba.gov. 4. Method of Selection and Evaluation Criteria All Phase 1 and 2 proposals will be evaluated and judged on a competitive basis. Proposals will be initially screened to determine responsiveness. Proposals passing this initial screening will be technically evaluated by engineers or scientists to determine the most promising technical and scientific approaches. Each proposal will be judged on its own merit. The Agency is under no obligation to fund any proposal or any specific number of proposals in a given topic. It also may elect to fund several or none of the proposed approaches to the same topic or subtopic. 4.1 Phase 1 Proposals Proposals judged to be responsive to the administrative requirements of this Solicitation and having a reasonable potential of meeting a NASA need, as evidenced by the technical abstract included in the Proposal Summary (Form B), will be evaluated by evaluators with knowledge of the subtopic area. 4.1.1 Evaluation Process. Proposals should provide all information needed for complete evaluation. Evaluators do not seek additional information. Evaluations will be performed by NASA scientists and engineers at the Centers identified in the Solicitation for each subtopic. Also, qualified experts outside of NASA (including industry, academia, and other Government agencies) may assist in performing evaluations as required to determine or verify the merit of a proposal. Offerors should not assume that evaluators are acquainted with the firm, key individuals, or with any experiments or other information. Any pertinent references or publications should be noted in Part 5 of the technical proposal. 4.1.2 Phase 1 Evaluation Criteria. NASA plans to select for award those proposals offering the best value to the Government and the Nation. NASA will give primary consideration to the scientific and technical merit and feasibility of the proposal and its benefit to NASA. Each proposal will be judged and scored on its own merits using the factors described below: Factor 1. Scientific/Technical Merit and Feasibility The proposed R/R&D effort will be evaluated on whether it offers a clearly innovative and feasible technical approach to the described NASA problem area. Proposals must clearly demonstrate relevance to the subtopic. Specific objectives, approaches and plans for developing and verifying the innovation must demonstrate a clear understanding of the problem and the current state of the art. The degree of understanding and significance of the risks involved in the proposed innovation must be presented. Factor 2. Experience, Qualifications and Facilities The technical capabilities and experience of the PI or project manager, key personnel, staff, consultants and subcontractors, if any, are evaluated for consistency with the research effort and their degree of commitment and availability. The necessary instrumentation or facilities required must be shown to be adequate and any reliance on external sources, such as Government Furnished Equipment or Facilities, addressed (Section 5.15). Factor 3. Effectiveness of the Proposed Work Plan The work plan will be reviewed for its comprehensiveness, effective use of available resources, cost management and proposed schedule for meeting the Phase 1 objectives. The methods planned to achieve each objective or task should be discussed in detail. STTR: The clear delineation of the responsibilities of the SBC and RI for the success of the proposed cooperative R/R&D effort will be evaluated. The offeror must demonstrate the ability to organize for effective conversion of intellectual property into products or services of value to NASA and the commercial marketplace. Factor 4. Commercial Potential and Feasibility The proposal will be evaluated for any potential commercial applications in the private sector or for use by the Federal Government, as evidenced by the SBC’s record of commercializing SBIR or other research, the existence of second phase funding commitments from private sector or non-SBIR funding sources, the existence of third phase follow-on commitments for the subject of the research, and the presence of other indicators of the commercial potential of the innovation. Scoring of Factors and Weighting: Factors 1, 2, and 3 will be scored numerically with Factor 1 worth 50 percent and Factors 2 and 3 each worth 25 percent. The sum of the scores for Factors 1, 2, and 3 will comprise the Technical Merit score. The evaluation for Factor 4, Commercial Potential and Feasibility, will be in the form of an adjectival rating (Excellent, Very Good, Average, Below Average, Poor). For Phase 1 proposals, Technical Merit carries more weight than Commercial Merit. 4.1.3 Selection. Each Center will make recommendations for award among those proposals that it evaluates. Center recommendations will be forwarded to the Program Management Office for analysis and presented to the Source Selection Official and Mission Directorate Representatives. Final selection decisions will consider the recommendations as well as overall NASA priorities, program balance and available funding. Recommendations provided by the Centers do not guarantee selection for award. The Source Selection Official has the final authority for choosing the specific proposals for contract negotiation. The list of proposals selected for negotiation will be posted on the NASA SBIR/STTR Homepage (http://sbir.nasa.gov). All firms will receive a formal notification letter. A Contracting Officer will negotiate an appropriate contract to be signed by both parties before work begins. 4.1.4 Allocation of Rights Agreement (STTR awards only). After being selected for Phase 1 contract negotiations, but before the contract starts, the offeror shall provide to the Contracting Officer, a completed Allocation of Rights Agreement (ARA), which has been signed by authorized representatives of the SBC, RI and subcontractors and consultants, as applicable. The ARA shall state the allocation of intellectual property rights with respect to the proposed STTR activity and planned follow-on research, development and/or commercialization. 4.2 Phase 2 Proposals 4.2.1 Evaluation Process. The Phase 2 evaluation process is similar to the Phase 1 process. NASA plans to select for award those proposals offering the best value to the Government and the Nation. Each proposal will be reviewed by NASA scientists and engineers and by qualified experts outside of NASA as needed. In addition, those proposals with high technical merit will be reviewed for commercial merit. NASA uses a peer review panel to evaluate commercial merit. Panel membership will include non-NASA personnel expert in business development and technology commercialization. 4.2.2 Evaluation Factors. The evaluation of Phase 2 proposals under this Solicitation will apply the following factors: Factor 1. Scientific/Technical Merit and Feasibility The proposed R/R&D effort will be evaluated on its innovativeness, originality, and potential technical value, including the degree to which Phase 1 objectives were met, the feasibility of the innovation, and whether the Phase 1 results indicate a Phase 2 project is appropriate. Factor 2. Experience, Qualifications and Facilities The technical capabilities and experience of the PI or project manager, key personnel, staff, consultants and subcontractors, if any, are evaluated for consistency with the research effort and their degree of commitment and availability. The necessary instrumentation or facilities required must be shown to be adequate and any reliance on external sources, such as Government Furnished Equipment or Facilities, addressed (Section 5.15). Factor 3. Effectiveness of the Proposed Work Plan The work plan will be reviewed for its comprehensiveness, effective use of available resources, cost management and proposed schedule for meeting the Phase 1 objectives. The methods planned to achieve each objective or task should be discussed in detail. Factor 4. Commercial Potential and Feasibility. NASA will assess the proposed commercialization plan in terms of its credibility, objectivity, reasonableness of key assumptions and awareness of key risk areas and critical business vulnerabilities, as applicable to the following factors: (1) Commercial potential of the technology: This includes assessment of (a) a well-defined commercial product or service; (b) a realistic target market niche; (c) a commercial product or service that has strong potential for uniquely meeting a well-defined need within the target market; and (d) a commitment of necessary financial, physical, and/or personnel resources. (2) Commercial intent of the offeror: This includes assessing the commercial venture for (a) importance to the offeror’s current business and strategic planning; (b) reliance on (or lack thereof) Government markets; and (c) adequacy of funding sources necessary to bring technology to identified market. (3) Capability of the offeror to realize commercialization: This includes assessment of (a) the offeror’s past success in bringing SBIR/STTR or other innovative technology to commercial application; (b) the offeror’s business plan; (c) the likelihood that the offeror will be able to obtain the remaining necessary financial, technical, and personnel-related resources; and (d) the current strength and continued financial viability of the offeror. In applying these commercial criteria, NASA will assess proposal information in terms of credibility, objectivity, reasonableness of key assumptions, independent corroborating evidence, internal consistency, demonstrated awareness of key risk areas and critical business vulnerabilities, and other indicators of sound business analysis and judgment. 4.2.3 Evaluation and Selection. Factors 1, 2, and 3 will be scored numerically with Factor 1 worth 50 percent and Factors 2 and 3 each worth 25 percent. The sum of the scores for Factors 1, 2, and 3 will comprise the Technical Merit score. Proposals receiving numerical scores of 85 percent or higher will be evaluated and rated for their commercial potential using the criteria listed in Factor 4 and by applying the same adjectival ratings as set forth for Phase 1 proposals. Where technical evaluations are essentially equal in potential, cost to the Government may be considered in determining successful offerors. For Phase 2 proposals, commercial merit is a critical factor. Each Center will make recommendations for award among those proposals that it evaluates. The Center recommendations will be forwarded to the Program Management Office for analysis and presented to the Source Selection Official and Mission Directorate Representatives. Final selection decisions will consider the recommendations, overall NASA priorities, program balance and available funding, as well as any other evaluations or assessments (particularly pertaining to commercial potential). Recommendations provided by the Centers do not guarantee selection for award. The Source Selection Official has the final authority for choosing the specific proposals for contract negotiation. Note: Companies with Prior NASA SBIR Awards NASA has instituted a comprehensive commercialization survey/data gathering process for companies with prior NASA SBIR awards. Information received from SBIR companies completing the survey is kept confidential, and will not be made public except in broad aggregate, with no company-specific attribution. Responding to the survey is strictly voluntary. However, the SBIR Source Selection Official does see the information contained within the survey as adding to the program's ability to use past performance in decision making as well as providing a database of SBIR/STTR results for management. If you have not completed a survey, or if you would like to update a previously submitted response, please go on line at http://sbir.nasa.gov/SBIR/survey.html. 4.3 Debriefing of Unsuccessful Offerors After Phase 1 and Phase 2 selection decisions have been announced, debriefings for unsuccessful proposals will be available to the offeror's corporate official or designee via e-mail. Telephone requests for debriefings will not be accepted. Debriefings are not opportunities to reopen selection decisions. They are intended to acquaint the offeror with perceived strengths and weaknesses of the proposal and perhaps identify constructive future action by the offeror. Debriefings will not disclose the identity of the proposal evaluators, proposal scores, the content of, or comparisons with, other proposals. 4.3.1 Phase 1 Debriefings. For Phase 1 proposals, debriefings will be automatically e-mailed to the designated business official within 60 days of the selection announcement. If you have not received your debriefing by this time, contact the SBIR/STTR Program Support Office at sbir@reisys.com. 4.3.2 Phase 2 Debriefings. The offeror will be contacted by the appropriate Field Center for debriefing within 60 days of the selection announcement. If you have not received your debriefing by this time, contact the appropriate SBIR/STTR Field Center Program Manager. 5. Considerations 5.1 Awards 5.1.1 Availability of Funds. Both Phase 1 and Phase 2 awards are subject to availability of funds. NASA has no obligation to make any specific number of Phase 1 or Phase 2 awards based on this Solicitation, and may elect to make several or no awards in any specific technical topic or subtopic. SBIRSTTR> NASA plans to announce the selection of approximately 300 proposals resulting from this Solicitation, for negotiation of Phase 1 contracts with values not exceeding $70,000. Following contract negotiations and awards, Phase 1 contractors will have up to 6 months to carry out their programs, prepare their final reports, and submit Phase 2 proposals. > NASA anticipates that approximately 40 percent of the successfully completed Phase 1 projects from the SBIR 2005 Solicitation will be selected for Phase 2. Phase 2 agreements are fixed-price contracts with performance periods not exceeding 24 months and funding not exceeding $600,000. > NASA plans to announce the selection of approximately 40 proposals resulting from this Solicitation, for negotiation of Phase 1 contracts with values not exceeding $100,000. Following contract negotiations and awards, Phase 1 contractors will have up to 12 months to carry out their programs, prepare their final reports, and submit Phase 2 proposals. > NASA anticipates that approximately 40 percent of the successfully completed Phase 1 projects from the STTR 2005 Solicitation will be selected for Phase 2. Phase 2 agreements are fixed-price contracts with performance periods not exceeding 24 months and funding not exceeding $600,000. 5.1.2 Contracting. Fixed-price contracts will be issued for both Phase 1 and Phase 2 awards. Simplified contract documentation is employed; however, SBCs selected for award can reduce processing time by examining the procurement documents, submitting signed representations and certifications, and responding to the Contracting Officer in a timely manner. NASA will make a Phase 1 model contract and other documents available to the public on the NASA SBIR/STTR homepage (http://sbir.nasa.gov) at the time of the selection announcement. From the time of proposal selection until the award of a contract, only the Contracting Officer is authorized to commit the Government, and all communications must be through the Contracting Officer. Note: Costs incurred prior to and in anticipation of award of a contract are entirely the risk of the contractor in the event that a contract is not subsequently awarded. 5.2 Phase 1 Reporting Interim progress reports are required as described in the contract. These reports shall document progress made on the project and activities required for completion to provide NASA the basis for determining whether the payment is warranted. A final report must be submitted to NASA upon completion of the Phase 1 R/R&D effort in accordance with contract provisions. It shall elaborate the project objectives, work carried out, results obtained, and assessments of technical merit and feasibility. The final report shall include a single-page summary as the first page, in a format provided in the Phase 1 contract, identifying the purpose of the R/R&D effort and describing the findings and results, including the degree to which the Phase 1 objectives were achieved, and whether the results justify Phase 2 continuation. The potential applications of the project results in Phase 3 either for NASA or commercial purposes shall also be described. The final project summary is to be submitted without restriction for NASA publication. All reports are required to be submitted electronically via the SBIR/STTR homepage. 5.3 Payment Schedule for Phase 1 Payments are commonly authorized as follows: one-third at the time of award, one-third at project mid-point after award, and the remainder upon acceptance of the final report by NASA. The first two payments will be made 30 days after receipt of valid invoices. The final payment will be made 30 days after acceptance of the final report, the New Technology Report, and other deliverables as required by the contract. Electronic funds transfer will be employed and offerors will be required to submit account data if selected for contract negotiations. 5.4 Release of Proposal Information In submitting a proposal, the offeror agrees to permit the Government to disclose publicly the information contained on the Proposal Cover (Form A) and the Proposal Summary (Form B). Other proposal data is considered to be the property of the offeror, and NASA will protect it from public disclosure to the extent permitted by law including the Freedom of Information Act. 5.5 Access to Proprietary Data by Non-NASA Personnel 5.5.1 Non-NASA Reviewers. In addition to Government personnel, NASA, at its discretion and in accordance with 1815.207-71 of the NASA FAR Supplement, may utilize qualified individuals from outside the Government in the proposal review process. Any decision to obtain an outside evaluation shall take into consideration requirements for the avoidance of organizational or personal conflicts of interest and the competitive relationship, if any, between the prospective contractor or subcontractor(s) and the prospective outside evaluator. Any such evaluation will be under agreement with the evaluator that the information (data) contained in the proposal will be used only for evaluation purposes and will not be further disclosed. 5.5.2 Non-NASA Access to Confidential Business Information. In the conduct of proposal processing and potential contract administration the Agency may find it necessary to provide access to proposals to other NASA contractor and subcontractor personnel. NASA will provide access to such data only under contracts that contain an appropriate Handling of Data clause that requires the contractors to fully protect the information from unauthorized use or disclosure. 5.6 Final Disposition of Proposals The Government retains ownership of proposals accepted for evaluation, and such proposals will not be returned to the offeror. Copies of all evaluated Phase 1 proposals will be retained for a minimum of one year after the Phase 1 selections have been made. Successful proposals will be retained in accordance with contract file regulations. 5.7 Proprietary Information in the Proposal Submission Information contained in unsuccessful proposals will remain the property of the applicant. The Government may, however, retain copies of all proposals. Public release of information in any proposal submitted will be subject to existing statutory and regulatory requirements. If proprietary information is provided by an applicant in a proposal, which constitutes a trade secret, proprietary commercial or financial information, confidential personal information or data affecting the national security, it will be treated in confidence to the extent permitted by law. This information must be clearly marked by the applicant as confidential proprietary information. NASA will treat in confidence pages listed as proprietary in the following legend that appears on Cover Sheet (Form A) of the proposal: "This data shall not be disclosed outside the Government and shall not be duplicated, used, or disclosed in whole or in part for any purpose other than evaluation of this proposal, provided that a funding agreement is awarded to the offeror as a result of or in connection with the submission of this data, the Government shall have the right to duplicate, use or disclose the data to the extent provided in the funding agreement and pursuant to applicable law. This restriction does not limit the Government's right to use information contained in the data if it is obtained from another source without restriction. The data subject to this restriction are contained in pages ____ of this proposal." Note: Do not label the entire proposal proprietary. The Proposal Cover (Form A), the Proposal Summary (Form B), and the Optional Briefing Chart should not contain proprietary information. 5.8 Limited Rights Information and Data Rights to data used in, or first produced under, any Phase 1 or Phase 2 contract are specified in the clause at FAR 52.227-20, Rights in Data--SBIR/STTR Program. The clause provides for rights consistent with the following: 5.8.1 Non Proprietary Data. Some data of a general nature are to be furnished to NASA without restriction (i.e., with unlimited rights) and may be published by NASA. These data will normally be limited to the project summaries accompanying any periodic progress reports and the final reports required to be submitted. The requirement will be specifically set forth in any contract resulting from this Solicitation. 5.8.2 Proprietary Data. When data that is required to be delivered under an SBIR/STTR contract qualifies as “proprietary,” i.e., either data developed at private expense that embody trade secrets or are commercial or financial and confidential or privileged, or computer software developed at private expense that is a trade secret, the contractor, if the contractor desires to continue protection of such proprietary data, shall not deliver such data to the Government, but instead shall deliver form, fit, and function data. 5.8.3 Non Disclosure Period. For a period of 4 years after acceptance of all items to be delivered under this contract, the Government agrees to use these data for Government purposes only, and they shall not be disclosed outside the Government (including disclosure for procurement purposes) during such period without permission of the Contractor, except that, subject to the foregoing use and disclosure prohibitions, such data may be disclosed for use by support Contractors. After the aforesaid 4-year period the Government has a royalty-free license to use, and to authorize others to use on its behalf, these data for Government purposes, but is relieved of all disclosure prohibitions and assumes no liability for unauthorized use of these data by third parties. 5.8.4 Copyrights. Subject to certain licenses granted by the contractor to the Government, the contractor receives copyright to any data first produced by the contractor in the performance of an SBIR/STTR contract. 5.8.5 Patents. The contractor may normally elect title to any inventions made in the performance of an SBIR/STTR contract. The Government receives a nonexclusive license to practice or have practiced for or on behalf of the Government each such invention throughout the world. Small business concerns normally may retain the principal worldwide patent rights to any invention developed with Government support. The Government receives a royalty-free license for Federal Government use, reserves the right to require the patent holder to license others in certain circumstances, and requires that anyone exclusively licensed to sell the invention in the United States must normally manufacture it domestically. In accordance with the Patent Rights Clause (FAR 52.227-11), SBIR/STTR contractors must disclose all subject inventions, which means any invention or discovery which is or may be patentable and is conceived or first actually reduced to practice in the performance of the contract. Once disclosed, the contractor has 2 years to decide whether to elect title. If the contractor fails to do so within the 2-year time period, the Government has the right to obtain title. To the extent authorized by 35 USC 205, the Government will not make public any information disclosing such inventions, allowing the contractor the allowable time to file a patent. Costs associated with patent applications are not allowable. 5.8.6 Invention Reporting. Awardees must report inventions to the awarding agency within 2 months of the inventor’s report to the awardee. The reporting of inventions should be accomplished in accordance with the negotiated contract. 5.9 Cost Sharing Cost sharing occurs when a Contractor proposes to bear some of the burden of reasonable, allocable and allowable contract costs. Cost sharing is permitted, but not required for proposals under this Solicitation. Cost sharing is not an evaluation factor in consideration of your proposal. Cost sharing, if included, should be shown in the budget summary. No profit will be paid on the cost-sharing portion of the contract. STTR: If cost sharing is proposed, then these added funds shall be included in the 40/30 work percentage distribution and reflected in the Summary Budget (Form C). 5.10 Profit or Fee Both Phase 1 and Phase 2 contracts may include a reasonable profit. The reasonableness of proposed profit is determined by the Contracting Officer during contract negotiations. Reference FAR 15.404-4. 5.11 Joint Ventures and Limited Partnerships Both joint ventures and limited partnerships are permitted, provided the entity created qualifies as an SBC in accordance with the definition in Section 2.14. A statement of how the work load will be distributed, managed, and charged should be included in the proposal. A copy or comprehensive summary of the joint venture agreement or partnership agreement should be appended to the proposal. This will not count as part of the 25-page limit for the Phase 1 proposal. 5.12 Similar Awards and Prior Work If an award is made pursuant to a proposal submitted under either SBIR or STTR Solicitations, the firm will be required to certify that it has not previously been paid nor is currently being paid for essentially equivalent work by any agency of the Federal Government. Failure to acknowledge or report similar or duplicate efforts can lead to the termination of contracts or civil or criminal penalties. 5.13 Contractor Commitments Upon award of a contract, the contractor will be required to make certain legal commitments through acceptance of numerous clauses in the Phase 1 contract. The outline that follows illustrates the types of clauses that will be included. This is not a complete list of clauses to be included in Phase 1 contracts, nor does it contain specific wording of these clauses. Copies of complete provisions will be made available prior to contract negotiations. 5.13.1 Standards of Work. Work performed under the contract must conform to high professional standards. Analyses, equipment, and components for use by NASA will require special consideration to satisfy the stringent safety and reliability requirements imposed in aerospace applications. 5.13.2 Inspection. Work performed under the contract is subject to Government inspection and evaluation at all reasonable times. 5.13.3 Examination of Records. The Comptroller General (or a duly authorized representative) shall have the right to examine any directly pertinent records of the contractor involving transactions related to the contract. 5.13.4 Default. The Government may terminate the contract if the contractor fails to perform the contracted work. 5.13.5 Termination for Convenience. The contract may be terminated by the Government at any time if it deems termination to be in its best interest, in which case the contractor will be compensated for work performed and for reasonable termination costs. 5.13.6 Disputes. Any dispute concerning the contract that cannot be resolved by mutual agreement shall be decided by the Contracting Officer with right of appeal. 5.13.7 Contract Work Hours. The contractor may not require a non-exempt employee to work more than 40 hours in a work week unless the employee is paid for overtime. 5.13.8 Equal Opportunity. The contractor will not discriminate against any employee or applicant for employment because of race, color, religion, age, sex, or national origin. 5.13.9 Affirmative Action for Veterans. The contractor will not discriminate against any employee or applicant for employment because he or she is a disabled veteran or veteran of the Vietnam era. 5.13.10 Affirmative Action for Handicapped. The contractor will not discriminate against any employee or applicant for employment because he or she is physically or mentally handicapped. 5.13.11 Officials Not to Benefit. No member of or delegate to Congress shall benefit from an SBIR or STTR contract. 5.13.12 Covenant Against Contingent Fees. No person or agency has been employed to solicit or to secure the contract upon an understanding for compensation except bona fide employees or commercial agencies maintained by the contractor for the purpose of securing business. 5.13.13 Gratuities. The contract may be terminated by the Government if any gratuities have been offered to any representative of the Government to secure the contract. 5.13.14 Patent Infringement. The contractor shall report to NASA each notice or claim of patent infringement based on the performance of the contract. 5.13.15 American-Made Equipment and Products. Equipment or products purchased under an SBIR or STTR contract must be American-made whenever possible. 5.13.16 Export Control Laws. The contractor shall comply with all U.S. export control laws and regulations, including the International Traffic in Arms Regulations (ITAR) and the Export Administration Regulations (EAR). Offerors are responsible for ensuring that all employees who will work on this contract are eligible under export control and International Traffic in Arms (ITAR) regulations. Any employee who is not a U.S. citizen or a permanent resident may be restricted from working on this contract if the technology is restricted under export control and ITAR regulations unless the prior approval of the Department of State or the Department of Commerce is obtained via a technical assistance agreement or an export license. Violations of these regulations can result in criminal or civil penalties. 5.14 Additional Information 5.14.1 Precedence of Contract Over Solicitation. This Program Solicitation reflects current planning. If there is any inconsistency between the information contained herein and the terms of any resulting SBIR/STTR contract, the terms of the contract are controlling. 5.14.2 Evidence of Contractor Responsibility. Before award of an SBIR or STTR contract, the Government may request the offeror to submit certain organizational, management, personnel, and financial information to establish responsibility of the offeror. Contractor responsibility includes all resources required for contractor performance, i.e., financial capability, work force, and facilities. 5.14.3 Central Contractor Registration: Offerors should be aware of the requirement to register in the Central Contractor Registration (CCR) database prior to contract award. To avoid a potential delay in contract award, offerors are strongly encouraged to register prior to submitting a proposal. The CCR database is the primary repository for contractor information required for the conduct of business with NASA. It is maintained by the Department of Defense. To be registered in the CCR database, all mandatory information, which includes the DUNS or DUNS+4 number, and a CAGE code, must be validated in the CCR system. The DUNS number or Data Universal Number System is a 9-digit number assigned by Dun and Bradstreet Information Services (http://www.dnb.com) to identify unique business entities. The DUNS+4 is similar, but includes a 4-digit suffix that may be assigned by a parent (controlling) business concern. The CAGE code or Commercial Government and Entity Code is assigned by the Defense Logistics Information Service (DLIS) to identify a commercial or Government entity. If an SBC does not have a CAGE code, one will be assigned during the CCR registration process. The DoD has established a goal of registering an applicant in the CCR database within 48 hours after receipt of a complete and accurate application via the Internet. However, registration of an applicant submitting an application through a method other than the Internet may take up to 30 days. Therefore, offerors that are not registered should consider applying for registration immediately upon receipt of this solicitation. Offerors and contractors may obtain information on CCR registration and annual confirmation requirements via the Internet at http://www.ccr.gov or by calling 888-CCR-2423 (888-227-2423). 5.14.4 Software Development Standards: Offerors proposing projects involving the development of software should note that NASA has adopted a software engineering procedural requirement. Developers should comply with the requirements of NASA Procedural Requirements (NPR) 7150.2, “NASA Software Engineering Requirements.” In particular, the requirements of Sections 5.27 and 5.28 should be noted as compliance will be required. NPR 7150.2 is available online at http://nodis3.gsfc.nasa.gov/lib_docs.cfm?range=7___. 5.15 Property and Facilities In accordance with the Federal Acquisition Regulations (FAR) Part 45, it is NASA's policy not to provide facilities (capital equipment, tooling, test and computer facilities, etc.) for the performance of work under SBIR/STTR contracts. An SBC will furnish its own facilities to perform the proposed work as an indirect cost to the contract. Special tooling required for a project may be allowed as a direct cost. When an SBC cannot furnish its own facilities to perform required tasks, an SBC may propose to acquire the use of available non Government facilities. Rental or lease costs may be considered as direct costs as part of the total funding for the project. If unique requirements force an offeror to acquire facilities under a NASA contract, they will be purchased as Government Furnished Equipment (GFE) and will be titled to the Government. An offeror may propose the use of unique or one-of-a-kind Government facilities if essential for the research. If a proposed project or product demonstration requires the use of unique Government facilities or equipment that will be funded with SBIR dollars, the offeror must provide a) an explanation of why the SBIR/STTR research project requires the use of the Federal facility or personnel, including data that verifies the absence of non-Federal facilities or personnel capable of supporting the research effort, and b) a statement, signed by the appropriate Government official at the facility, verifying that it will be available for the required effort. The proposal should also include relevant information on the funding source(s) private, internal, or other Government. Failure to provide this explanation and the site manager’s written authorization of use may invalidate any proposal selection. If the offeror proposes the use of SBIR/STTR funds for Government equipment or facilities, this explanation will be provided to SBA during the Agency waiver process. 5.16 False Statements Knowingly and willfully making any false, fictitious, or fraudulent statements or representations may be a felony under the Federal Criminal False Statement Act (18 U.S.C. Sec 1001), punishable by a fine of up to $10,000, up to five years in prison, or both. 6. Submission of Proposals 6.1 Submission Requirements NASA utilizes a paperless, electronic process for management of the SBIR/STTR programs. This management approach requires that a proposing firm have Internet access and an e-mail address. Paper submissions are not accepted. An Electronic Handbook for submitting proposals via the internet is hosted on the NASA SBIR/STTR Homepage (http://sbir.nasa.gov). The handbook will guide the firms through the various steps required for submitting an SBIR/STTR proposal. All electronic handbook submissions are through a secure connection. Communication between NASA and the firm is through a combination of electronic handbooks and e-mail. 6.2 Submission Process To begin the submission process, SBCs must first register in the handbook. It is recommended that the Business Official, or an authorized representative designated by the Business Official, be the first person to register for the SBC. The SBC’s Employer Identification Number (EIN)/Taxpayer Identification Number is required during registration. For successful proposal submission, SBCs must complete all three forms online, upload their technical proposal in an acceptable format, and have the Business Official electronically endorse the proposal. Electronic endorsement of the proposal is handled online with no additional software requirements. The term “technical proposal” refers to the part of the submission as described in Section 3.2.4 for Phase 1 and 3.3.4 for Phase 2. STTR: The Research Institution is required to electronically endorse the Cooperative Agreement prior to the SBC endorsement of the completed proposal submission. 6.2.1 What Needs to Be Submitted. The entire proposal including Forms A, B, and C must be submitted via the Submissions Handbook located on the NASA SBIR/STTR website. a. Forms A, B, and C are to be completed online. b. The technical proposal is uploaded from your computer via the Internet utilizing secure communication protocol. c. Firms are encouraged to upload an optional briefing chart, which is not included in the page count (See Sections 3.2.7 and 3.3.6). Note: Other forms of submissions such as postal, paper, fax, diskette, or e-mail attachments are not acceptable. 6.2.2 Technical Proposal Submissions. NASA converts all technical proposal files to PDF format for evaluation purposes. Therefore, NASA requests that technical proposals be submitted in PDF format, and encourages companies to do so. Other acceptable formats are MS Works, MS Word, and WordPerfect. Unix and TeX users please note that due to PDF difficulties with non-standard fonts, output technical proposal files in DVI format. Graphics. For reasons of space conservation and simplicity the offeror is encouraged, but not required, to embed graphics within the document. For graphics submitted as separate files, the acceptable file formats (and their respective extensions) are: Bit-Mapped (.bmp), Graphics Interchange Format (.gif), JPEG (.jpg), PC Paintbrush (.pcx), WordPerfect Graphic (.wpg), and Tagged-Image Format (.tif). Virus Check. The offeror is responsible for performing a virus check on each submitted technical proposal. As a standard part of entering the proposal into the processing system, NASA will scan each submitted electronic technical proposal for viruses. The detection, by NASA, of a virus on any electronically submitted technical proposal, may cause rejection of the proposal. 6.2.3 Technical Proposal Uploads. Firms will upload their proposals using the Submissions Electronic Handbook. Directions will be provided to assist users. All transactions via the electronic handbook are encrypted for security. Proposals can be uploaded multiple times with each new upload replacing the previous version. An e-mail will be sent acknowledging each successful upload. An example is provided below: Sample E-mail for Successful Upload of Technical Proposal Subject: Successful Upload of Technical Proposal Upload of Technical Document for your NASA SBIR/STTR Proposal No. _________ This message is to confirm the successful upload of your technical proposal document for: Proposal No. ____________ (Uploaded File Name/Size/Date) Please note that any previous uploads are no longer considered as part of your submission. This e-mail is NOT A RECEIPT OF SUBMISSION of your entire proposal IMPORTANT! The Business Official or an authorized representative must electronically endorse the proposal in the Electronic Handbook using the “Sign Proposal” step. Upon endorsement, you will receive an e-mail that will be your official receipt of proposal submission. . Thank you for your participation in NASA’s SBIR/STTR program. NASA SBIR/STTR Program Support Office You may upload the technical proposal multiple times but only the final uploaded and electronically endorsed version will be considered for review. 6.3 Deadline for Phase 1 Proposal Receipt All Phase 1 proposal submissions must be received no later than 5:00 p.m. EDT on Wednesday, September 7, 2005, via the NASA SBIR/STTR homepage (http://sbir.nasa.gov). The server/electronic handbook will not be available for Internet submissions after this deadline. Any proposal received after that date and time shall be considered late and handled according to NASA FAR Supplement 1815.208. 6.4 Acknowledgment of Proposal Receipt The final proposal submission includes successful completion of Form A (electronically endorsed by the SBC Official), Form B, Form C, and the uploaded technical proposal. NASA will acknowledge receipt of electronically submitted proposals upon endorsement by the SBC Official to the SBC Official’s e-mail address as provided on the proposal cover sheet. If a proposal acknowledgment is not received, the offeror should call NASA SBIR/STTR Program Support Office at 301-937-0888. An example is provided below: Sample E-mail for Official Confirmation of Receipt of Full Proposal: Subject: Official Receipt of your NASA SBIR/STTR Proposal No. _______________ Confirmation No. __________________ This message is to acknowledge electronic receipt of your NASA SBIR/STTR Proposal No. _______________. Your proposal, including the forms and the technical document, has been received at the NASA SBIR/STTR Support Office. SBIR/STTR 2005 Phase 1 xx.xx-xxxx (Title) Form A completed on: Form B completed on: Form C completed on: Technical Proposal Uploaded on: File Name: File Type: File Size: Briefing Chart (Optional) completed on: Proposal endorsed electronically by: This is your official confirmation of receipt. Please save this email for your records, as no other receipt will be provided. The official selection announcement is currently scheduled for November 18, 2005, and will be posted via the SBIR/STTR homepage (http://sbir.nasa.gov). Thank you for your participation in the NASA SBIR/STTR program. NASA SBIR/STTR Program Support Office 6.5 Withdrawal of Proposals Proposals may be withdrawn via the electronic handbook system hosted on the NASA SBIR homepage (http://sbir.nasa.gov) with an endorsement by the designated SBC Official. 6.6 Service of Protests Protests, as defined in Section 33.101 of the FAR, that are filed directly with an agency, and copies of any protests that are filed with the General Accounting Office (GAO) shall be served on the Contracting Officer by obtaining written and dated acknowledgement of receipt from the NASA SBIR/STTR Program Manager at the address listed below: Paul Mexcur, Program Manager NASA SBIR/STTR Program Management Office Code 408, Goddard Space Flight Center Greenbelt, MD 20771-0001 Winfield.P.Mexcur@nasa.gov The copy of any protest shall be received by the NASA SBIR/STTR Program Manager within one day of filing a protest with the GAO. 7. Scientific and Technical Information Sources 7.1 NASA SBIR/STTR Homepage Detailed information on NASA's SBIR/STTR Programs is available at: http://sbir.nasa.gov. 7.2 NASA Commercial Technology Network The NASA Commercial Technology Network (NCTN) contains a significant amount of on line information about the NASA Commercial Technology Program. The address for the NCTN homepage is: http://nctn.hq.nasa.gov/ 7.3 NASA Technology Utilization Services The National Technology Transfer Center (NTTC), sponsored by NASA in cooperation with other Federal agencies, serves as a national resource for technology transfer and commercialization. NTTC has a primary role to get Government research into the hands of U.S. businesses. Its gateway services make it easy to access databases and to contact experts in your area of research and development. For further information, call 800-678-6882. NASA's network of Regional Technology Transfer Centers (RTTCs) provides business planning and development services. However, NASA does not accept responsibility for any services these centers may offer in the preparation of proposals. RTTCs can be contacted directly as listed below to determine what services are available and to discuss fees charged. Alternatively, to contact any RTTC, call 800-472-6785. Northeast: Center for Technology Commercialization Massachusetts Technology Park 1400 Computer Drive Westboro, MA 01581-5043 Phone: 508-870-0042 URL: http://www.ctc.org Mid-Atlantic: TECC – The Technology Commercialization Center 144 Research Drive Hampton, VA 23666 Phone: 757-766-9200 URL: http://www.teccenter.orgSoutheast: Georgia Institute of Technology 151 6th Street 216 O’Keefe Building Atlanta, GA 30332-0640 Phone: 404-894-6786 URL: http://www.edi.gatech.edu/nasa/ Mid-West: Great Lakes Industrial Technology Center 25000 Great Northern Corporate Center Suite 260 Cleveland, OH 44135 Phone: 216-898-6400 URL: http://www.glitec.orgMid-Continent: Mid-Continent Technology Transfer Center Texas Engineering Extension Service 301 Tarrow Street College Station, TX 77840-7896 Phone: 979-845-8762 URL: http://www.mcttc.com/ Far-West: Far-West Technology Transfer Center University of Southern California 3716 South Hope Street, Suite 200 Los Angeles, CA 90007-4344 Phone: 800-642-2872 URL: http://www.usc.edu/dept/engineering/TTC/NASA 7.4 United States Small Business Administration The Policy Directives for the SBIR/STTR Programs, which also state the SBA policy for this Solicitation, may be obtained from the following source. SBA information can also be obtained at: http://www.sba.gov/. Office of Innovation, Research and Technology U.S. Small Business Administration 409 Third Street, S.W. Washington, DC 20416 Phone: 202-205-7701 7.5 National Technical Information Service The National Technical Information Service, an agency of the Department of Commerce, is the Federal Government's central clearinghouse for publicly funded scientific and technical information. For information about their various services and fees, call or write: National Technical Information Service 5285 Port Royal Road Springfield, VA 22161 Phone: 703-605-6040 URL: http://www.ntis.gov 8. Submission Forms and Certifications Form A – SBIR Cover Sheet 34 Guidelines for Completing SBIR Cover Sheet 35 Form B – SBIR Proposal Summary 36 Guidelines for Completing SBIR Proposal Summary 37 Form C – SBIR Budget Summary 38 Guidelines for Preparing SBIR Budget Summary 39 SBIR Check List 41 Form A – STTR Cover Sheet 42 Guidelines for Completing STTR Cover Sheet 43 Form B – STTR Proposal Summary 45 Guidelines for Completing STTR Proposal Summary 46 Form C – STTR Budget Summary 47 Guidelines for Preparing STTR Budget Summary 48 Model Cooperative R/R&D Agreement 50 Model Allocation of Rights Agreement 51 STTR Check List 55 Example Format for Briefing Chart 56 NASA SBIR/STTR Technology Taxonomy 57 Form A – SBIR Cover Sheet Subtopic Number 1. PROPOSAL NUMBER: 05 - . 2. SUBTOPIC TITLE: 3. PROPOSAL TITLE: 4. SMALL BUSINESS CONCERN (SBC): NAME: MAILING ADDRESS: CITY/STATE/ZIP: PHONE: FAX: EIN/TAX ID: DUNS + 4: CAGE CODE: NUMBER OF EMPLOYEES: 5. AMOUNT REQUESTED $ DURATION: MONTHS 6. CERTIFICATIONS: OFFEROR CERTIFIES THAT: As defined in Section 1 of the Solicitation, the offeror certifies: a. The Principal Investigator is “primarily employed” by the Yes No organization as defined in the SBIR Solicitation As defined in Section 2 of the Solicitation, the offeror qualifies as a: b. SBC Yes No Number of employees: _____ c. Socially and economically disadvantaged SBC Yes No d. Women-owned SBC Yes No e. HUBZone-owned SBC Yes No As defined in Section 3.2.4 Part 11 of the Solicitation indicate if f. Work under this project has been submitted for Federal funding only to the NASA Yes No SBIR Program g. Funding has been received for work under this project by any other Federal Yes No grant, contract, or subcontract As described in Section 3 of this solicitation, the offeror meets the following requirements completely: h. All 11 parts of the technical proposal are included in part order Yes No i. Subcontracts/consultants proposed? Yes No i) If yes, limits on subcontracts/consultants met Yes No j. Government equipment or facilities required (cannot use SBIR funds)? Yes No i) If yes, signed statement enclosed in Part 8 Yes No ii) If yes, non-SBIR funding source identified in Part 8? Yes No In accordance with Section 5.13.16 of the Solicitation as applicable k. The offeror will comply with export control regulations Yes No 7. ACN NAME: E-MAIL: 8. I understand that providing false information is a criminal offense under Title 18 US Code, Section 1001, False Statements, as well as Title 18 US Code, Section 287, False Claims. 9. ENDORSEMENT BY SBC OFFICIAL: NAME: TITLE: PHONE: E-MAIL: SIGNATURE: DATE: NOTICE: This data shall not be disclosed outside the Government and shall not be duplicated, used, or disclosed in whole or in part for any purpose other than evaluation of this proposal, provided that a funding agreement is awarded to the offeror as a result of or in connection with the submission of this data, the Government shall have the right to duplicate, use or disclose the data to the extent provided in the funding agreement and pursuant to applicable law. This restriction does not limit the Government's right to use information contained in the data if it is obtained from another source without restriction. The data subject to this restriction are contained in pages __________ of this proposal. Guidelines for Completing SBIR Cover Sheet Complete Cover Sheet Form A electronically. 1. Proposal Number: This number does not change. The proposal number consists of the four-digit subtopic number and four-digit system-generated number. 2. Subtopic Title: Enter the title of the subtopic that this proposal will address. Use abbreviations as needed. 3. Proposal Title: Enter a brief, descriptive title using no more than 80 keystrokes (characters and spaces). Do not use the subtopic title. Avoid words like "development" and "study." 4. Small Business Concern: Enter the full name of the company submitting the proposal. If a joint venture, list the company chosen to negotiate and receive contracts. If the name exceeds 40 keystrokes, please abbreviate. Address: Address where mail is received City, State, Zip: City, 2-letter State designation (i.e. TX for Texas), 9-digit Zip code (i.e. 20705-3106) Phone, Fax: Number including area code EIN/Tax ID: Employer Identification Number/Taxpayer ID DUNS + 4: 9-digit Data Universal Number System plus a 4-digit suffix given by parent concern CAGE Code: Commercial Government and Entity Code (Issued by Central Contractor Registration (CCR)) 5. Amount Requested: Proposal amount from Budget Summary. The amount requested should not exceed $70,000 (see Sections 1.4.1, 5.1.1). Duration: Proposed duration in months. The requested duration should not exceed 6 months (see Sections 1.4.1, 5.1.1). 6. Certifications: Answer Yes or No as applicable for 6a, 6b, 6c, 6d, 6e, 6f, 6h (see the referenced sections for definitions). 6g. SBCs should choose “No” to confirm that work under this project has not been funded under any other Federal grant, contract or subcontract. 6i. Subcontracts/consultants proposed? By answering yes, the SBC certifies that subcontracts/consultants have been proposed and arrangements have been made to perform on the contract, if awarded. i) If yes, limits on subcontracting and consultants met: By answering yes, the SBC certifies that business arrangements with other entities or individuals do not exceed one-third of the work (amount requested including cost sharing if any, less fee, if any) and is in compliance with Section 3.2.4, Part 9. 6j. Government furnished equipment required? By answering yes, the SBC certifies that unique, one-of-a-kind Government Furnished Facilities or Government Furnished Equipment are required to perform the proposed activities (see Sections 3.2.4 Part 8, 3.3.4 Part 8, 5.17). By answering no, the SBC certifies that no such Government Furnished Facilities or Government Furnished Equipment is required to perform the proposed activities. i) If yes, signed statement enclosed in Part 8: By answering yes, the SBC certifies that a statement describing the uniqueness of the facility and its availability to the offeror at specified times, signed by the appropriate Government official, is enclosed in the proposal. ii) If yes, non-SBIR funding source identified in Part 8: By answering yes, the SBC certifies that it has a confirmed, non-SBIR funding source for whatever charges may be incurred when utilizing the required Government facility. 6k. Offerors are responsible for ensuring compliance with export control and International Traffic in Arms (ITAR) regulations. All employees who will work on this contract must be eligible under these regulations or the offeror must have in place a valid export license or technical assistance agreement. Violations of these regulations can result in criminal or civil penalties. 7. ACN Name and E-mail: Name and e-mail address of Authorized Contract Negotiator. 8. Endorsement of this form certifies understanding of this statement. 9. Endorsement: An official of the firm must electronically endorse the proposal cover. Form B – SBIR Proposal Summary Subtopic Number 1. Proposal Number 05 - . . 2. Subtopic Title 3. Proposal Title 4. Small Business Concern Name: Address: City/State: Zip: Phone: 5. Principal Investigator/Project Manager Name: Address: City/State: Zip: Phone: E-mail: 6. Technical Abstract (Limit 2,000 characters, approximately 200 words)/Technology Taxonomy (Select only the technologies relevant to this specific proposal) 7. Potential NASA Application(s): (Limit 1,500 characters, approximately 150 words) 8. Potential Non-NASA Commercial Application(s): (Limit 1,500 characters, approximately 150 words) Guidelines for Completing SBIR Proposal Summary Complete Proposal Summary Form B electronically. 1. Proposal Number: Same as Cover Sheet. 2. Subtopic Title: Same as Cover Sheet. 3. Proposal Title: Same as Cover Sheet. 4. Small Business Concern: Same as Cover Sheet. 5. Principal Investigator/Project Manager: Enter the full name of the PI/MS and include all required contact information. 6. Technical Abstract: Summary of the offeror’s proposed project in 200 words or less. The abstract must not contain proprietary information and must describe the NASA need addressed by the proposed R/R&D effort. Technology Taxonomy: Selections for the Technology Taxonomy are limited to technologies supported or relevant to the specific proposal. 7. Potential NASA Application(s): Summary of the direct or indirect NASA applications of the project, assuming the goals of the proposed R/R&D are achieved. Limit your response to 100 words or 1,500 characters, whichever is less. 8. Potential Non-NASA Commercial Application(s): Summary of the direct or indirect NASA applications of the project, assuming the goals of the proposed R/R&D are achieved. Limit your response to 100 words or 1,500 characters, whichever is less. Form C – SBIR Budget Summary PROPOSAL NUMBER: SMALL BUSINESS CONCERN: DIRECT LABOR: Category Hours Rate Cost $ TOTAL DIRECT LABOR: (1) $ OVERHEAD COST ______% of Total Direct Labor or $ ______ OVERHEAD COST: (2) $ OTHER DIRECT COSTS (ODCs): Category Cost $ TOTAL OTHER DIRECT COSTS: (3) $ Explanation of ODCs ______________________________________ ______________________________________ ______________________________________ (1)+(2)+(3)=(4) SUBTOTAL: (4) $ GENERAL & ADMINISTRATIVE (G&A) COSTS ______% of Subtotal or $ ______ G&A COSTS: (5) $ (4)+(5)=(6) TOTAL COSTS (6) $ ADD PROFIT or SUBTRACT COST SHARING PROFIT/COST SHARING: (As applicable) (7) $ (6)+(7)=(8) AMOUNT REQUESTED: (8) $ PHASE 1 DELIVERABLES: Upon selection, SBCs will be required to submit mandatory deliverables such as progress reports, final report and New Technology report as per their contract. Samples of all required contract deliverables are available in the NASA SBIR/STTR Firms Library via the NASA SBIR homepage (http://sbir.nasa.gov). If your firm is proposing any additional deliverables, list them below: Deliverable Quantity Project Delivery Milestone AUDIT AGENCY: If a Federal agency has ever audited your accounting system, please identify the agency, office location, and contact information below: Agency: _________________________ Office/Location: _________________________ Phone: _________________________ Email: ________________________________ Guidelines for Preparing SBIR Budget Summary Complete Budget Summary Form C electronically. The offeror electronically submits to the Government a pricing proposal of estimated costs with detailed information for each cost element, consistent with the offeror's cost accounting system. This summary does not eliminate the need to fully document and justify the amounts requested in each category. Such documentation should be contained, as appropriate, in the text boxes provided on the electronic form. Firm: Same as Cover Sheet. Proposal Number: Same as Cover Sheet. Direct Labor: Enter labor categories proposed (e.g., Principal Investigator/Project Manager, Research Assistant/Laboratory Assistant, Analyst, Administrative Staff), labor rates and the hours for each labor category. Overhead Cost: Specify current rate and base. Use current rate(s) negotiated with the cognizant Federal auditing agency, if available. If no rate(s) has (have) been negotiated, a reasonable indirect cost (overhead) rate(s) may be requested for Phase 1 for acceptance by NASA. Show how this rate is determined. The offeror may use whatever number and types of overhead rates are in accordance with the firm's accounting system and approved by the cognizant Federal negotiating agency, if available. Multiply Direct Labor Cost by the Overhead Rate to determine the Overhead Cost. Example: A typical SBC might have an overhead rate of 30 percent. If the total direct labor costs proposed are $50,000, the computed overhead costs for this case would be .3x50,000=$15,000, if the base used is the total direct labor costs. or provide a number for total estimated overhead costs to execute the project. Note: If no labor overhead rate is proposed and the proposed direct labor includes all fringe benefits, you may enter “0” for the overhead cost line. Other Direct Costs (ODCs): - Materials and Supplies: Indicate types required and estimate costs. - Documentation Costs or Page Charges: Estimate cost of preparing and publishing project results. - Subcontracts: Include a completed budget including hours and rates and justify details. (Section 3.2.4, Part 9.) - Consultant Services: Indicate name, daily compensation, and estimated days of service. - Computer Services: Computer equipment leasing is included here. List all other direct costs that are not otherwise included in the categories described above. Explanations of all items identified as ODCs must be provided under “Explanation of ODCs.” Offeror should include the basis used for estimating costs (vendor quote, catalog price, etc.) For example, if “Materials” is listed as an ODC, include a description of the materials, the quantity required and basis for the proposed cost. Note: NASA will not fund the purchase of capital equipment or supplies that are not to be delivered to the government or consumed in the production of a prototype. The cost of capital equipment should be depreciated and included in G&A if appropriate. Subtotal (4): Sum of (1) Total Direct Labor, (2) Overhead and (3) ODCs General and Administrative (G&A) Costs (5): Specify current rate and base. Use current rate negotiated with the cognizant Federal negotiating agency, if available. If no rate has been negotiated, a reasonable indirect cost (G&A) rate may be requested for acceptance by NASA. Show how this rate is determined. If a current negotiated rate is not available, NASA will negotiate a reasonable rate with the offeror. Multiply (4) subtotal (Total Direct Cost) by the G&A rate to determine G&A Cost. or provide an estimated G&A costs number for the proposal. Total Costs (6): Sum of Items (4) and (5). Note that this value will be used in verifying the minimum required work percentage for the SBC. Profit/Cost Sharing (7): See Sections 5.9 and 5.10. Profit to be added to total budget, shared costs to be subtracted from total budget, as applicable. Amount Requested (8): Sum of Items (6) and (7), not to exceed $70,000. Deliverables and Audit Information (9): Deliverables: List any additional deliverables, if applicable. Include the deliverable name, quantity (include unit of measurement, i.e., 2 models or 1.5 lbs. of material), and the proposed delivery milestone (i.e., end of contract). This section should only be completed if the offeror is proposing a deliverable in addition to the mandatory deliverables (progress report, final report and New Technology Report). Audit Agency: Complete the “Contact Information” section if your firm’s accounting system has been audited by a Federal agency. Provide the agency name, the office branch or location, and the phone number and/or email. SBIR Check List For assistance in completing your proposal, use the following checklist to ensure your submission is complete. 1. The entire proposal including any supplemental material shall not exceed a total of 25 8.5 x 11 inch pages (Section 3.2.1). 2. The proposal and innovation is submitted for one subtopic only. (Section 3.1). 3. The entire proposal is submitted consistent with the requirements and in the order outlined in Section 3.2 4. The technical proposal contains all eleven parts in order. (Section 3.2.4). 5. Certifications in Form A are completed. 6. Proposed funding does not exceed $70,000. (Sections 1.4.1, 5.1.1). 7. Proposed project duration should not exceed 6 months. (Sections 1.4.1, 5.1.1). 8. Entire proposal including Forms A, B, and C submitted via the Internet. 9. Form A electronically endorsed by the SBC Official. 10. Proposals must be received no later than 5:00 p.m. EDT on Wednesday, September 7, 2005 (Section 6.3). Form A – STTR Cover Sheet 1. PROPOSAL NUMBER: 05 - . 2. RESEARCH TOPIC: 3. PROPOSAL TITLE: 4. SMALL BUSINESS CONCERN (SBC) RESEARCH INSTITUTION (RI) NAME: NAME: ADDRESS: ADDRESS: CITY/STATE/ZIP: CITY/STATE/ZIP : PHONE: FAX: PHONE: FAX: EIN/TAX ID: EIN/TAX ID: DUNS + 4: CAGE CODE: 5. AMOUNT REQUESTED: $_____________________ DURATION: _________ MONTHS 6. CERTIFICATIONS: THE ABOVE SBC CERTIFIES THAT: As defined in Section 2 of the Solicitation, the offeror qualifies as a: a. SBC Yes No Number of employees: ____ b. Socially and economically disadvantaged SBC Yes No c. Woman-owned SBC Yes No d. HUBZone-owned SBC Yes No As described in Section 2.10 of the Solicitation, the partnering institution qualifies as a: e. FFRDC Yes No f. Nonprofit research institute Yes No g. Nonprofit college or university Yes No As described in Section 3 of the Solicitation, the offeror meets the following requirements completely: h. Cooperative Agreement signed by the SBC and RI enclosed Yes No i. All eleven parts of the technical proposal included in part order Yes No j. Subcontracts/consultants proposed? (Other than the RI) Yes No i) If yes, limits on subcontracts/consultants met Yes No k. Government equipment or facilities required (cannot use STTR funds)? Yes No i) If yes, signed statement enclosed in Part 8 Yes No ii) If yes, non-STTR funding source identified in Part 8? Yes No l. A signed Allocation of Rights Agreement will be available for the Contracting Officer at time of selection Yes No As defined in Section 3.2.4 of the Solicitation, indicate if: m. Work under this project has been submitted for funding only to the NASA STTR Yes No Program n. Funding has been received for work under this project by any other Federal Yes No grant, contract, or subcontract In accordance with Section 5.13.16 of the Solicitation as applicable o. The offeror will comply with export control regulations Yes No 7. ACN NAME: E-MAIL: 8. The SBC will perform ___% of the work and the RI will perform ___% of the work of this project. 9. I understand that providing false information is a criminal offense under Title 18 US Code, Section 1001, False Statements, as well as Title 18 US Code, Section 287, False Claims. 10. ENDORSEMENT BY SBC OFFICIAL: NAME: TITLE: PHONE: E_MAIL: SIGNATURE: DATE: NOTICE: This data shall not be disclosed outside the Government and shall not be duplicated, used, or disclosed in whole or in part for any purpose other than evaluation of this proposal, provided that a funding agreement is awarded to the offeror as a result of or in connection with the submission of this data, the Government shall have the right to duplicate, use or disclose the data to the extent provided in the funding agreement and pursuant to applicable law. This restriction does not limit the Government's right to use information contained in the data if it is obtained from another source without restriction. The data subject to this restriction are contained in pages _____ of this proposal. Guidelines for Completing STTR Cover Sheet Complete Cover Sheet Form electronically. 1. Proposal Number: This number does not change. The proposal number consists of the program year (i.e. 04) and unique four-digit system-generated number. 2. Research Topic: NASA research topic number and title (Section 9). 3. Proposal Title: A brief, descriptive title, avoid words like "development of" and "study of," and do not use acronyms or trade names. 4. Small Business Concern: Full name and address of the company submitting the proposal. If a joint venture, list the company chosen to negotiate and receive contracts. If the name exceeds 40 keystrokes, please abbreviate. Research Institution: Full name and address of the research institute. Mailing Address: Address where mail is received City, State, Zip: City, 2-letter State designation (i.e. TX for Texas), 9-digit Zip code (i.e. 20705-3106) Phone, Fax: Number including area code EIN/TAX ID: Employer Identification Number/Taxpayer ID DUNS + 4: 9-digit Data Universal Number System plus a 4-digit suffix given by parent concern CAGE Code: Commercial Government and Entity Code (Issued by Central Contractor Registration (CCR) 5. Amount Requested: Proposal amount from Budget Summary. The amount requested should not exceed $100,000 (see Sections 1.4.1, 5.1.1). Duration: Proposed duration in months. The requested duration should not exceed 12 months (see Sections 1.4.1, 5.1.1). 6. Certifications: Answer Yes or No as applicable for 6a, 6b, 6c, 6d, 6e, 6f, 6g, 6i, 6l (see Section 2 for definitions). 6h. Cooperative Agreement signed by the SBC and RI: By answering yes, the SBC/RI certifies that a Cooperative Agreement signed by both SBC and RI is enclosed in the proposal (see Sections 3.2.2, 3.2.5). 6j. Subcontracts/consultants proposed? By answering yes, the SBC/RI certifies that subcontracts/consultants have been proposed and arrangements have been made to perform on the contract, if awarded. i) If yes, limits on subcontracting and consultants met: By answering yes, the SBC/RI certifies that business arrangements with other entities or individuals do not exceed 30 percent of the work (amount requested including cost sharing if any, less fee, if any) and is in compliance with Section 3.2.4, Part 9. 6k. Government furnished equipment required? By answering yes, the SBC/RI certifies that unique, one-of-a-kind Government Furnished Facilities or Government Furnished Equipment are required to perform the proposed activities (see Sections 3.2.4 Part 8, 3.3.4 Part 8, 5.15). By answering no, the SBC/RI certifies that no such Government Furnished Facilities or Government Furnished Equipment are required to perform the proposed activities. i) If yes, signed statement enclosed in Part 8: By answering yes, the SBC/RI certifies that a statement describing the uniqueness of the facility and its availability to the offeror at specified times, signed by the appropriate Government official, is enclosed in the proposal. ii) If yes, non-SBIR funding source identified in Part 8. By answering yes, the SBC certifies that it has confirmed, non-SBIR funding source for whatever charges may be incurred when utilizing the required Government facility. 6n. SBCs should choose “No” to confirm that work under this project has not been funded under any other Federal grant, contract or subcontract. 6o. Offerors are responsible for ensuring compliance with export control and International Traffic in Arms (ITAR) regulations. All employees who will work on this contract must be eligible under these regulations or the offeror must have in place a valid export license or technical assistance agreement. Violations of these regulations can result in criminal or civil penalties. 7. ACN Name and E-mail: Name and e-mail address of Authorized Contract Negotiator. 8. Proposals submitted in response to this Solicitation must be jointly developed by the SBC and the RI, and at least 40 percent of the work (amount requested including cost sharing, less fee, if any) is to be performed by the SBC as the prime contractor, and at least 30 percent of the work is to be performed by the RI (see Section 3.2.4). 9. Endorsement of this form certifies understanding of this statement. 10. Endorsements: An official of the firm must electronically endorse the proposal cover. Form B – STTR Proposal Summary 1. Proposal Number 05 - . . 2. Research Topic: 3. Proposal Title: 4. Small Business Concern 5. Research Institution Name: Name: Address: Address: City/State: City/State: Zip: Zip: Phone: Phone: 6. Principal Investigator/Project Manager: 7. Technical Abstract (Limit 2,000 characters, approximately 200 words)/Technology Taxonomy (Select only the technologies relevant to this specific proposal) 8. Potential NASA Application(s): (Limit 1,500 characters, approximately 150 words) 9. Potential Non-NASA Commercial Application(s): (Limit 1,500 characters, approximately 150 words) Guidelines for Completing STTR Proposal Summary Complete Form B electronically. 1. Proposal Number: Same as Cover Sheet 2. Research Topic: Same as Cover Sheet. 3. Proposal Title: Same as Cover Sheet. 4. Small Business Concern: Same as Cover Sheet. 5. Research Institution: Same as Cover Sheet. 6. Principal Investigator/Project Manager: Enter the full name of the PI/PM and include all required contact information. 7. Technical Abstract: Summary of the offeror’s proposed project in 200 words or less. The abstract must not contain proprietary information and must describe the NASA need addressed by the proposed R/R&D effort. Technology Taxonomy: Selections for the Technology Taxonomy are limited to technologies supported or relevant to the specific proposal. 8. Potential NASA Application(s): Summary of the direct or indirect NASA applications of the project, assuming the goals of the proposed R/R&D are achieved. Limit your response to 100 words or 1,500 characters, whichever is less. 9. Potential Non-NASA Commercial Application(s): Summary of the direct or indirect NASA applications of the project, assuming the goals of the proposed R/R&D are achieved. Limit your response to 100 words or 1,500 characters, whichever is less. Form C – STTR Budget Summary PROPOSAL NUMBER: SMALL BUSINESS CONCERN: DIRECT LABOR: Category Hours Rate Cost $ TOTAL DIRECT LABOR: (1) $ OVERHEAD COST ______% OF TOTAL DIRECT LABOR OR $ ______ OVERHEAD COST: (2) $ OTHER DIRECT COSTS (ODCs) including RI budget: Category Cost $ TOTAL OTHER DIRECT COSTS: (3) $ Explanation of ODCs ______________________________________ ______________________________________ ______________________________________ (1)+(2)+(3)=(4) SUBTOTAL: (4) $ GENERAL & ADMINISTRATIVE (G&A) COSTS ______% of Subtotal or $ ______ G&A COSTS: (5) $ (4)+(5)=(6) TOTAL COSTS (6) $ ADD PROFIT or SUBTRACT COST SHARING PROFIT/COST SHARING: (As applicable) (7) $ (6)+(7)=(8) AMOUNT REQUESTED: (8) $ PHASE 1 DELIVERABLES: Upon selection, SBCs will be required to submit mandatory deliverables such as progress reports, final report and New Technology Report as per their contract. Samples of all required contract deliverables are available in the NASA SBIR/STTR Firms Library via the NASA SBIR homepage (http://sbir.nasa.gov). If your firm is proposing any additional deliverables, list them below: Deliverable Quantity Project Delivery Milestone AUDIT AGENCY: If a Federal agency has ever audited your accounting system, please identify the agency, office location, and contact information below: Agency: _________________________ Office/Location: _________________________ Phone: ______________________ Email: ____________________________ Guidelines for Preparing STTR Budget Summary Complete Summary Budget Form C electronically. The offeror electronically submits to the Government a pricing proposal of estimated costs with detailed information for each cost element, consistent with the offeror's cost accounting system. This summary does not eliminate the need to fully document and justify the amounts requested in each category. Such documentation should be contained, as appropriate, in the text boxes provided on the electronic form. Small Business Concern - Same as Cover Sheet. Principal Investigator/Project Manager - Same as Cover Sheet. Direct Labor - Enter labor categories proposed (e.g., Principal Investigator/Project Manager, Research Assistant/Laboratory Assistant, Analyst, Administrative Staff), labor rates and the hours for each labor category. Overhead Cost - Specify current rate and base. Use current rate(s) negotiated with the cognizant Federal auditing agency, if available. If no rate(s) has (have) been audited, a reasonable indirect cost (overhead) rate(s) may be requested for Phase 1 for acceptance by NASA. Show how this rate is determined. The offeror may use whatever number and types of overhead rates are in accordance with the firm's accounting system and approved by the cognizant Federal negotiating agency, if available. Multiply Direct Labor Cost by the Overhead Rate to determine the Overhead Cost. Example: A typical SBC might have an overhead rate of 30%. If the total direct labor costs proposed are $50,000, the computed overhead costs for this case would be .3x50,000=$15,000, if the base used is the total direct labor costs. or provide a number for total estimated overhead costs to execute the project. Note: If no labor overhead rate is proposed and the proposed direct labor includes all fringe benefits, you may enter “0” for the overhead cost line. Other Direct Costs (ODCs) - Include total cost for the Research Institution. Note that the proposal should include sufficient information from the Research Institution to determine how their budget was calculated. - Materials and Supplies: Indicate types required and estimate costs. - Documentation Costs or Page Charges: Estimate cost of preparing and publishing project results. - Subcontracts: Include a completed budget including hours and rates and justify details. (Section 3.2.4, Part 9.) - Consultant Services: Indicate name, daily compensation, and estimated days of service. - Computer Services: Computer equipment leasing is included here. List all other direct costs that are not otherwise included in the categories described above. Explanations of all items identified as ODCs must be provided under “Explanation of ODCs.” Offeror should include the basis used for estimating costs (vendor quote, catalog price, etc.) For example, if “Materials” is listed as an ODC, include a description of the materials, the quantity required and basis for the proposed cost. Note: NASA will not fund the purchase of capital equipment or supplies that are not to be delivered to the government or consumed in the production of a prototype. The cost of capital equipment should be depreciated and included in G&A if appropriate. Subtotal (4) - Sum of (1) Total Direct Labor, (2) Overhead and (3) ODCs General and Administrative (G&A) Costs (5)- Specify current rate and base. Use current rate negotiated with the cognizant Federal negotiating agency, if available. If no rate has been negotiated, a reasonable indirect cost (G&A) rate may be requested for acceptance by NASA. If a current negotiated rate is not available, NASA will negotiate a reasonable rate with the offeror. Multiply (4) subtotal (Total Direct Cost) by the G&A rate to determine G&A Cost. or provide an estimated G&A costs number for the proposal. Total Costs (6) - Sum of Items (4) and (5). Note that this value will be used in verifying the minimum required work percentage for the SBC and RI. Profit/Cost Sharing (7) - See Sections 5.9 and 5.10. Profit to be added to total budget, shared costs to be subtracted from total budget, as applicable. Amount Requested (8) - Sum of Items (6) and (7), not to exceed $100,000. Deliverables and Audit Information (9): Deliverables: List any additional deliverables, if applicable. Include the deliverable name, quantity (include unit of measurement, i.e., 2 models or 1.5 lbs. of material), and the proposed delivery milestone (i.e., end of contract). This section should only be completed if the offeror is proposing a deliverable in addition to the mandatory deliverables (progress report, final report and New Technology Report). Audit Agency: Complete the “Contact Information” section if your firm’s accounting system has been audited by a Federal agency. Provide the agency name, the office branch or location, and the phone number and/or email. Model Cooperative R/R&D Agreement By virtue of the signatures of our authorized representatives, (Small Business Concern), and (Research Institution) have agreed to cooperate on the (Proposal Title) Project, in accordance with the proposal being submitted with this agreement. This agreement shall be binding until the completion of all Phase 1 activities, at a minimum. If the (Proposal Title) Project is selected to continue into Phase 2, the agreement may also be binding in Phase 2 activities that are funded by NASA, then this agreement shall be binding until those activities are completed. The agreement may also be binding in Phase 3 activities that are funded by NASA. After notification of Phase 1 selection and prior to contract release, we shall prepare and submit, if requested by NASA, an Allocation of Rights Agreement, which shall state our rights to the intellectual property and technology to be developed and commercialized by the (Proposal Title) Project. We understand that our contract cannot be approved and project activities may not commence until the Allocation of Rights Agreement has been signed and certified to NASA. Please direct all questions and comments to (Small Business Concern representative) at (Phone Number) Signature Name/title Small Business Concern Signature Name/title Research Institution Small Business Technology Transfer (STTR) Program Model Allocation of Rights Agreement This Agreement between _________________________________________, a small business concern organized as a _________________________ under the laws of _________________ and having a principal place of business at ___________________________________________________________________________________________ ____________________, ("SBC") and __________________________________________________, a research institution having a principal place of business at __________________________ _________________,("RI") is entered into for the purpose of allocating between the parties certain rights relating to an STTR project to be carried out by SBC and RI (hereinafter referred to as the "PARTIES") under an STTR funding agreement that may be awarded by _NASA________ to SBC to fund a proposal entitled "___________________________________ _____________________________________________________________________________" submitted, or to be submitted, to by SBC on or about __________________________, 200___. 1. Applicability of this Agreement. (a) This Agreement shall be applicable only to matters relating to the STTR project referred to in the preamble above. (b) If a funding agreement for STTR project is awarded to SBC based upon the STTR proposal referred to in the preamble above, SBC will promptly provide a copy of such funding agreement to RI, and SBC will make a sub-award to RI in accordance with the funding agreement, the proposal, and this Agreement. If the terms of such funding agreement appear to be inconsistent with the provisions of this Agreement, the Parties will attempt in good faith to resolve any such inconsistencies. However, if such resolution is not achieved within a reasonable period, SBC shall not be obligated to award nor RI to accept the sub-award. If a sub-award is made by SBC and accepted by RI, this Agreement shall not be applicable to contradict the terms of such sub-award or of the funding agreement awarded by NASA to SBC except on the grounds of fraud, misrepresentation, or mistake, but shall be considered to resolve ambiguities in the terms of the sub-award. (c) The provisions of this Agreement shall apply to any and all consultants, subcontractors, independent contractors, or other individuals employed by SBC or RI for the purposes of this STTR project. 2. Background Intellectual Property. (a) "Background Intellectual Property" means property and the legal right therein of either or both parties developed before or independent of this Agreement including inventions, patent applications, patents, copyrights, trademarks, mask works, trade secrets and any information embodying proprietary data such as technical data and computer software. (b) This Agreement shall not be construed as implying that either party hereto shall have the right to use Background Intellectual Property of the other in connection with this STTR project except as otherwise provided hereunder. (1) The following Background Intellectual Property of SBC may be used nonexclusively and, except as noted, without compensation by RI in connection with research or development activities for this STTR project (if "none" so state):_______________________________________________________________________ _____________________________________________________________________; (2) The following Background Intellectual Property of RI may be used nonexclusively and, except as noted, without compensation by SBC in connection with research or development activities for this STTR project (if "none" so state): ____________________________________________________________________________________________________________________________________________________________; (3) The following Background Intellectual Property of RI may be used by SBC nonexclusively in connection with commercialization of the results of this STTR project, to the extent that such use is reasonably necessary for practical, efficient and competitive commercialization of such results but not for commercialization independent of the commercialization of such results, subject to any rights of the Government therein and upon the condition that SBC pay to RI, in addition to any other royalty including any royalty specified in the following list, a royalty of _____% of net sales or leases made by or under the authority of SBC of any product or service that embodies, or the manufacture or normal use of which entails the use of, all or any part of such Background Intellectual Property (if "none" so state): _________________________________________________________________________________________________________________________________________. 3. Project Intellectual Property. (a) "Project Intellectual Property" means the legal rights relating to inventions (including Subject Inventions as defined in 37 CFR § 401), patent applications, patents, copyrights, trademarks, mask works, trade secrets and any other legally protectable information, including computer software, first made or generated during the performance of this STTR Agreement. (b) Except as otherwise provided herein, ownership of Project Intellectual Property shall vest in the party whose personnel conceived the subject matter, and such party may perfect legal protection in its own name and at its own expense. Jointly made or generated Project Intellectual Property shall be jointly owned by the Parties unless otherwise agreed in writing. The SBC shall have the first option to perfect the rights in jointly made or generated Project Intellectual Property unless otherwise agreed in writing. (1) The rights to any revenues and profits, resulting from any product, process, or other innovation or invention based on the cooperative shall be allocated between the SBC and the RI as follows: SBC Percent: ________ RI Percent: ________ (2) Expenses and other liabilities associated with the development and marketing of any product, process, or other innovation or invention shall be allocated as follows: the SBC will be responsible for ______ percent and the RI will be responsible for ______ percent. (c) The Parties agree to disclose to each other, in writing, each and every Subject Invention, which may be patentable or otherwise protectable under the United States patent laws in Title 35, United States Code. The Parties acknowledge that they will disclose Subject Inventions to each other and the Agency within two months after their respective inventor(s) first disclose the invention in writing to the person(s) responsible for patent matters of the disclosing Party. All written disclosures of such inventions shall contain sufficient detail of the invention, identification of any statutory bars, and shall be marked confidential, in accordance with 35 U.S.C. § 205. (d) Each party hereto may use Project Intellectual Property of the other nonexclusively and without compensation in connection with research or development activities for this STTR project, including inclusion in STTR project reports to the AGENCY and proposals to the AGENCY for continued funding of this STTR project through additional phases. (e) In addition to the Government's rights under the Patent Rights clause of 37 CFR § 401.14, the Parties agree that the Government shall have an irrevocable, royalty free, nonexclusive license for any Governmental purpose in any Project Intellectual Property. (f) SBC will have an option to commercialize the Project Intellectual Property of RI, subject to any rights of the Government therein, as follows? (1) Where Project Intellectual Property of RI is a potentially patentable invention, SBC will have an exclusive option for a license to such invention, for an initial option period of _______ months after such invention has been reported to SBC. SBC may, at its election and subject to the patent expense reimbursement provisions of this section, extend such option for an additional _______ months by giving written notice of such election to RI prior to the expiration of the initial option period. During the period of such option following notice by SBC of election to extend, RI will pursue and maintain any patent protection for the invention requested in writing by SBC and, except with the written consent of SBC or upon the failure of SBC to reimburse patenting expenses as required under this section, will not voluntarily discontinue the pursuit and maintenance of any United States patent protection for the invention initiated by RI or of any patent protection requested by SBC. For any invention for which SBC gives notice of its election to extend the option, SBC will, within ______ days after invoice, reimburse RI for the expenses incurred by RI prior to expiration or termination of the option period in pursuing and maintaining (i) any United States patent protection initiated by RI and (ii) any patent protection requested by SBC. SBC may terminate such option at will by giving written notice to RI, in which case further accrual of reimbursable patenting expenses hereunder, other than prior commitments not practically revocable, will cease upon RI's receipt of such notice. At any time prior to the expiration or termination of an option, SBC may exercise such option by giving written notice to RI, whereupon the parties will promptly and in good faith enter into negotiations for a license under RI's patent rights in the invention for SBC to make, use and/or sell products and/or services that embody, or the development, manufacture and/or use of which involves employment of, the invention. The terms of such license will include: (i) payment of reasonable royalties to RI on sales of products or services which embody, or the development, manufacture or use of which involves employment of, the invention; (ii) reimbursement by SBC of expenses incurred by RI in seeking and maintaining patent protection for the invention in countries covered by the license (which reimbursement, as well as any such patent expenses incurred directly by SBC with RI's authorization, insofar as deriving from RI's interest in such invention, may be offset in full against up to _______ of accrued royalties in excess of any minimum royalties due RI); and, in the case of an exclusive license, (3) reasonable commercialization milestones and/or minimum royalties. (2) Where Project Intellectual Property of RI is other than a potentially patentable invention, SBC will have an exclusive option for a license, for an option period extending until ______ months following completion of RI's performance of that phase of this STTR project in which such Project Intellectual Property of RI was developed by RI. SBC may exercise such option by giving written notice to RI, whereupon the parties will promptly and in good faith enter into negotiations for a license under RI's interest in the subject matter for SBC to make, use and/or sell products or services which embody, or the development, manufacture and/or use of which involve employment of, such Project Intellectual Property of RI. The terms of such license will include: (i) payment of reasonable royalties to RI on sales of products or services that embody, or the development, manufacture or use of which involves employment of, the Project Intellectual Property of RI and, in the case of an exclusive license, (ii) reasonable commercialization milestones and/or minimum royalties. (3) Where more than one royalty might otherwise be due in respect of any unit of product or service under a license pursuant to this Agreement, the parties shall in good faith negotiate to ameliorate any effect thereof that would threaten the commercial viability of the affected products or services by providing in such license(s) for a reasonable discount or cap on total royalties due in respect of any such unit. 4. Followon Research or Development. All followon work, including any licenses, contracts, subcontracts, sublicenses or arrangements of any type, shall contain appropriate provisions to implement the Project Intellectual Property rights provisions of this agreement and insure that the Parties and the Government obtain and retain such rights granted herein in all future resulting research, development, or commercialization work. 5. Confidentiality/Publication. (a) Background Intellectual Property and Project Intellectual Property of a party, as well as other proprietary or confidential information of a party, disclosed by that party to the other in connection with this STTR project shall be received and held in confidence by the receiving party and, except with the consent of the disclosing party or as permitted under this Agreement, neither used by the receiving party nor disclosed by the receiving party to others, provided that the receiving party has notice that such information is regarded by the disclosing party as proprietary or confidential. However, these confidentiality obligations shall not apply to use or disclosure by the receiving party after such information is or becomes known to the public without breach of this provision or is or becomes known to the receiving party from a source reasonably believed to be independent of the disclosing party or is developed by or for the receiving party independently of its disclosure by the disclosing party. (b) Subject to the terms of paragraph (a) above, either party may publish its results from this STTR project. However, the publishing party will give a right of refusal to the other party with respect to a proposed publication, as well as a _____ day period in which to review proposed publications and submit comments, which will be given full consideration before publication. Furthermore, upon request of the reviewing party, publication will be deferred for up to ______ additional days for preparation and filing of a patent application which the reviewing party has the right to file or to have filed at its request by the publishing party. 6. Liability. (a) Each party disclaims all warranties running to the other or through the other to third parties, whether express or implied, including without limitation warranties of merchantability, fitness for a particular purpose, and freedom from infringement, as to any information, result, design, prototype, product or process deriving directly or indirectly and in whole or part from such party in connection with this STTR project. (b) SBC will indemnify and hold harmless RI with regard to any claims arising in connection with commercialization of the results of this STTR project by or under the authority of SBC. The PARTIES will indemnify and hold harmless the Government with regard to any claims arising in connection with commercialization of the results of this STTR project. 7. Termination. (a) This agreement may be terminated by either Party upon __ days written notice to the other Party. This agreement may also be terminated by either Party in the event of the failure of the other Party to comply with the terms of this agreement. (b) In the event of termination by either Party, each Party shall be responsible for its share of the costs incurred through the effective date of termination, as well as its share of the costs incurred after the effective date of termination, and which are related to the termination. The confidentiality, use, and/or nondisclosure obligations of this agreement shall survive any termination of this agreement. AGREED TO AND ACCEPTED Small Business Concern By:____________________________________ Date:______________ Print Name:__________________________________________________ Title:_______________________________________________________ Research Institution By:____________________________________ Date:______________ Print Name:__________________________________________________ Title:_______________________________________________________ STTR Check List For assistance in completing your proposal, use the following checklist to ensure your submission is complete. 1. The entire proposal including any supplemental material shall not exceed a total of 25 8.5 x 11 inch pages, including Cooperative Agreement. (Sections 3.2.1, 3.2.5). 2. The proposal and innovation is submitted for one topic only. (Section 3.1). 3. The entire proposal is submitted consistent with the requirements and in the order outlined in Section 3.2 4. The technical proposal contains all eleven parts in order. (Section 3.2.4). 5. Certifications in Form A are completed. 6. Proposed funding does not exceed $100,000. (Sections 1.4.1, 5.1.1). 7. Proposed project duration should not exceed 12 months. (Sections 1.4.1, 5.1.1). 8. Cooperative Agreement has been electronically endorsed by both the SBC Official and RI. (Sections 3.2.5, 6.2). 9. Entire proposal including Forms A, B, C, and Cooperative Agreement submitted via the Internet. 10. Form A electronically endorsed by the SBC Official. 11. Proposals must be received no later than 5:00 p.m. EDT on Wednesday, September 7, 2005 (Section 6.3). 12. Signed Allocation of Rights Agreement available for Contracting Officer at time of selection. Example Format for Briefing Chart NASA SBIR/STTR Technology Taxonomy Avionics and Astrionics Airport Infrastructure and Safety Attitude Determination and Control Guidance, Navigation, and Control On-Board Computing and Data Management Pilot Support Systems Spaceport Infrastructure and Safety Telemetry, Tracking and Control Bio-Technology Air Revitalization and Conditioning Biomass Production and Storage Biomedical and Life Support Biomolecular Sensors Sterilization/Pathogen and Microbial Control Waste Processing and Reclamation Communications Architectures and Networks Autonomous Control and Monitoring Laser RF Cryogenics Fluid Storage and Handling Instrumentation Production Education General Public Outreach K-12 Outreach Mission Training Electronics Highly-Reconfigurable Photonics Radiation-Hard/Resistant Electronics Ultra-High Density/Low Power Extravehicular Activity Manned-Manuvering Units Portable Life Support Suits Tools Information Autonomous Reasoning/Artificial Intelligence Computer System Architectures Data Acquisition and End-to-End-Management Data Input/Output Devices Database Development and Interfacing Expert Systems Human-Computer Interfaces Portable Data Acquisition or Analysis Tools Software Development Environments Software Tools for Distributed Analysis and Simulation Manufacturing Earth-Supplied Resource Utilization In-situ Resource Utilization Microgravity Materials Ceramics Composites Computational Materials Metallics Multifunctional/Smart Materials Optical & Photonic Materials Organics/Bio-Materials Radiation Shielding Materials Semi-Conductors/Solid State Device Materials Superconductors and Magnetic Tribology Microgravity Biophysical Utilization Combustion Liquid-Liquid Interfaces Power and Energy Biochemical Conversion Energy Storage MHD and Related Conversion Nuclear Conversion Photovoltaic Conversion Power Management and Distribution Renewable Energy Thermodynamic Conversion Thermoelectric Conversion Wireless Distribution Propulsion Aerobrake Aircraft Engines Beamed Energy Chemical Electromagnetic Thrusters Electrostatic Thrusters Feed System Components Fundamental Propulsion Physics High Energy Propellents (Recombinant Energy & Metallic Hydrogen) Launch Assist (Electromagnetic, Hot Gas and Pneumatic) MHD Micro Thrusters Monopropellants Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear) Propellant Storage Solar Tethers Robotics Human-Robotic Interfaces Integrated Robotic Concepts and Systems Intelligence Manipulation Mobility Perception/Sensing Teleoperation Sensors and Sources Biochemical Gravitational High-Energy Large Antennas and Telescopes Microwave/Submillimeter Optical Particle and Fields Sensor Webs/Distributed Sensors Substrate Transfer Technology Structures Airframe Airlocks/Environmental Interfaces Controls-Structures Interaction (CSI) Erectable Inflatable Kinematic-Deployable Launch and Flight Vehicle Modular Interconnects Structural Modeling and Tools Tankage Thermal Ablatives Control Instrumentation Cooling Reuseable Thermal Insulating Materials Verification and Validation Operations Concepts and Requirements Simulation Modeling Environment Testing Facilities Testing Requirements and Architectures Training Concepts and Architectures 9. Research Topics for SBIR and STTR 9.1 SBIR Research Topics Introduction The SBIR Program Solicitation topics are developed in coordination with the NASA management structure organized by four Mission Directorates (http://www.nasa.gov). The Mission Directorates (MDs) identify, at the most fundamental level, what NASA does and for whom. Each MD is analogous to a strategic business unit employed by private-sector companies to focus on and respond to their customers' needs. Each MD has a unique set of goals, objectives, and strategies. These are the following: Aeronautics Research Exploration Systems Science Space Operations In August of 2004, the Mission Directorate structure was created, replacing the Enterprise structure. Biological and Physical Research became part of Exploration Systems, and is reflected this year in Topics X11-X14. Earth Science and Space Science were combined under Science. The Space Flight Enterprise, which was reflected in the Exploration Systems Enterprise in last year’s Solicitation, became Space Operations. 9.1.1 AERONAUTICS RESEARCH The Aeronautics Research Mission Directorate (ARMD) provides some of the most advanced aeronautics research in the world. ARMD keeps America the most advanced nation in commercial, scientific, and defense use of aeronautics and greatly increases aviation safety, security, and ability. Additionally, the results of ARMD research are used in other NASA endeavors. http://www.aerospace.nasa.gov/ TOPIC: A1 Aviation Safety and Security 60 A1.01 Crew Systems Technologies for Improved Aviation Safety (LaRC) 60 A1.02 Aviation Safety and Security; Fire, Icing, Propulsion and Secure CNS Aircraft Systems (GRC) 61 A1.03 Aviation Security Technologies (LaRC) 62 A1.04 Automated On-Line Health Management and Data Analysis (ARC) 63 TOPIC: A2 Vehicle Systems 63 A2.01 Noise Breakthrough Turbine-Based Propulsion Technologies (GRC) 64 A2.02 Fuel Cell Technologies for Aircraft Propulsion and Power (GRC) 64 A2.03 Hydrogen Fuel Systems and Components for Aircraft Applications (GRC) 65 A2.04 Aircraft Systems Noise Prediction and Reduction (LaRC) 66 A2.05 Electric Drive Components, Power Management and Distribution Technologies (GRC) 66 A2.06 Smart, Adaptive Aerospace Vehicles With Intelligence (ARC) 67 A2.07 Revolutionary Atmospheric Flight Concepts (DFRC) 68 A2.08 Modeling, Identification, and Simulation for Control of Aerospace Vehicles to Prepare for Flight Test (DFRC) 68 A2.09 Flight Sensors and Airborne Instruments for Flight Research (DFRC) 69 TOPIC: A3 Airspace Systems 70 A3.01 Next Generation Air-Traffic Management Systems (ARC) 70 TOPIC: A1 Aviation Safety and Security The worldwide commercial aviation accident rate has been nearly constant over the past two decades. Although the rate is very low, increasing traffic over the years may result in the absolute number of accidents also increasing. Without improvements, doubling or tripling of air traffic by 2017 could lead to 50 or more major accidents a year. This number of accidents would have an unacceptable impact on the air transportation system. The goal of NASA’s Aviation Safety and Security Program (AvSSP) is to develop and demonstrate technologies that contribute to a reduction in the fatal aviation accident rate. Research and technology will address accidents involving hazardous weather, controlled flight into terrain, human-error-caused accidents and incidents, and mechanical or software malfunctions. The Program will also develop and integrate information technologies needed to build a safer aviation system and provide information for the assessment of situations and trends that indicate unsafe conditions before they lead to accidents. NASA researchers are also looking at ways to adapt aviation technologies already being developed to improve aviation security. The AvSSP is focusing on areas where NASA expertise could make a significant contribution to security: 1) the hardening of aircraft and their systems, 2) secure airspace operation technologies, 3) improved systems to screen passenger and cargo information, and 4) sensors designed to better detect threats. NASA seeks highly innovative proposals that will complement its work in Aviation Safety and Security in the following subtopic areas: A1.01 Crew Systems Technologies for Improved Aviation Safety Lead Center: LaRC NASA seeks highly innovative, crew-centered, technologies to improve aerospace system safety. Such advanced technologies may meet this goal by ensuring appropriate situation awareness; facilitating and extending human perception, information interpretation, and response planning and selection; counteracting human information processing limitations, biases, and error-tendencies; assisting in response planning and execution; and ensuring appropriate access to airspace as constrained by safety and security concerns. We require improved methods and tools for characterizing current and future users of aerospace systems, and tailoring designs to users. Such advanced technologies must be evaluated sensitively and in operationally-valid contexts. Therefore, NASA also seeks tools and methods for measuring and evaluating aerospace system operator performance, and as this performance is reflected by system performance. Technologies may take the form of tools, models, operational procedures, instructional systems, prototypes, and devices for use in the flight deck, elsewhere by pilots, or by those who design systems for crew use. Specific topical areas of interest include the following: * Intelligent systems monitoring and alerting technologies for improved failure mode identification, recovery, and threat mitigation * Designs for human-error prevention, detection, and mitigation * Decision-support tools and methods to improve communication, collaborative, and distributive decision-making * Data fusion technologies to integrate flight-related information for improved situation awareness and appropriate workload modulation * Support for crew response planning and selection * Computational approaches to determine and appropriately modulate crew engagement, workload, and situation awareness * Human-centered information technologies to improve the performance of less-experienced operators, and pilots from special population groups * Avionics designers and/or certification specialist tools to improve the application of human-centered principles * Human-error reliability approaches to analyzing flight deck displays decision aids, and procedures; * Presentation and aiding concepts for the display and use of data with spatial or temporal uncertainty, and of integrated streams of data with various levels of integrity * Individual and team performance metrics, analysis methods, and tools to better evaluate and certify human and system performance for use in operational environments, simulation, and model-based analyses Proposals should describe technologies, tools, and approaches with high potential to serve NASA program objectives, and to be developed as marketable products. A1.02 Aviation Safety and Security; Fire, Icing, Propulsion and Secure CNS Aircraft Systems Lead Center: GRC NASA is concerned with the prevention of hazardous in-flight conditions and the mitigation of their effects when they do occur. Aircraft fires represent a small number of actual accident causes, but the number of fatalities due to in-flight, post-crash, and on-ground fires is large. One particular emphasis is on early, false-alarm resistant detection of the location, spread, and suppression of in-flight fires in hidden, inaccessible areas of the aircraft. Examples of hidden areas are behind cabin panels, inside ductwork, and so on. Another area of interest is in-tank monitoring of fuel /air flammability factors to provide more efficient active control of fuel tank inerting systems. A second emphasis for this subtopic is on propulsion system health management, in order to predict, prevent, or accommodate safety-significant malfunctions and damage. Past advances in this area have helped improve the reliability and safety of aircraft propulsion systems; however, propulsion system component failures are still a contributing factor in numerous aircraft accidents and incidents. Advances in technology are sought which help to further reduce the occurrence of and/or mitigate the effects of safety-significant propulsion system malfunctions and damage. Specifically the following are sought: propulsion health management technologies such as instrumentation, sensors, ground and on-wing nondestructive inspection, health monitoring algorithms, and fault accommodating logic, which will predict/prognose, diagnose, prevent, assess, and allow recovery from propulsion system malfunctions, degradation, or damage. A third emphasis is to increase the level of safety for all aircraft flying in the atmospheric icing environment. To maximize the level of safety, aircraft must be capable of handling all possible icing conditions by either avoiding or tolerating the conditions. Proposals are invited that lead to innovative new approaches or significant improvements in existing technologies for in-flight icing conditions avoidance (icing weather information systems) or tolerance (airframe and engine ice protection systems and design tools). With these emphases in mind, products and technologies that can be made affordable and retrofitable within the current aviation system, as well as for use in the future, are sought: * Ground and airborne radome technologies for microwave wavelength radar and radiometers that remain clear of liquid water and ice in all weather situations. * In situ icing environment measurement systems that can provide practical, very low-cost validation data for emerging icing weather information systems and atmospheric modeling. Measured information must include location, altitude, cloud liquid water content, temperature, and ideally cloud particle sizing and phase information. Solutions envisioned would use radiosonde-based systems. * Ice protection and detection technology submittal must provide significant improvements over current systems or address new design needs. Areas of improvement can be considered to be: efficient thermal protection systems, including composite wing or structures applications, ice sensors that provide detection and accretion rate for all possible icing conditions, wide area ice detection, detection that serves both ground and in-flight applications, ice crystal detection probe (for non-research aircraft applications), engine icing probe (that can measure Liquid Water Content and Total Water Content inside engine passages), and de-icing systems that operate at near anti-icing performance. Any submittal must be cost competitive to current technologies. A fourth emphasis for this subtopic is protection and hardening of the aircraft's communication, navigation, and surveillance (CNS) systems, as well as enabling new aviation security applications through improved air-to-ground data link communications and secure onboard information processing, computing, and air/ground networking. Technology is needed to harden the CNS systems, both onboard and air-to-ground, against abnormalities and deliberate attacks towards also enabling the next-generation airborne, ground- and space-based surveillance systems. Other communications related needs can be found in other NASA SBIR subtopics areas. The final emphasis for this subtopic is on propulsion damage adaptive controls technologies and systems for new aircraft security applications. This technology is needed to enable a propulsion system to mitigate aircraft damage from hostile attacks. A1.03 Aviation Security Technologies Lead Center: LaRC Participating Center(s): ARC, JPL The NASA Strategic Plan includes requirements to enable a more secure air transportation system and to create a more secure world by investing in technologies and collaborating with other agencies, industry, and academia. NASA’s role in civil aeronautics has always been to develop high-risk, high-payoff technologies to meet critical national aviation challenges. NASA aims to develop and advance technologies that will reduce the vulnerability of the Air Transportation System (ATS) to threats or hostile acts, and identify and inform users of potential vulnerabilities in a timely fashion. Specific technical focus areas include system-wide security risk assessment and incident precursor identification; enhanced flight procedures and on-board systems to protect critical infrastructures and key assets and enable the safe recovery of a seized aircraft; definition of directed energy threats to the aircraft and on/off-board systems that will provide surveillance and countermeasures of these threats; integrated adaptive control systems to detect and compensate for vehicle damage; hardened and security enhanced aircraft networks and datalinks; remote monitoring of the aircraft environment and systems; new materials for composite fire and explosive resistant fuselage structures; advanced, airborne, in situ detection of chemical and biological terror agents; and commercial aircraft fuel tank inerting. Technologies under development are intended for the next-generation ATS; however, issues such as retrofit, certification, system implementation, and cost-benefit must be considered during the technology development process. NASA seeks highly innovative and commercially viable technologies that will improve aviation security by addressing threats to air vehicles as well as the ATS. Specific areas of focus include: preventing aircraft from being used as a weapon of mass destruction; protection from man-portable air defense systems (ManPADS) and electromagnetic energy (EME) attacks; light-weight, fire and explosive resistant composite materials; explosive resistant fuel systems; ground-based decision support tools needed to monitor airspace security concerns; reporting systems to monitor security violations; secure encrypted datalink systems, intrusion-tolerant communications networks and communications systems to support emerging aviation security applications; tools to support real-time management of security information; and Chem/Bio sensor development. Technologies may take the form of tools, models, techniques, procedures, substantiated guidelines, prototypes, and devices: * Intelligent Systems monitoring and alerting technologies; * Secure communications systems to support emerging aviation security applications; * Onboard and ground surveillance and interception systems for aircraft immunity to electromagnetic interference and electromagnetic pulse intrusions; * Flight control systems that accommodate vehicle damage relative to changes in aircraft stability, control, and structural load characteristics; * Material systems, fuselage structural concepts, and fuel systems that are resistant to fire and explosions; * Fuel system technologies that prevent or minimize in-flight vulnerability of civil transport aircraft due to small arms or man-portable defense systems type projectiles; * Computational approaches to monitoring crew health, stress level, state of duress, and performance; * Validation methods and tools for advanced safety/security critical systems; * Technologies that enable secure communications, navigation, and surveillance on-board the aircraft; * Technologies and methods to provide accurate information and guidance to enable pilot avoidance of protected airspace, maintain positive identity verification of aircraft operators, determine pilot intent, and deny flight control access to unauthorized persons; * Decision-support tools and methods to improve communication and collaborative and distributive decision-making; and * Data fusion technologies for integrating disparate sources of flight-related information. A1.04 Automated On-Line Health Management and Data Analysis Lead Center: ARC Participating Center(s): DFRC Online health monitoring is a critical technology for improving air transportation safety in the 21st century. Safe, affordable, and more efficient operation of aircraft requires advances in online health monitoring of vehicle subsystems and information monitoring from many sources over local- and wide-area networks. Online health monitoring is a general concept involving signal-processing algorithms designed to support decisions related to safety, maintenance, or operating procedures. The concept of online health monitoring emphasizes algorithms that minimize the time between data acquisition and decision-making. This subtopic seeks solutions for online aircraft subsystem health monitoring and prognostics. Solutions should exploit multiple computers communicating over standard networks where applicable. Solutions can be designed to monitor a specific subsystem or a number of systems simultaneously. Resulting commercial products might be implemented in a distributed decision-making environment such as onboard diagnostics and management systems, or maintenance and inspection networks of potentially global proportion. Proposers should discuss who the users of resulting products would be, e.g., research/test/development, manufacturing; maintenance depots, flight crew, Unmanned Aerial Vehicles/Remotely Operated Aircraft (UAV/ROA) aircraft operators, airports, flight operations or mission control, or airlines. Proposers are encouraged to discuss data acquisition, processing, and presentation components in their proposal. Proposals that focus solely on sensor development should not be submitted to this subtopic. Such proposals should be addressed to sensor development subtopics such as the Flight Sensors and Airborne Instruments for Flight Research subtopic. Examples of desired solutions targeted by this subtopic follow: * Real-time autonomous sensor validity monitors; * Flight control system or flight path diagnostics for predicting loss of control; * Automated testing and diagnostics of mission-critical avionics; * Structural fatigue, life cycle, static, or dynamic load monitors; * Methods and tools for remaining life estimation and prognostics for critical aircraft components; * Automated nondestructive evaluation for faulty structural components; * Electrical system monitoring and fire prevention; * Architectures for online monitoring, including architectures that exploit wireless communication technology to reduce costs; * Model-reference or model-updating schemes based on measured data, which operate autonomously; * Proactive maintenance concepts for aircraft engines, including engine life-cycle monitors; * Predicting or detecting any equipment malfunction; * Middleware or software toolkits to lower the cost of developing online aircraft health monitoring applications; and * Innovative solutions for harvesting, managing, archiving, and retrieving aircraft health data. TOPIC: A2 Vehicle Systems The Vehicle Systems Program (VSP) goal is to provide breakthrough technologies for significantly advanced future air vehicles. The approach is to develop these technologies and demonstrate them in flight to provide evidence of barrier breakthroughs. The benefits of these breakthrough technologies including opening more communities to air transportation, enabling new air transportation models by doubling vehicle speed capacity, eliminating aviation pollution, and enabling new science platforms. VSP will focus on four demonstration projects. The subsonic noise reduction project will start by demonstrating a 50% noise reduction compared to 1997 state of the art. The sonic boom reduction project will begin by demonstrating technology that could enable an acceptable sonic boom level. The high altitude, long endurance project will start by demonstrating a 14-day duration high-altitude aircraft. Finally, the zero emissions aircraft will begin by demonstrating an aircraft powered by hydrogen fuel cells. A2.01 Noise Breakthrough Turbine-Based Propulsion Technologies Lead Center: GRC Future subsonic and supersonic aircraft may be required to achieve reduced noise levels up to 20 effective perceived noise levels (EPNdB) below FAR 36 Stage 3 certification levels without significant impacts to performance. The main emphasis of this subtopic is on high-risk, breakthrough technologies in order to reduce the technical risk associated with the development and deployment of new technologies in future commercial products. Subsonic noise reduction to date has predominantly been achieved via higher-bypass-ratio engines. With current practices, the nacelle diameter limit has physically been reached and engine noise is now comparable to airframe noise on approach. Engine noise reduction concepts proposed for subsonic applications must be compatible with low noise propulsion/airframe integration designs and continuous descent approach, low noise guidance flight procedures. Innovative noise reduction concepts need to be identified that provide economical alternatives to conventional propulsion systems. Integrated, advanced propulsion systems with intelligent controls technologies will enable supersonic vehicles (up to Mach 2) having acceptable takeoff/landing noise and increased efficiency. Studies suggest that gas turbine engines with increased thrust-to-weight, bypass ratios, and decreased thrust specific fuel consumption are required to support quiet supersonic aircraft. NASA is interested in the development of advanced gas turbine engine concepts and key enabling technologies that can dramatically reduce the landing/take-off noise to an acceptable level, and which have the potential to dramatically improve the sustained cruise performance of a supersonic aircraft. Concepts proposed for supersonic applications must not adversely impact the airframe configurations to reduce sonic boom intensity, especially with regard to the formation of shaped waves and the human response to shaped waves. Specific areas of interest include but are not limited to the following: Subsonic Propulsion System Technologies * Innovative source identification techniques for fan, jet, combustor, or turbine noise; * Advanced turbine engine cycles to achieve effective very high-bypass-ratio with smaller diameter engines; * Innovative technologies for reduction of fan, jet, combustor, or turbine noise; and * Advanced sound attenuating liners, including active and passive control. Supersonic Propulsion System Technologies * Advanced turbine engine cycle concepts to achieve low takeoff/landing noise and high supersonic cruise efficiency, including high pressure, high bypass multiple spool cycles, inter-stage turbine burning, variable cycle engines; * Advanced propulsion system technologies, including advanced integrated airframe-propulsion control methodologies, adaptive flow control technologies, smart structures for nozzles and inlets, inlet technologies for weight/ performance/ operability/ stability; and * High temperature materials such as monolithic ceramics and nano materials, evaporatively cooled turbine blades, and counter rotating stages enable more compact engine cores, greater thermal efficiency, and higher thrust to weight ratios. Proposals must show improvements to the state-of-the art and viable application to aircraft. A2.02 Fuel Cell Technologies for Aircraft Propulsion and Power Lead Center: GRC Participating Center(s): DFRC Fuel cells offer a promising technology for clean, efficient power generation important to both High Altitude Long Endurance (HALE) remotely piloted aircraft, and future envisioned environmentally friendly commercial transports. Both consumable fuel and regenerative fuel based fuel cells are of interest. The former type is applicable to both HALE and commercial transports, while the latter type is of interest for a solar-electric powered HALE capable of multi-month missions. The consumable fuel based fuel cell will likely use atmospheric air for the cathode gas, while the regenerative systems will likely use pure oxygen stored and regenerated on-board. For both applications, the focus of this subtopic is on hydrogen fuel based systems including liquid for consumable fuel systems and gaseous for regenerative fuel cell systems. To realize these aircraft applications will require one or even two orders of magnitude improvement in unit power and power density (volume and weight) for the power generation system, and specifically the fuel cell stack, as compared to ground based systems. In addition, the systems are required to operate at altitude, including high altitudes (? 60,000 ft) for the HALE applications, and provide service life and reliability significantly greater than ground-based systems. Thus, NASA is seeking “break-through” technologies necessary for aircraft instead of evolutionary improvement to current state-of-the-art. Technologies of specific interest include: * Innovative fuel cell power systems demonstrating high specific power and high efficiency using consumed liquid hydrogen fuel with scalability to 100’s of kW and capable of high altitude operations; * PEM stack demonstrating ? 2 kW/kg and ? 50% efficiency (LHV) with scalability to 100’s of kW; * SOFC stack demonstrating ? 1 kW/kg and ? 50% efficiency (LHV) with scalability to 100’s of kW; and * Innovative regenerative fuel cell energy storage systems and critical components (e.g., unitized fuel cell and electolyzer stack, PEM or SOFC based systems, etc) demonstrating ? 600 watt-hr/kg and high round trip efficiency. A2.03 Hydrogen Fuel Systems and Components for Aircraft Applications Lead Center: GRC Participating Center(s): DFRC, LaRC Hydrogen is the most likely fuel to enable future zero emissions aircraft and High Altitude Long Endurance Remotely Operated Aircraft (HALE ROA). Due to the increased volume required for hydrogen systems as compared to current hydrocarbon fueled aircraft, key technologies are required to reduce feed system weight while maximizing propellant storage efficiency. To be a viable technology for future aircraft systems, hydrogen feed components most likely will require life cycles approaching 10,000+ with an expectation of 20+ years in service, a significant difference from current state-of-the-art for space flight systems. For HALE ROA systems, vehicle mass must be kept low enough for flights up to altitudes exceeding 60,000 ft. Insulation systems must be lightweight and designed for minimum maintenance. Hydrogen storage and feed systems can be either cryogenic or gaseous depending upon the vehicle configuration. Tank mass fraction requirements (mass of storage system/mass of hydrogen) for liquid hydrogen on the order of 15% are expected to meet mission requirements. Hydrogen tank systems applications will be expected to provide storage for flight vehicles for up to 14 days duration with cryogenic systems and 6 months for aircraft with gaseous hydrogen. System safety is a critical factor in the design and development of any hydrogen system. To ensure public safety it is important that highly-sensitive, low-power-use sensors and instrumentation are developed to identify and diagnose potential problems with the hydrogen systems. Technology focus areas will include storage, distribution, and propellant conditions. Innovations are solicited in the following areas: Storage and Distribution Components * Lightweight, low thermal conductivity on-board cryogenic storage tanks, feed lines, valves, and relief devices; * Lightweight, low thermal conductivity insulation for tanks and feed lines that requires minimal inspection and maintenance; * Lightweight, low permeable gaseous hydrogen storage tanks and feed lines; and * Low power, high-sensitivity sensors for hydrogen leak detection and condition monitoring. Propellant Conditioning Components and Technologies * Innovative methods to reduce the volume of stored hydrogen while minimizing system weight; * Technologies for the reformation of hydrocarbon based fuels to hydrogen; * Advanced technologies to minimize losses during loading and unloading of hydrogen, including autonomous operations, tank transfers, delivery to propulsion system, venting, and/or hydrogen recovery; * Advanced technologies to minimize hydrogen losses and reduce energy requirements for system pre-chill, delivery to propulsion system, venting and/or hydrogen recovery, and long duration temperature. Proposals must show improvements to the state-of-the-art and viable application to aircraft. A2.04 Aircraft Systems Noise Prediction and Reduction Lead Center: LaRC Innovative technologies and methods are necessary for the design and development of efficient, environmentally acceptable airplanes, rotorcraft, and advanced aerospace vehicles. In support of the goal of the Quiet Aircraft Technology Project for reduced noise impact on community residents, improvements in noise prediction and control are needed for jet, propeller, rotor, fan, turbomachinery, and airframe noise sources. In addition, improvements in prediction and control of noise transmitted through aerospace vehicle structures are needed to reduce noise impact on aircraft passengers and crew and on launch vehicle payloads. Innovations in the following specific areas are solicited: * Fundamental and applied computational fluid-dynamics techniques for aero acoustic analysis, which can be adapted for design codes; * Simulation and prediction of aero acoustic noise sources particularly for airframe noise sources and situations with significant interactions between airframe and propulsion systems; * Concepts for active and passive control of aero acoustic noise sources for conventional and advanced aircraft configurations; * Innovative active and passive acoustic treatment concepts for engine nacelle liners and concepts for high-intensity acoustic sources, which can be used to characterize engine nacelle liner materials; * Reduction technologies and prediction methods for rotorcraft and advanced propeller aerodynamic noise; * Development of synthesis and auditory display technologies for subjective assessments of aircraft community and interior noise; * Development and application of flight procedures for reducing community noise impact of rotorcraft and subsonic and future supersonic commercial aircraft while maintaining safety, capacity, and fuel efficiency; * Computational and analytical structural acoustics techniques for aircraft and advanced aerospace vehicle interior noise prediction, particularly for use early in the airframe design process; * Technologies and techniques for active and passive interior noise control for aircraft and advanced aerospace vehicle structures; and * Prediction and control of high-amplitude aero acoustic loads on advanced aerospace structures and the resulting dynamic response and fatigue. A2.05 Electric Drive Components, Power Management and Distribution Technologies Lead Center: GRC Participating Center(s): GSFC, JPL, JSC Future environmentally harmonious aircraft propulsion systems may be driven by electric power. These new systems will likely be fueled by hydrogen stored as a cryogenic liquid. Like all flight systems, these new electric based propulsion concepts will require each component to be extremely lightweight, especially when compared to similar ground-based systems. Future specific power requirements for the entire propulsion system from power supply to electric motor could reach 20-kW/kg. The total electric power supplied for aircraft will be orders of magnitude higher than for existing flight-rated secondary electrical systems. Future high power electric systems present a number of challenges for application to volume and weight limited aircraft. NASA is interested in the development of innovative technologies that demonstrate the feasibility of high power densities (>5kW/kg) for electric power delivery and propulsion. Specific areas of interest include but are not limited to the following: * High power density electric motors and actuators, including superconducting, cryogenic and non-cryogenic systems; * Cryogenically cooled lightweight, possibly superconducting, high power transmission lines; * Cryogenically cooled and non-cryogenic lightweight power conditioning and control technology including technologies for isolation of noise-sensitive avionics power busses from main propulsion power busses; * Cryogenically cooled and non-cryogenic lightweight high voltage high power density power management components; * Highly integrated dual function components and systems that have the potential to reduce overall vehicle and subsystem weight (e.g., power conductors that are integrated into the airframe structure, motors directly integrated into the fan/propeller structure); * Advanced enabling technologies such as nanoelectronics, smart sensors, and actuators; * Advanced diagnostics, health monitoring and control concepts, smart sensors, electronics and actuators for enabling self-diagnosis and prognosis, and self-reconfiguration capabilities; * Concepts that integrate distributed sensing with actuation and control logic for micro-level control of parameters (such as propulsion system internal flows, electrical states, etc. that impact performance and environment). Proposals must show improvements to the state-of-the-art and viable application to aircraft. A2.06 Smart, Adaptive Aerospace Vehicles With Intelligence Lead Center: ARC Participating Center(s): LaRC This subtopic emphasizes the roles of aerodynamics, aerothermodynamics, adaptive software, vehicle dynamics in nonlinear flight regimes, and advanced instrumentation in research directed towards the identification, development, and validation of enabling technologies that support the design of future, autonomous aerospace vehicle and platform concepts for aviation safety, and security vehicle systems. Some of the vehicle attributes envisioned by this subtopic include: a) "Smart" vehicle attributes-using advanced sensor technologies, flight vehicle systems are "highly aware" of onboard health and performance parameters, as well as the external flow field and potential threat environments; b) "Adaptive" vehicle attributes-flight avionics systems are reconfigurable, structural elements are self-repairing, flight control surfaces and/or effectors respond to changing flight parameters and/or vehicle system performance degradation; and c)"Intelligent" vehicle attributes-vehicle onboard processing and artificial intelligence technologies, interfaced with advanced vehicle structural component and subcomponent designs and appropriate actuating devices, reacts rapidly and effectively to changing performance demands and/or external flight and security threat environments. Future air vehicles with the above attributes will manage complexity, "know" themselves, continuously tune themselves, adapt to unpredictable conditions, prevent and recover from failures, and provide a safe environment. For atmospheric vehicles and platforms, both military and civil applications are sought, while for aviation applications, emphasis is placed on configurations that enable the discovery of new aviation safety and security concepts. Concepts and corresponding enabling technologies are sought which expand the traditional boundaries of conventional piloted vehicles categories such as General Aviation (GA) or Personal Air Vehicles (PAV), as well as significantly advance the state-of-the-art in remotely operated vehicle classes such as Long-Endurance Sensing Platforms (LESP), Unmanned Aerial Vehicles (UAV) or Unmanned Combat Aerial Vehicles (UCAV) as they can relate to aviation safety and security. Furthermore, for Earth applications, special emphasis is placed on research proposals that attempt to provide solutions for a future state in which revolutionary vehicles operate in a highly integrated airspace including hub and spoke, point-to-point, long-haul, unmanned aircraft, green aircraft, as well as a future state where air vehicle designs reflect a high level of integration in performance, safety and security, airspace capacity, environmental impact and cost factors. There are a number of specific areas of interest: * Conceptual flight vehicle/platform designs featuring variable levels of vehicle and airspace requirements integration, and/or smart, intelligent, and adaptive flight vehicle capabilities, as demonstrated by state-of-the-art systems analyses methods to determine enabling technologies and resulting impacts on future system integrated performance, environmental impact, and safety and security issues; * New algorithms for predicting vehicle loads and response using minimal vehicle state information; * Novel optimization methodologies to support conceptual design studies for highly-integrated flight vehicle and air space concepts and/or smart, intelligent and adaptive flight vehicle capabilities, which demonstrate appropriate design variable selection, scaling techniques, suitable cost functions, and improved computational efficiency; * Physics-based modeling and simulation tools of multiple vehicle classes and corresponding airspace operations aspects to support scenario-based planning and requirements definition of highly integrated vehicle and airspace capacity concepts, including investigations of the potential use of virtual/immersive simulations on future engineering decision making processes; and * Micro-scale wireless communications, health monitoring, energy harvesting, and power-distribution technologies for large arrays of vehicle-embedded MEMS sensors and actuators. A2.07 Revolutionary Atmospheric Flight Concepts Lead Center: DFRC This subtopic solicits innovative flight test experiments that demonstrate breakthrough vehicle or system concepts, technologies, and operations in the real flight environment. The emphasis of this subtopic is the feasibility, development, and maturation of advanced flight research experiments that demonstrate advanced or revolutionary methodologies, technologies, and concepts. It seeks advanced flight techniques, operations, and experiments that promise significant leaps in vehicle performance, operation, safety, cost, and capability; and may require a demonstration or validation in an actual flight environment to fully characterize or validate it. The scope of this subtopic is broad and includes advanced flight experiments that accelerate the understanding, research, and development of advanced technologies and unconventional operational concepts. Examples extend to (but are not limited to) such things as inflatable aero-structures (new designs or innovative applications, new manufacturing methods, new materials, new in-flight inflation methods, and new methods for analysis of inflation dynamics), innovative control surface effectors (micro-surfaces, embedded boundary-layer control effectors, and micro-actuators), innovative engine designs for UAV aircraft, alternative engines/motors/concepts, alternative fuels research (hydrocarbon, hydrogen, or regenerative), sonic boom reduction, noise reduction for Conventional Take-off and Landing/Short Take-off and Landing (CTOL/STOL) aircraft and engines, advanced mass transportation concepts, aerodynamic systems optimization for planetary aircraft (Venus, Mars, Io, and/or Titan), flexible system stability derivative identification, innovative approaches to thermal protection that minimize aerodynamic performance degradation, innovative approaches to structures, stability, control, and aerodynamics integration schemes, and innovative approaches to incorporation of UAV operations into commercial airspace. This subtopic is intended to advance and demonstrate revolutionary concepts and is not intended to support evolutionary steps required in normal product development. Proposals should emphasize the need of flight testing a concept or technology as a necessary means of verifying or proving its worth; emphasis should also be given to multidisciplinary integration of advanced flight systems. The benefit of this effort will ultimately be more efficient aerospace vehicles, increased flight safety (particularly during flight research), and an increased understanding of the complex interactions between the vehicle or technology concept and the flight environment. A2.08 Modeling, Identification, and Simulation for Control of Aerospace Vehicles to Prepare for Flight Test Lead Center: DFRC Safer and more efficient design of advanced aerospace vehicles requires advancement in current predictive design and analysis tools. The goal of this subtopic is to develop more efficient software tools for predicting and understanding the response of an airframe under the simultaneous influence of structural dynamics, thermal dynamics, steady and unsteady aerodynamics, and the control system. The benefit of this effort will ultimately be an increased understanding of the complex interactions between the vehicle dynamical subsystems with an emphasis towards flight test validation methods for control-oriented applications. Proposals for novel multidisciplinary nonlinear dynamic systems modeling, identification, and simulation for control objectives are encouraged. Control objectives include feasible and realistic boundary layer and laminar flow control, aero elastic maneuver performance, and load control including smart actuation and active aero structural concepts, autonomous health monitoring for stability and performance, and drag minimization for high efficiency and range performance. Methodologies should pertain to any of a variety of types of vehicles, such as Unmanned Aerospace Vehicles/Remotely Operated Aircraft (UAV/ROA), and flight regimes ranging from low-speed High-Altitude Long-Endurance (HALE) to hypersonic and access-to-space aerospace vehicles. Proposals should address one or more of the following: * Accurate prediction with validation of steady and unsteady pressure, stress, and thermal loads; * Effective multidisciplinary dynamics analysis algorithms with flight-test correlation capability conducive to validation with test data, such as with finite-element aeroservoelastic computations; * Time-accurate simulation systems from nonlinear multidisciplinary dynamics models with applications toward flight-testing, such as with reduced-order CFD-based methods; * Novel and efficient schemes for control-oriented identification of nonlinear aeroservoelastic dynamics from test data with provisions for uncertainty estimation and model correlation; * Online and autonomous model update schemes for loads, aerodynamic, and aero elastic model identification for stability and performance monitoring and prediction in adaptive control; * Self-learning control strategies for aero structural vehicles and development of enhanced real-time controls software and hardware for long-term onboard systems operation; * Integration of modeling, analysis, simulation, and identification techniques for control objectives in a unified, compatible manner; and * Innovative, high-performance facilities for integrated simulation and graphical interface, or virtual reality systems, for multidisciplinary aerospace systems. A2.09 Flight Sensors and Airborne Instruments for Flight Research Lead Center: DFRC Real-time measurement techniques are needed to acquire aerodynamic, structural, and propulsion system performance characteristics in flight and to safely expand the flight envelope of aerospace vehicles. The scope of this subtopic is the development of sensors or instrumentation systems for improving the state-of-the-art in aircraft flight testing. This includes the development of sensors to enhance aircraft safety by determining atmospheric conditions. The goals are to improve the effectiveness of flight testing by simplifying and minimizing sensor installation, measuring new parameters, improving the quality of measurements, and minimizing the disturbance to the measured parameter from the sensor presence or deriving new information from conventional techniques. This subtopic solicits proposals for improving airborne sensors and instrumentation systems in all flight regimes. These sensors and systems are required to have fast response, low volume, minimal intrusion, and high accuracy and reliability. Innovative concepts are solicited in the areas that follow below. Vehicle Condition Monitoring Sensor development in support of vehicle health and performance monitoring includes the monitoring of aerodynamic, structural, propulsion, electrical, pneumatic, hydraulic, navigation, control, and communication subsystems. Proposals that focus solely on health management algorithms and systems integration should be addressed in the Automated Online Health Management and Data Analysis subtopic. Vehicle Environmental Monitoring Sensor development in support of vehicle environmental monitoring includes the following: * Non-intrusive air data parameters (airspeed, air temperature, ambient and stagnation pressures, Mach number, air density, and flow angle); * Off-surface flow field measurement and/or visualization (laminar, vortical, and separated flow, turbulence) zero to 50 meters from the aircraft; * Boundary layer flow field, surface pressure distribution, acoustics or skin friction measurements or visualization; and * Unusually small, light and low-power instrumentation for use on miniature aircraft and high altitude long endurance vehicles. TOPIC: A3 Airspace Systems NASA's Airspace Systems (AS) program is investing in development of revolutionary improvements and modernization for the air traffic management (ATM) system. The AS Program will enable new aircraft, new aircraft technologies, and air traffic technology to safely maximize operational efficiency, flexibility, predictability, and access into airspace systems. The major challenges are to accommodate projected growth in air traffic while preserving and enhancing safety; provide all airspace system users more flexibility and efficiency in the use of airports, airspace and aircraft; reduce system delays; enable new modes of operation that support the FAA commitment to "Free Flight" and maintain pace with a continually evolving technical environment, and provide for doorstep to destination transportation developments. AS Program objectives are: improve mobility, capacity, efficiency and access of the airspace system; improve collaboration, predictability and flexibility for the airspace users; enable modeling and simulation of air transportation systems; enable runway-independent aircraft and general aviation operations; and maintain system safety and environmental protection. NASA is working to develop, validate, and transfer advanced concepts, technologies, and procedures through partnership with the Federal Aviation Administration (FAA), other government agencies, and in cooperation with the U.S. aeronautics industry. A3.01 Next Generation Air-Traffic Management Systems Lead Center: ARC Participating Center(s): DFRC The challenges in Air Traffic Management (ATM) are to create the next generation system and to develop the optimal plan for transitioning to the future system. This system should be one that (1) economically moves people and goods from origin to destination on schedule, (2) operates without fatalities or injuries resulting from system or human errors or terrorist intervention, (3) seamlessly supports the operation of unmanned aerial vehicles (UAVs) or remotely operated aircraft (ROAs), (4) is environmentally compatible, and (5) supports an integrated national transportation system and is harmonized with global transportation. This can only be achieved by developing ATM concepts characterized by increased automation and distributed responsibilities. It requires a new look at the way airspace is managed and the automation of some controller functions, thereby intensifying the need for a careful integration of machine and human performance. As these new automated and distributed systems are developed, security issues need to be addressed as early in the design phase as possible. To meet these challenges, innovative and economically attractive approaches are sought to advance technologies in the following areas: * Decision support tools (DST) to assist pilots, controllers, and dispatchers in all parts of the airspace (surface, terminal, en route, command center); * Integration of DST across different airspace domains; * Next generation simulation and modeling capability-models of uncertainty and complexity, National Airspace System (NAS) operational performance, economic impact; * Distributed decision making; * Security of advanced ATM systems; * System robustness and safety-sensor failure, threat mitigation, health monitoring; * Weather modeling and improved trajectory estimation for traffic management applications; * Role of data exchange and data link in collaborative decision-making; * Modeling of the NAS; * Distributed complex, real-time simulations-components with different levels of fidelity, human-in-the-loop decision agents; * Integrated ATM/aircraft systems that reduce noise and emissions; * Automation concepts for advanced ATM systems and methodologies that address transitioning to more automated systems; * Application of methodologies from other domains to address ATM research issues; * Intelligent software architecture; * Runway-independent (e.g., Vertical Take-off Landing [VTOL], Short Take-off and Landing [STOL], and Vertical/Short Take-off and Landing [V/STOL]) aircraft technologies required to meet national air transportation needs, to satisfy requirements for airline productivity, passenger acceptance, and community friendliness, and autonomous operations; * Automated, real-time detect, see, and avoid operations; * Intermodal transportation technologies; and * Each of the abovementioned technologies and other technologies specifically fostering the operation of unpiloted aircraft within NAS under control of the ATM system, including, but not limited to, innovative control, navigation, and surveillance (CNS) concepts; also considering high altitude, long endurance operations. This page has intentionally been left blank. 9.1.2 EXPLORATION SYSTEMS On January 14, 2004, the President directed NASA to embark upon a robust space exploration program that will advance the nation's scientific, security, and economic interests. This is the fundamental goal of the Vision for Space Exploration and, therefore, the primary objective of the Exploration Systems Mission Directorate (ESMD). The Exploration Systems Mission Directorate is a new organization within NASA. It is dedicated to creating a constellation of new capabilities, supporting technologies, and performing foundational research that enables and supports sustained and affordable human and robotic exploration. In order to support its complex mission, the directorate has been organized into eight divisions: the Office of Research, the Development Programs Office, the Office of Mission Integration, Acquisition and Mission Support, the Contracts Division, the Requirements Division, the Office of Communication, and the Administration Office. Within these offices are numerous subdivisions, which are integral to the objectives of ESMD, including Constellation Systems, Exploration Systems Research and Technology, Prometheus Nuclear Systems and Technology, and Human Systems Research and Technology. The goal of these subtopics will be to help supplement and enhance the ongoing research of ESMD through the involvement of creative high tech firms eligible for SBIR contracts. http://www.exploration.nasa.gov/ TOPIC: X1 Communications, Computing, Electronics and Imaging (CCEI) 75 X1.01 In-Space Computing and Reconfigurable Electronics (GSFC) 75 X1.02 Extreme Environment Electronics/SEE (JPL) 76 X1.03 Sensing and Imaging (JPL) 77 X1.04 Surface Networks and Access Links (GRC) 78 TOPIC: X2 Advanced Materials and Structural Concepts (AMSC) 79 X2.01 Advanced Materials (LaRC) 79 X2.02 Structures and Habitats (LaRC) 79 X2.03 Nanostructured Materials (ARC) 80 TOPIC: X3 Power Propulsion and Chemical Systems (PPCS) 81 X3.01 Power Generation and Transmission (GRC) 81 X3.02 Energy Storage (GRC) 82 X3.03 Cryo and Thermal Management (MSFC) 83 TOPIC: X4 Advanced Studies Concepts and Tools (ASCT) 84 X4.01 Technology Systems Analysis (GRC) 85 X4.02 Design and Analysis Tools (GSFC) 86 TOPIC: X5 Software, Intelligent Systems and Modeling 86 X5.01 Software Engineering (ARC) 87 X5.02 Human Autonomy Interaction (JSC) 88 TOPIC: X6 Advanced Space Operations (ASO) 89 X6.01 Intelligent Operations Systems (ARC) 89 X6.02 Space Assembly Maintenance and Servicing (GSFC) 90 X6.03 Launch Site Technologies (KSC) 91 TOPIC: X7 High Energy Space Systems (HESS) 92 X7.01 Chemical Propulsion Systems and Modeling (MSFC) 92 X7.02 Chemical Propulsion Components (MSFC) 93 X7.03 High-Power Electric Propulsion (GRC) 94 X7.04 Aeroassist Systems (JSC) 95 TOPIC: X8 Advanced Space Platforms and Systems 96 X8.01 Vehicle Health Management Systems (ARC) 96 X8.02 Intelligent Modular Systems (MSFC) 97 TOPIC: X9 Lunar and Planetary Surface Operations 98 X9.01 In Situ Resource Utilization and Space Manufacturing (JSC) 98 X9.02 Surface Mobility/Mechanisms (JPL) 101 TOPIC: X10 Prometheus Technologies 102 X10.01 Long-Life Validation and Flight Qualification of Nuclear Space Systems Hardware Prior to Flight Use (MSFC) 102 X10.02 Critical Technologies for In-Space Application of Nuclear Thermal Propulsion (GRC) 103 X10.03 Critical Technologies for Space-Based Nuclear Fission Power Systems (GRC) 104 X10.04 Heat Rejection Technologies for Nuclear Systems (GRC) 105 X10.05 Computational Material Science Tools for Space Nuclear Design Systems (GRC) 106 TOPIC: X11 Human Systems Research and Technology 107 X11.01 Radiation Health (JSC) 107 X11.02 Human Health Countermeasures (JSC) 109 X11.03 Autonomous Medical Care (JSC) 110 TOPIC: X12 Life Support and Habitation 112 X12.01 Advanced Life Support: Air and Thermal (JSC) 112 X12.02 EVA Technologies (JSC) 114 X12.03 Contingency Response Technologies (GRC) 115 X12.04 Advanced Environment Monitoring and Control (JPL) 116 X12.05 Advanced Life Support: Food Provisioning and Biomass (JSC) 117 X12.06 Habitation Systems (JSC) 118 X12.07 Advanced Life Support: Water and Waste Processing (JSC) 119 TOPIC: X13 Human Systems Integration 120 X13.01 Space Human Factors Engineering (JSC) 120 X13.02 Behavioral Health and Performance (ARC) 121 X13.03 Systems Engineering and Requirements (JSC) 121 TOPIC: X14 Space-Based Industry Enabling Technologies 122 X14.01 Space-Based Industries (MSFC) 123 X14.02 Multi-Use Microgravity and Software (JSC) 123 TOPIC: X1 Communications, Computing, Electronics and Imaging (CCEI) The goals of this topic are to develop advanced space communications and networking technology; high-performance computers and computing architectures for space systems and data analysis; low-power electronics to enable robotic operations in extreme environments; and imaging sensors for machine vision systems and the characterization of planetary resources. Subtopics of this topic area include: In-Space Computing and Reconfigurable Electronics. This subtopic includes architectures and components required for space-based computing and avionics systems. Architecture efforts will emphasize modular, fault-tolerant approaches that leverage commercial standards and COTS devices. Component work will focus on capabilities for enhancing general- and special-purpose processing to meet multiple mission goals. Products of particular interest include reconfigurable electronics, fault-tolerant, reconfigurable processor, micro-controllers and storage devices. Extreme Environments/Low Temperature Electronics. This subtopic includes radiation-tolerant, wide-temperature-range digital, analog, mixed signal, dynamic member and RF electronic components, and integrated modules suitable for operation in the extreme environments of the Moon, Mars and other deep space destinations. Efforts will emphasize supporting electronics for sensors, actuators and communications. The focus of this subtopic is radiation-tolerant, analog, mixed signal, dynamic memory and RF electronic components, and integrated modules suitable for operation in extreme low-temperature space environments. Sensing and Imaging. This subtopic includes orbital remote sensing for topographical and resource mapping and atmospheric profiling and control-loop sensing for robotic functions such as rendezvous and docking, assembly and construction, and precision landing. Products of particular interest include control-loop sensors for position, velocity and force, rapid detection and readout arrays for 2D and 3D imaging at 1.5 µm and multi-wavelength IR and visible laser arrays. Surface Networks and Access Links. This subtopic includes communications technologies to support operational activities in space beyond low Earth orbit and on planetary surfaces in which nodes are simultaneously connected to each other, to Earth, and to the CEV via in-space relay orbiters, and via wired and wireless networks providing the bidirectional voice, video and data needed. The focus of this subtopic is on the modular, reconfigurable RF communications and networking technologies needed to support a human presence on remote lunar and planetary surfaces with short-range networks and access links to long-haul systems. X1.01 In-Space Computing and Reconfigurable Electronics Lead Center: GSFC Participating Center(s): JSC, MSFC The goal for this subtopic is the development of advanced space technology to further high-performance computers and computing architectures and reliable electronic systems that can operate effectively for long periods of time in harsh environments. These systems require management of low power and radiation, and must be reliable, robust and reconfigurable. The objective for this development goal is to elicit novel architectural concepts and component technologies that have realistic potential and achievable applications and are responsive to the priority areas of this subtopic. Technologies will be selected based on the potential that their final end products are sustainable (affordable, reliable/safe and effective), and will advance solutions to the challenges of reusability, modularity and autonomy. Priority areas are: Data processing * General purpose processors (piece part, rather than an entire board) possessing fault tolerance at cell and or die levels, floating point and error correction. * Technologies that reduce the physical size and power requirements of computing systems: making the data system more adaptable, modular, and cost effective. * New standard models for analysis of interplanetary radiation and radiation belts, and technologies that enable radiation measurements such as total dose and single event effects in computing systems: enhances capability to design radiation tolerant data systems, monitor systems in flight, and predict errors and contingencies. Reconfigurable Electronics and Implementations * Reconfigurable designs and architectures that support fault tolerance and are functionally and physically modular. * Solutions, designed around generic blocks, for recovery from multipoint failures (as opposed to single fault) component failure, where a system can monitor and identify the failing components, and self-repair or bypass small portions of the electronics. These prioritized generic blocks would enable graceful degradation of higher functions while maintaining the system core functionality. Data System Support Electronics * Radiation-hard microcontrollers, phase lock loops (PLL), and high-speed oscillators (greater than 150 MHz, equal duty cycle). * FPGA: Environmentally tested, reliable, tolerant IO, radiation hardened cell structures, Anti-Fuse or reconfigurable. * Robust and reliable non-volatile storage devices such as EEPROMs and FLASH memory. Command and Data Transfer * Inter-system data transfer communications between spacecraft subsystems based on standard interfaces that address high multi-drop throughput (10 to 100 mbps), self diagnosis, inherent redundancy and low power, and support subsystem data transfer to realize higher autonomy. * Intra-system data transfer communications within the spacecraft subsystems, between cards within a box, to replace the conventional passive backplanes, e.g., switched fabric backplanes with fault detection and serial interfaces. X1.02 Extreme Environment Electronics/SEE Lead Center: JPL Participating Center(s): GSFC, MSFC Moon equatorial regions experience wide temperature swings from -180°C to +130°C during the lunar day/night cycle, and the sustained temperature at the shadowed regions of lunar poles can be as low as -230°C. Mars diurnal temperature changes from about -120°C to +20°C. All exploration endeavors, including robotic, habitat, and ISRU systems that are expected to reliably operate on the Moon or Mars surface for years will need electronics that are able to survive and operate in a wide temperature range and thermal-cycling environment. The lunar and Martian temperatures are well outside the specification range of military and commercial electronics. While many types of devices, especially Si CMOS transistors, can operate down to low temperatures. There are significant circuit design challenges that need to be addressed, especially in the case of mixed signal and analog circuits. In addition, thermal cycling present in lunar, and especially Mars, environments introduces reliability concerns associated with mechanical stress and fatigue of the IC package. For example, compounds optimized for Earth-like packaging of electronic systems have glass transition temperatures that are within the cycling range of these environments, and cycling of electronic systems packaged using these materials will likely result in package failures. Hence, the choice of packaging technology and material combination used is extremely critical for these missions. Proposals are sought in following specific areas: * Wide temperature (-180°C to +130°C) and low-temperature (-230°C), radiation-tolerant and SEU immune, low power, mixed-signal circuits including analog-to-digital converters, digital-to-analog converters, low-noise pre-amplifiers, voltage and current references, multiplexors, power switches, microcontrollers, and integrated command/control/drive electronics for sensors, actuators, and communications transponders. * High-density packaging able to survive large numbers of thermal cycles (hundreds) and tolerant of the extreme temperatures of the Moon and Mars, including appropriate selection of packaging materials combinations (substrates, die-attach, encapsulants, etc.) modular system level electronics packaging, including power, command and control, and processing functions, enabling integration of electronics with sensors and actuators elements. * Wide temperature (-180°C to +130°C) and ultra-low temperature (-230°C) RF electronics for short range and long-range communication systems. * Computer Aided Design (CAD) tools for predicting the electrical performance, reliability, and life cycle for low-temperature electronic systems and components. Research should be conducted to demonstrate technical feasibility during Phase 1 and show a path toward a Phase 2 hardware/software demonstration, and when possible, deliver a demonstration unit for testing at the completion of the Phase 2 contract. X1.03 Sensing and Imaging Lead Center: JPL Participating Center(s): GSFC, LaRC Sensing and imaging systems can provide a number of capabilities required for anticipated NASA missions including exploration of Mars and the Moon. Capabilities of interest include the following: * Orbiting sensors to map: - Extent and concentration of useful, surface, or subsurface resources to identify promising outpost or science sites and traversable terrains; - Surface topography and roughness to identify promising safe landing sites for human, robotic science, and pre-provisioning missions, and to guide pinpoint landing algorithms. * Robot-mounted sensors for: estimating robot pose and motion; recovering 3D scene structure; identifying hazards or objects of interest; identifying articulation of observed objects, and performing visual serving. Flight ready (radiation and temperature hardened), high cycle rate, and low power systems are generally preferred. Applications include: - Autonomous rendezvous and docking; - Pinpoint landing; - Surface navigation; - Surface and on-orbit assembly/construction; - Resource mining/processing; - Multi-vehicle cooperation. Specific technologies of interest in addressing these challenges include: * Rapid frame rate arrays for 1, 1.5 and 2 µm vision (2D and 3D); * Multi-wavelength laser arrays; * Flight-ready, high-speed, medium-resolution (640x480) stereo-vision sensors; * Flight-ready, low-power lighting systems (headlights) to allow imaging during nighttime robotic operations; * Tightly coupled inertial and vision sensors for pose estimation; * Ground truthing systems for evaluating performance of ranging systems. A number of related technologies are of interest but are covered under other subtopics, including: * High power or high rep-rate lasers (S6.02, S1.04); * Ultra-high sensitivity detectors and arrays (S4.01); * Active and passive microwave sensors (S6.04, S6.05). X1.04 Surface Networks and Access Links Lead Center: GRC Participating Center(s): GSFC, JPL, JSC To develop safe and sustainable exploration capabilities at minimum cost, while maximizing return, an incremental spiral development process will guide a build out of an integrated communication, navigation, networking, computing, informatics, and power architecture that supports all surface and proximity nodes, including humans in spacesuits, robots, rovers, human habitats, satellite relays, and pressurized vehicles. The architecture will enable operational activities in which both fixed and mobile nodes with vastly differing communications requirements are seamlessly interoperable. Nodes are simultaneously connected to each other, to Earth, and to the CEV via in-space relay orbiters, and via wired and wireless networks that provide the bidirectional voice, video, and data needed. The need to be self-sufficient during exploration requires local control and an unprecedented level of autonomous operation to seamlessly connect the nodes and reduce operations cost. The Moon and Mars environments require SEU and extreme temperature-tolerant equipment tightly constrained by power, mass, and volume. Human presence requires at least one usable bidirectional link to the communications network at all times and high definition video to engage the public interest. This subtopic focuses on the modular, reconfigurable RF communications and networking technologies needed to support a human presence on remote lunar and planetary surfaces with surface-to-surface and surface-to-orbit (access) communications. Surface Networks The complexity of astronaut excursions, habitats, surface manned and unmanned rovers, and landers make surface operations and man-occupation complex and daunting tasks. Exploration of planetary surfaces will require short-range, bidirectional, multi-point links to provide on-demand, autonomous interconnection among surface-based assets. Some of the nodes will be fixed (base stations) and some will be moving (rovers and humans). This will encompass a number of communications and networking technologies for communications in the 2.4 Ghz range, including: integrated low mass, low power (100's of milliwatts) transceivers for very short-range interfaces with sensors and other small devices; power-efficient, miniature, modular transceivers for short-range communications among large (e.g., lander) and medium-sized (e.g., rover) surface assets; reconfigurable directionally selectable, multi-frequency arrays for wide coverage, high-gain links among surface assets; miniaturized modular antenna technology for surface-to-surface communications among mobile and fixed nodes; wireless products integrated with low-power space-rated ASICs and FPGAs; short (~1km) range access point base stations, or wireless router bridges for extending surface network coverage; fixed, long (~50km) range, wireless network terminals for extending high data rate communications over large distances; self-healing ad-hoc network MAC and protocols for intelligent, autonomous link management; and networking technologies to enable autonomous, seamless interconnectivity among all nodes. Access Links To interface with orbiting relays, terminals capable of providing seamless connectivity between surface networks and orbiting relays will be positioned on lunar and planetary surfaces and in orbit. Such an access link communications system will include: high rate, efficient, solid state amplifiers capable of very high data rates over 1,000-10,000 km distances with ranging signals embedded; very low-power data rates, and cost inter-spacecraft S-band transceivers/transponders for inexpensive spacecraft; optical transceivers capable of very high data rates over 1,000-10,000 km distances; SEU and solar flare tolerant transponders capable of: programmable wide-carrier frequency ranges from S-band to Ka-band, taking GPS measurements, and handling IP at the digital level; micro software radio technology for autonomous and intelligent space applications; low mass, volume, power, and cost-stable oscillators to provide accurate time and frequencies for autonomous operations; autonomously reconfigurable receivers capable of automatic link configuration and management; microwave ranging hardware built into communication systems for rendezvous and collision avoidance; and ad hoc long range spacecraft-to-spacecraft network protocols to setup links on demand, such that each node can route data through to another node. TOPIC: X2 Advanced Materials and Structural Concepts (AMSC) The goals of this topic are to develop high-performance materials, fabrics, modular vehicle structural concepts, and mechanical components for exploration systems. Major technology drivers include reducing system cost, mass, and launch volume; enabling the construction of space and surface infrastructure from modular elements; extending the performance and lifetime of systems operating in extreme environments; and providing systems with integrated diagnostic and adaptive capabilities. This topic is responsible for basic technology level research, development, and testing through experimental and/or analytical validation of novel materials and structural concepts for a wide range of exploration applications. The three subtopics include Advanced Materials and Mechanisms, Structures and Habitats, and Nanotechnology. X2.01 Advanced Materials Lead Center: LaRC Participating Center(s): GRC, MSFC Technology areas included in this subtopic are high performance, super lightweight structural materials, space-durable materials, multifunctional materials, and flexible material systems. Materials of interest include ceramics, metals, polymers, and their composites as well as coatings for erosion resistance and environmental protection. Proposals with innovative and revolutionary ideas in the area of advanced materials are sought for explorations applications such as: * Flexible fabrics and thermal insulation for spacesuits and habitats; * High strength-to-weight and high temperature composite materials for lightweight vehicle structures and power and propulsion systems; * Self-healing materials to repair damage to spacesuits, habitats, and wire insulation electronics, sensing, and actuators for monitoring system health and adapting to changing mission conditions; * Flexible fabrics relevant to mission needs such as inflatable systems for ballutes, habitats, airbags, parachutes, and suits; * Innovative approaches to materials systems yielding durable, lightweight, flexible films and fabrics. X2.02 Structures and Habitats Lead Center: LaRC Participating Center(s): DFRC, MSFC, JSC This subtopic solicits innovative structural concepts, materials, and assembly techniques that support the development of modular space systems. Also needed is a criteria to judge the different concepts in terms of impact on the overall performance and weight. Structural concepts can include inflatable, erectable, deployable, or easily connected modules to create large space structures utilizing membranes, composites, or other material concepts. Modular units can provide reconfigurable structures, such as multiple-energy configurations using cables and linkages, compliant structures or mechanisms that adapt to varying surfaces, or multi-purpose integrated structures, such as load-bearing modular power distribution, thermal management, or radiation protection systems. Additionally, this subtopic includes research related to novel rotating devices, actuators, tribology, and seals. It further includes intelligent structural, electrical, and fluid interfaces to enable the assembly (or 'self-assembly') of modular systems. Of particular interest are inflatable structures and habitats to minimize launch volume and costs. Large inflatable structures can be folded into compact packages for launch, pressurized for deployment once in space, and rigidized after deployment so that internal pressure is not required to maintain structural stiffness and shape. New concepts, materials, and methods for in-space structures and habitats to enable humans to safely and effectively live and work in space are needed. Specifically, structures or habitats with integral radiation shielding, impact shielding, thermal management, and integral diagnostics/health monitoring capabilities are of interest as well as high strength-to-weight materials (e.g., foamed materials), structural elements, and beams that can be deployed or fabricated in situ. Development of smart and multifunctional modular structures, including the use of embedded sensors and actuators, is encouraged. Also solicited are assembly technologies such as innovative connectors for joining and/or bonding techniques, module positioning and alignment concepts, component deployment or erection concepts, and component/module inspection and verification techniques. Structures and materials that support reconfigurable modular architectures are also solicited. Modeling and structural testing techniques and analyses that support the design of modular structural concepts or their assembly are of interest. Two areas are of particular interest: one is controls-structures interaction (CSI) techniques and the second one is hybrid-test and physics based-modeling approaches. Application of advanced controls-structures interaction (CSI) techniques for measuring and controlling structural dynamics and geometry are important. Solutions for incorporation of CSI techniques for controlling such inflatable structures are also highly desirable. On hybrid modeling, ways to integrate test and physics-based models for cases where the physics-based models are not sufficient is also desirable. X2.03 Nanostructured Materials Lead Center: ARC Participating Center(s): LaRC, JSC The applications of advances in Nanotechnology are anticipated to have a profound impact on NASA’s future missions by offering significant advantages in terms of cost affordability and reliability from multifunctional materials. Nanotechnology enables systems performance beyond those expected from conventional materials. While many fundamental findings are reported in the literature, there is a strong need to focus efforts on the demonstration of real benefits provided by nanostructured material systems. It is especially interesting to meet exploration challenges with the development of high strength-to-weight and multi-functionality possible from the unique combinations of desirable properties of the nano-structred materials. The promise of high strength-to-weight, multi-functional, nano-structured materials has led to intense interest in developing them for near-term applications for human spaceflight and exploration. Nano-structured materials of interest include, but are not limited to, the utilization of single wall, carbon, nanotube-based composites, ceramic nanofibers, and bio/nano-inspired materials and composites. Due to the size scale and fundamental physical properties of the structures involved, a successful proposal for applications development should demonstrate a mature understanding of nano-material synthesis and material quality, as well as incorporate the development and use of new characterization methodologies to fully assess the impact of the nano-structured materials upon a given matrix or system. The specific focus of this subtopic will include, but not be limited to: * New materials for structures and components offering significant mass reduction and increased strength with improved thermal conductivity, low permeability, low density, and improved damage tolerance through self-repairing mechanisms; * Application of nano-structured materials to self-healing and self-repair materials and concepts; * Nano-structured materials offering enhanced radiation protection; * Development of nano-material systems that are resistant to large thermal fluctuations, radiation, electrostatic charging, abrasion, and micrometeoroid debris damage; * Nano-materials for energy generation, storage, and distribution. TOPIC: X3 Power Propulsion and Chemical Systems (PPCS) The goals of this topic are to develop high-efficiency power conversion/generation, energy storage, and power management and distribution systems to provide abundant power for long-duration, sustainable, human and robotic exploration missions as well as systems for the storage and handling of cryogens and other propellants. The subtopics include: Power Generation and Transmission, Energy Storage, and Cryogenic and Thermal Management. X3.01 Power Generation and Transmission Lead Center: GRC Participating Center(s): JPL, MSFC All innovative technologies for power generation and conversion are highly encouraged under this subtopic. Proposals addressing technologies, including solar photovoltaic conversion, thermo-photovoltaic conversion, thermoelectric conversion, and thermodynamic conversion (heat engines), etc., are encouraged. In addition, research and technology development in topics related to advanced power cabling and power management are also needed. Significant improvements in photovoltaic systems are required to enable future exploration missions. Dramatic increases in array mass specific power (>1000 W/kg), reductions in stowed volume, increases in operational voltages to 1000V, increases in radiation hardness enabling reliable operation in high-radiation environments, increases in survivability over wide temperature extremes, as exists on a lunar surface, and developments of automated deployment systems for surface power applications. Developments are sought for photovoltaic cells on flexible, ultra-lightweight substrates, array technologies that maintains the high mass specific power of these cells, nanostructures incorporated to enhance the performances of thin-film, organic/inorganic, or single-crystal photovoltaic cells and thermo-photovoltaic cells. Demonstrations of high efficiency, lightweight, concentrator cell and supporting array techniques, multi-quantum well and multi-quantum dot devices, and advanced multi-band gap devices are also of interest. Advanced photovoltaic areas of emphasis include high-efficiency quantum well technology. Nano-engineered materials are an area of emphasis for all of these applications. High power solar dynamic power conversion systems, including Brayton and Stirling, support the development of solar-electric propulsion and power systems requiring low overall system specific mass (kg/kW). The objectives for solar dynamic systems, with power output capacities ranging from 100W to >100kW, require demonstrating thermal efficiencies greater than 30% over a range of cycle temperature ratios and heat rejection temperatures. A system specific mass of <200 kg/kWe modularity, and high reliability by fault-tolerant system architectures are desired. Technological advances are needed for large deployable solar concentrators and secondary concentrators, high temperature heat receivers with thermal energy storage capability, and advanced lightweight heat rejection sub-systems. For Brayton power, advances are needed in ceramic high temperature turbine technology, high efficiency compressors matched to turbine performance, high efficiency alternators, lightweight carbon composite heat exchangers and recuperators. For Stirling, advances required are: high frequency, low inductance linear alternators, low mass displacer, hot-end materials and structures, efficient cold-end thermal integration with lightweight radiators, high efficiency low mass controllers, and regenerators. For power management and distribution systems, areas of emphasis include: high reliability, light weight, radiation-hardened power electronic components (semiconductor switches, diodes, capacitors, and transformers); high voltage switching contactors (>100Vdc) tolerant to corona discharge; and high efficiency (>95%) modular DC converters for boost and buck conversion. Concepts for monitoring power system status, fault tolerance, redundancy, and energy management. Advanced power cabling including high voltage, superconductors, carbon nanotube, and cable mbedded with structural elements. Also of importance are, intelligent and modular distribution switchgear and power management that can autonomously reconfigure in response to faults and changing loads. Research for Wireless Power Transmission (WPT) technology development, to reduce the cost of electrical power and to provide a stepping stone to NASA for delivery of power between objects in space, between space, and surface sites, between ground and space, and between ground and air-platform vehicles. WPT can involve lasers or microwaves along with the associated power interfaces. Microwave and laser transmission techniques have been studied with several promising approaches to safe and efficient WPT identified. These investigations have included microwave phased array transmitters, as well as visible light laser transmission, and associated optics. There is a need to produce "proof-of-concept" validation of critical WPT technologies for both the near-term as well as far-term applications. These investments will be harvested in near-term, beam-safe demonstrations of commercial WPT applications. Proposals are sought that include such activities as the technology elements, architecture, and demonstration programs for wireless transmission of power. Receiving sites (users) include ground-based stations for terrestrial electrical power, orbital sites to provide power for satellites and other platforms, future space elevator systems, and space-based sites for spacecraft and space vehicle propulsion. X3.02 Energy Storage Lead Center: GRC Participating Center(s): JPL, JSC All exploration missions require advanced primary and rechargeable energy storage devices that are high-density, have long-life capability, and have the ability to function at extreme temperatures. The energy storage requirements vary significantly from a few watt-hours (astronaut equipment) to hundreds of kilowatt-hours (human outposts), depending on the mission. Similarly, power requirements also vary from a few watts (astronaut equipment) to several kilowatts, depending on the mission (human rovers, human outposts, and crew exploration vehicles). Advanced energy storage devices, such as primary batteries, rechargeable batteries, fuel cells, and flywheels are required to enable future robotic and human exploration missions. Advanced primary batteries are required for applications such as astronaut equipment, communication devices, in situ resource utilization systems, sensor networks, etc. Advanced rechargeable batteries are required for solar powered landers and rovers, solar powered human outposts, astronaut equipment, and spacecraft. Primary fuel cells are required for crew exploration vehicles and rovers. Regenerative fuel cells provide an enabling, mass-efficient solution for surface electrical energy storage for future long-duration human exploration of the lunar and Mars surfaces. Flywheels provide an effective solution to meeting peak power requirements when used in hybrid systems with battery or fuel cell systems providing the base power, and offer the capability of integrated power and attitude control. Energy Storage devices are needed for EVA and EVA accessory applications as well as vehicle and base back-up or peaking power applications. Areas of emphasis include advanced battery materials and cell designs with the potential to achieve the performance and safety advancements required for manned applications. Hybrid systems consisting of fuel cells, batteries, flywheels, and/or ultra capacitors are of interest. Also sought are high energy density fuel cell reactant storage innovations compatible with the performance and safety goals specified herein. Micro and nano-engineered materials are an area of emphasis for all of these applications. Proposals addressing micro-batteries, and integrated power generation and storage are sought. Primary and rechargeable lithium-based batteries with advanced anode and cathode materials and advanced liquid and polymer electrolytes and solid-state systems are of particular interest. Technology advancements that contribute to the following performance goals are sought: specific energy >180 Wh/kg, calendar life (>15years), and a wide operating temperature range (-60°C to 60°C). Primary batteries with the following performance targets are of interest: low temperature operation capable of delivering >30% of their ambient temperature capacity at temperatures as low as -100°C, specific energy: >400 Wh/kg, long calendar life >15 years, and high rate capability >C/10. Fuel cell (FC) and regenerative fuel cell (RFC) systems with power capabilities in the range of 100-1000 watts and 2-10kW are of interest. Technological advances are sought that FC/RFC based systems with the following characteristics: specific energies: FC >1500 W/kg, RFC >600 Wh/kg. Efficiencies: FC>70% at 1500 W/kg, RFC >60% at 600 Wh/kg, and lifetimes: FC >10,000 hours, RFC >1500 cycles. Concepts that incorporate passive operation and advanced reactant storage options (example: H2, O2) are sought. Advanced fuel cell development should include proton exchange membrane fuel cells (PEMFC - high and low temperature), regenerative fuel cells (RFC), and solid oxide fuel cells (SOFC). PEMFC areas of emphasis include long-life stacks and systems with emphasis on gravity-independent water management within the stack or elsewhere in the system, passive water separators, and passive reactant recirculation devices. RFC areas of emphasis include long-life, high-efficiency PEMFCs and electrolyzers. SOFC areas of emphasis include the capability to utilize CO/CO2 and methane fuels for power generation. Flywheel technology areas of interest are: system configuration concepts for high specific energy (>100Wh/kg for systems >500Whr and >50Wh/kg for systems <500Wh), and advanced vehicle integration, motor, and magnetic bearing control electronics. Flywheel Energy Storage development that addresses rotor concepts using advanced materials incorporating composite nanotubes that enable rotor specific energy >600 Wh/kg, and/or concepts that integrate energy storage, momentum storage, and spacecraft structure are sought. X3.03 Cryo and Thermal Management Lead Center: MSFC Participating Center(s): JSC, GSFC This subtopic includes technologies for waste heat management, movement, and rejection; technologies including lightweight and/or high-temperature radiators, heat pipes, heat sinks, etc. Also includes cryo-coolers and related low-temperature systems. These technologies will impact space solar power systems, spacesuits and habitation systems, robotics, and surface systems. Spaceport operations, both on Earth as well as extraterrestrial, are heavily dependent upon a wide range of cryogenic systems, including liquid oxygen, liquid nitrogen, liquid helium, and supercritical breathing air. Each above application has unique performance requirements that need to be met. Sizes of these systems range from the small (<20 for supercritical air and payload cooling) to very large (>3400 m3 for LOX and LH2 ground propellant storage). Advanced cryogenic technologies are being solicited for all these applications. Proposed technologies should offer enhanced safety, reliability, or economic efficiency over current state-of-the-art, or should feature enabling technologies to allow NASA to meet future space exploration goals. Technology focus areas are divided as follows: passive systems, storage and distribution components, refrigeration systems, advanced instrumentation, and advanced operational concepts. Cryogenic propellants such as hydrogen, methane, and oxygen are required for many current and future space missions. Operating efficiency and reliability of these cryogenic systems must be improved considering the launch environment, operations in a space environment, and system life, cost, and safety. Innovative concepts are requested for cryogenic insulation systems, fluid system components, and instrumentation. Although this subtopic solicits unique and innovative concepts in the cryogenic components and instrumentation areas, there is an emphasis at this time for: * Advanced thermal switches to isolate heat transfer from a de-powered cryocooler; * Advanced low-gravity submersible pumps designed specifically for moving cryogen heat that enters the tank wall to the heat exchanger coupled to the cryocooler; * Advanced tank support systems capable of supporting tanks during the launch environment, but decoupling on on-orbit to minimize thermal loads; * Advanced cryocoolers which are reliable, lightweight, and capable of removing significant heat at liquid hydrogen temperatures; * Low heat leak cryogenic quick disconnects capable of sealing against the vacuum of space; * Long-life, low power valves capable of sealing at cryogenic temperatures and being cycled many times without consuming pressurant gas; * Liquid acquisition devices capable of preventing gas ingestion into engine feed lines in low gravity; * Methods for cryogenic fluid acquisition and transfer in zero gravity; * Methods of determining liquid remaining in propellant tanks in low gravity; * High accuracy differential pressure transducers, which can be read submerged in liquid cryogen; * On-orbit leak detectors; * Lightweight, low-power temperature sensors which can be placed internally to the storage tank with a minimum number of feed-throughs; * New technology valves for cryogenic applications, including LOX, LH2 and Lhe, that minimize thermal losses and pressure drops. Components include shutoff and flow-control valves. Valves should be adaptable to electromechanical actuation and range in size from ˝ to 6 inches; * Integrated heat exchangers in large-scale storage systems designed to provide for zero boiloff and densification of liquid hydrogen and liquid oxygen; * Advanced low-temperature materials for cryogenic containment; * Insulation materials capable of retaining structural integrity while accommodating large operating temperatures ranging from cryogenic to elevated temperature conditions. Thermal management systems are needed for the rejection of heat to hot environments for daytime operations on the lunar surface, large space radiators to dissipate heat from power and propulsion systems, thermal control for mobile systems, cryogenic propellant storage and handling for in-space refueling, and long-term cryogen storage for propellant depots. Thermal management concepts include advanced heat sinks, heat pipes, and interface materials with high thermal conductivity that are electrically isolative. Innovative methods of increasing the specific thermal capacitance of the power systems are also sought: * Qualified heat pumps to reject heat to hot environments; * Multi-zone thermal control systems for spacesuits and mobile systems; * Lightweight deployable low temperature radiators for use on the lunar surface; * Concepts for the thermal management of advanced power system component designs for operation in deep space, lunar, and Martian environments. TOPIC: X4 Advanced Studies Concepts and Tools (ASCT) The goal of this topic is to develop ESR&T (Exploration Systems Research and Technology) tools that advance the SOA (State-Of-Art) for: the study of revolutionary exploration system advanced concepts, system technologies, and architectures; the prioritization of mission enabling technologies; systems engineering analysis, which reduces mission risk; systems design and analysis; and the conduct of exploratory research and development for emerging technologies. The projects to be selected are expected to challenge SBIR companies to take on research projects with higher technology development risk and higher potential payoff than they would, otherwise; and, in addition, are judged to be likely to provide new capabilities to meet NASA’s strategic goals and objectives for Exploration Systems. Projects must press the state-of-the-art, display a high degree of innovation, and involve significant technical challenges. Projects must be technically feasible, but the proposer should not assume that the lower the technical risk in a project, the greater the probability that it will be funded. Component-related, system-related, and process-related projects are all of interest. Subtopics of this ASCT topic area include: Technology Systems Analysis Tools – this subtopic includes the development of advanced tools to support: advanced concept analysis; systems architecture analysis; emerging systems technology analysis; technology portfolio assessment and forecast analysis; campaign analysis; technology databases; advanced concept development risk and cost modeling; etc. This subtopic encompasses support for technology road map definition. Systems Design and Analysis Tools – this subtopic includes the development of advanced tools for implementing: an advanced modeling and systems simulation environment; integrated analysis for assessing potential system engineering impacts of new technologies; design and analysis databases; system engineering models; engineering discipline analysis; system level risk analysis; probabilistic risk analysis (PRA); reliability, maintainability, and availability analyses; human factor analysis; life cycle cost analysis; and other systems engineering Figures of Merit (FOM) analyses. This ASCT topic is currently focusing on developing advanced tools, which enable the following: * Study of revolutionary exploration system advanced concepts, technologies, and architectures; * Exploratory research and technology in the full range of technical fields related to space exploration; * Integrated modeling and simulation of exploration systems and mission risk. X4.01 Technology Systems Analysis Lead Center: GRC Participating Center(s): JPL The goal of this subtopic is to develop new tools to ensure that advanced technology investments are guided by appropriate analyses. These analyses are needed in areas involving all of the various element programs within ESR&T. The analyses will support the definition of technology road maps for ESR&T. The scope of Technology Systems Analysis Tools includes the development of advanced tools to support technology systems analyses, such as: portfolio analysis; campaign analysis; system technology architecture impact analysis; advanced concept analysis; sensitivity analysis; verification and validation analysis; development cost analysis; and the population of advanced technology databases and information systems. The ASCT analyses planned will be performed using low-fidelity/high-level techniques. They will focus on entry level technologies and notional architectures. Higher fidelity assessments will be performed using ESMD (Exploration Systems Mission Directorate) Simulation Based Acquisition (SBA) resources. This Technology Systems Analysis Tools subtopic is currently focusing on developing advanced tools which enable the following: * Conducting exploratory research and development of emerging technologies and advanced concepts with high potential payoff; * Performing architecture, campaign, and technology analyses to identify and inform portfolio development for relevant exploration applications; * Technology analysis to identify and prioritize mission enabling technologies; * Architecture, mission, advanced concept, and technology risk analysis; * Technology databases, roadmaps, and portfolio development; * Exploration and implementation of different advanced concepts development methodologies and techniques to enable more effective and efficient study development; * Development of advanced concepts analyses and sensitivity analyses that can incorporate the full range of technical fields related to space exploration; * Analysis of advanced concepts, advanced technologies, and portfolio analysis; * Campaign analysis including the synthesis and analysis of many missions, architectures and competing capabilities and technologies against FOMs; * Technology analysis that identifies SOA and levels of performance metrics associated with cost- and risk-dependent chronologies (technology datasheets); * Advanced concept and system technology verification and validation; * Effective techniques for presenting tradeoffs and recommendations to decision-makers. X4.02 Design and Analysis Tools Lead Center: GSFC Participating Center(s): LaRC, ARC The goal of this subtopic is to maximize the credibility of the integrated systems analysis efforts being performed within ASCT by providing validated systems design, system analysis, and systems engineering tools. This will include the development of tools to produce: a modeling and simulation environment, design and analysis databases, system engineering models, engineering discipline analysis, parametric-based risk analysis, and probabilistic risk analysis (PRA), etc. This effort will closely coordinate with and support the development of the Simulation Based Acquisition (SBA) system in support of Exploration System Mission Directorate (ESMD) program acquisition and analysis. The scope of System Design and Analysis Tools includes tool development activities in the following areas: advanced systems simulation modeling environment; design and analysis databases and system models; performance and structural sizing; SBA advanced systems engineering tools for mid-technology level simulation and visualization of life cycle cost, risk, reliability, supply chain logistics, maintainability, availability, and other system engineering Figures of Merit. This subtopic is currently focusing on the following technology areas: * Systems engineering tools and discipline analysis tools in support of Simulation Based Acquisition. See ESMD-RQ-0025, ESMD-RQ-0026 and SBA Strategy in the Crew Exploration Vehicle Procurement Bidder's library (http://exploration.nasa.gov/acquisition/cev_procurement.html) for additional information. * Advanced engineering tools that integrate performance, risk, and cost modeling. * Development of system engineering tools that implement new analytical methodologies and techniques in support of both ESR&T and SBA activities. * Advanced systems simulation modeling environment that includes database technologies and data collection tools. * Seamless integration of design tools, modeling tools, simulation tools, and other systems engineering tools via standards-based software interoperability. * Novel approaches to assessing the performance, cost, or risk of proposed mission architectures. * Techniques for characterizing and optimizing investments in Modeling and Simulation. * Methods to extend and reuse models and simulations over the program lifecycle. * Model-based techniques for optimizing designs in distributed, multi-organization, multi-contract design teams. TOPIC: X5 Software, Intelligent Systems and Modeling This SBIR Topic seeks innovative concepts for technologies that will reduce life-cycle mission costs by providing high-confidence design of onboard autonomy, including safe and reliable human autonomy interaction. NASA is preparing for human-robotic exploration of the Moon and Mars. Traditional means of providing system information, such as inspections and preventive maintenance, have limited utility for exploration missions. Other solutions, such as telemetry data, become less useful as communication bandwidth shrinks and communication delays increase. Under these circumstances, increasing the autonomy of the onboard systems provides the best means of managing system operations. Autonomous onboard system technologies involve the use of goal-oriented operations, requiring means for sensing the environment and making intelligent choices with regard to resources, procedures, health and safety, logistics, and configuration. The Software, Intelligent Systems and Modeling (SISM) Element program will develop and test reliable software, autonomous and human-robotic systems, and model-based methods for design, analysis, and operations. SISM is being formulated in collaboration with several ESRT Technology Maturation Program elements (for example, Advanced Space Operations, Lunar and Planetary Surface Operations, and Advanced Space Platforms and Systems), as well as the Human-Systems Integration Program in HSRT. In addition, this Element Program is cognizant of on-going FY04 SBIR tasks in related areas, such as advanced modeling and simulation. To focus the role of this SBIR Topic within the overall scope of SISM, there will be an emphasis on concepts that reduce life-cycle costs by increasing the usability of key classes of advanced design methods and tools. The key classes of methods and tools are defined by the two subtopics, Software Engineering (X5.01) and Human-Autonomy Interaction (X5.02). These kinds of design and test technologies have made great advances during the past ten years, but the usability of the technologies, and therefore their actual impact, has lagged behind their potential impact. X5.01 Software Engineering Lead Center: ARC Participating Center(s): JSC, GSFC The objective of this subtopic is to bring to fruition software engineering technologies that enable engineers to cost-effectively develop and maintain NASA mission-critical software systems. Particular emphasis will be on software engineering technologies for sustaining engineering: achieving affordable reliability over successive spirals of mission software development, maintenance, and upgrades for Crew Exploration Vehicle and Project Constellation. A key requirement is that projects address the usability of software engineering technologies by NASA (including NASA contractors) engineers, and not only specialists. Many of the capabilities needed for successful human exploration of space will rely on software. In addition to traditional capabilities, such as GNC (guidance, navigation, and control) or C&DH (command and data handling), new capabilities are under development: integrated vehicle health management, autonomous vehicle-centered operations, automated mission operations, and mixed human-robotic teams to accomplish mission objectives. These capabilities will be needed in exploration spirals 2 and 3, including the extended lunar missions. Ensuring that these capabilities are reliable and can be developed and maintained affordably, will be challenging but critical to both the lunar missions and the subsequent Martian missions. Proposals should clearly indicate how the technology is expected to address the challenge of reliability and affordability. Mission phases that can be addressed include not only the software life-cycle (requirement engineering through verification and validation) but also upstream activities (e.g., simulation-based acquisition for software capabilities; mission planning that incorporates trade-space development of software-based capabilities) and post-deployment (e.g., new approaches for computing fault tolerance; rapid reconfiguration, and certification of mission-critical software systems). Software engineering tools and methods that address reliability for exploration missions are sought. Projects can address technology development and maturation that provide for the following and related capabilities: * Software-based radiation fault tolerance for computation; * Methods and tools for development and validation of autonomic software systems (systems that are self protecting and self healing); * Automated software generation methods from engineering models that are highly reliable; * Scalable verification technology for complex mission software, e.g., model-checking technology that addresses the ‘state explosion’ problem and static-analysis technology that addresses mission-critical properties at the system level; * Automated testing that ensures coverage targeted both at the system level and software level, such as model-based testing where test-case generation and test monitoring are done automatically from system-level models; * Technology for calibrating software-based simulators and test-beds against high-fidelity hardware-in-the loop test-beds in order to achieve dependable test coverage; and * Technology for verifying and validating autonomy capabilities including intelligent execution systems, model-based diagnosis, and adaptive control. A requirement for a sustainable and affordable human exploration presence in space is the need for modular, reusable elements and subsystems. Major subsystems (e.g., integrated vehicle health management) will present challenges in terms of software-based reconfigurability needed over a long sequence of missions. Projects can address technology development and maturation that provide for the following and related capabilities: * Software reuse for mission-critical, real-time applications; * Architectures that facilitate reconfiguration with upgraded components; * Affordable verification, validation, and certification of upgraded components and sub-systems within a system (or system-of systems) context; * Intelligent management of software assets; * Middleware that enables software platforms to migrate to new hardware platforms (e.g., middleware that enables command and control software to be transparently ported to distributed grid and cluster computer platforms). X5.02 Human Autonomy Interaction Lead Center: JSC Participating Center(s): ARC, GSFC Autonomous and automated operations will be required for systems fulfilling the Vision for Space Exploration. This subtopic addresses the need for modeling and analysis tools and technologies for design, test, and evaluation of human-autonomy interaction systems. The tools will support analyses of scenarios, tasks, information, and communication. They can validate and build confidence in human-autonomy interfaces and interaction support by identifying and mitigating risks (e.g., workload, situational awareness, and error). The technologies will interoperate with models and tools for design, evaluation, and certification of hardware and software systems, and will support understanding by engineers and planners who are not experts in human-system design or human factors. They will be cost-effective to use and be easily updated and reconfigured to reflect changes in designs and plans. The human-autonomy modeling and analysis technology will be applied to astronaut crew-autonomy and ground-crew-autonomy interactions in space missions. Autonomous systems can include exploration vehicles and subsystems, science stations, robots, robotic manipulators, rovers, and communications satellites. Autonomous operations can include rendezvous, proximity operations, mating of on-orbit elements, in-space assembly, maintenance, and robotic operations, including inspection, material transport, and sampling. These operations can be nominal, off-nominal, or contingency operations. Autonomy will be essential to ensure safe robot operation in the proximity of critical systems and humans. Autonomous functions can include science traverse and path planning, crew and resource scheduling, procedure execution, and control of subsystems such a power, thermal, propulsion, and communications. Innovative human-autonomy modeling and analysis technologies are needed to address unique challenges of space missions. These include multi-modal interfaces, asynchronous communication with long delays and long blackouts, unanticipated problems, and rare crew interactions by exception. Human-autonomy interactions can include supervisory control, communication, and coordination in shared planning and operations. They can include interactions to adapt, modify, and maintain systems to respond to emerging requirements and challenges. The interactions can also include dynamic control and adjustment of level of autonomy or supervision, type of coordination, and type of communication. This subtopic seeks projects that will demonstrate innovative technologies for use by engineering and operations teams for analyzing human-autonomy interactions and risks and for evaluating proposed mitigations of these risks, within the constraints of an affordable and timely mission design and planning process. TOPIC: X6 Advanced Space Operations (ASO) This Topic covers a range of key technology options associated with future space exploration systems and architectures that involve a variety of combinations of advanced robotic and human capabilities, ranging from remotely telesupervised robotic systems, through locally-teleoperated systems, to focused human presence (with robotic agent assistance). Technologies that enable in-space assembly, maintenance, and servicing are also included. Key objectives derive from the goals of safe/reliable, affordable, and effective future human and robotic space exploration in support of the U.S. Vision for Space Exploration. These efforts will be closely coordinated with spacecraft subsystem, system, and related R&D within the Advanced Space Platforms and Systems Topic. X6.01 Intelligent Operations Systems Lead Center: ARC Participating Center(s): JSC, MSFC The goal of this subtopic is to develop intelligent systems and technologies that could dramatically improve the affordability and productivity of long-duration human space operations, while preserving the high degree of safety and flexibility offered by state-of-the-art approaches. The current operations models used for the Space Shuttle and International Space Station, which require large ground teams continuously managing the daily operation of the spacecraft and the activities of the crew, are a major cost driver for these programs. As the human exploration campaign ventures farther into deep space, the communications time delays and longer-duration missions will require greater crew autonomy from Earth-based support. To achieve NASA’s exploration goals, technologies are needed that can enable a new paradigm for human space operations. Intelligent Planning and Execution Systems for Crew Autonomy Greater autonomy from Earth-based support implies that crewmembers will need to manage their exploration missions holistically. This will be possible only if automation helps the crew to integrate the complex interactions among many spacecraft subsystems efficiently and to manage and prioritize human and automated activities. Intelligent systems will need to be seamlessly integrated with operational procedures so that all the information required to make key decisions is continuously updated and presented to the crew in a rapidly comprehensible fashion. Crew interfaces (e.g., displays, voice recognition, etc.) will need to be intuitive and reliable. Validated, automated systems are needed that help a spacecraft/habitat crew coordinate and prioritize plans and execute nominal/off-nominal procedures in accordance with codified mission rules and objectives. These systems should improve upon capabilities already demonstrated in human space exploration missions (e.g., Space Shuttle and International Space Station). To evaluate proposed intelligent systems technologies, it is important to identify measurable performance objectives. Such performance measures include: (1) the speed and ease by which astronauts can plan and schedule future activities and understand the consequences of exercising various planning options; (2) the reliability, speed, and ease by which astronauts can maintain comprehensive situational awareness of a complex spacecraft/habitat without cognitive overload; (3) the reliability, speed, and ease by which astronauts can derive (on demand, or in response to detection, of an off-nominal condition) sufficiently detailed knowledge of the spacecraft/habitat, to issue commands that isolate anomalies, perform recovery procedures, and make other safety/mission-critical decisions. Modular designs that employ open architectures and interface standards are very important to assure cost-effectiveness and flexibility of intelligent operations systems. These architectures should promote extensibility/evolvability and accommodate future system upgrades. Such designs could include standalone tools that capture and manage corporate knowledge about manned spacecraft operations. Also of interest, though of lesser priority, are innovative technologies that can significantly enhance ground operational efficiency and performance. Intelligent Modular Training Systems Intelligent training systems are needed that enable flight crews to operate complex spacecraft safely and effectively, retain proficiency during long-duration missions, adapt easily to an evolving and expanding set of flight systems during the course of the exploration campaign, and achieve flight certification faster and more cost-efficiently than is possible with existing systems. Plug-and-play crew training systems that employ open architectures and interface standards are very important. These architectures should promote extensibility/evolvability and accommodate future system upgrades. The intelligent training systems should enable connectivity with models from various sources, with simulated or flight data (real-time and archived), with students and teachers at multiple locations, and with various platforms including ground-based/desktop environments and in-space, zero-g/partial-g portable or control station systems. When integrated with an operational environment, these systems must demonstrate effectiveness while ensuring that the performance of the vehicle or facility is unaffected. Focus should be on the following applications: * Intelligent onboard technologies for human space exploration; and * Intelligent human space exploration mission control technologies. Note: Related technologies of interest but covered under other SBIR subtopics include: * X5.01 Software Engineering; * X5.02 Human Autonomy Interaction; * X6.03 Launch Site Technologies (Launch site command and control system technologies); and * X8.01 Vehicle Health Management Systems. X6.02 Space Assembly Maintenance and Servicing Lead Center: GSFC Participating Center(s): JSC The goal of this subtopic is to develop technologies that enable reliable and affordable in-space assembly, maintenance, and servicing for human and robotic exploration missions in Earth orbit and beyond. Systems that enhance crew safety and mission reliability by automating these functions (whether robotically, tele-robotically, or with integrated human/robotic teams) are needed. Technologies that enable robust and reliable Earth-orbit assembly of spacecraft components (both modular and non-uniform), and thus alleviate the difficulties of launching larger, pre-integrated payloads, are of particular interest. Long-duration maintenance and servicing systems that are modular and generically applicable to a variety of orbital or transfer exploration spacecraft are also of interest. Focus should be on the following applications: * Earth-orbit assembly of large spacecraft systems (e.g. heat shields, propellant stages); * Autonomous inspection of spacecraft systems using either small free-flying inspection spacecraft or attached, highly-mobile inspection robots; and * Autonomous removal and replacement of failed spacecraft systems. Specific technologies of interest in addressing these challenges include: * Self-contained collision prevention/avoidance systems for robots (free-flying or attached) in close proximity to spacecraft, instruments, astronauts, etc.; * Dexterous robotic end-effectors/manipulators for robotic assembly and maintenance, including systems that accommodate instability between robotics and target surfaces; * Robotic non-destructive structural inspection technologies; * Advanced robotic control systems (e.g., systems that provide active damping of robotic arms to reduce un-commanded motion, high degree-of-freedom (DOF) systems, systems that function in multiple mission environments, and systems that incorporate intuitive man-machine interfaces and/or virtual reality simulation); * Robotic tele-operation control systems that accommodate latency and enable “real time” robotic operations; * Vision systems for both autonomous and tele-robotic operations, including systems that demonstrate: autonomous and rapid object recognition, affordable zoom/focus lens control, robust spatial perception of working environments, ability to operate under various lighting conditions, economical video compression and 3-D mapping techniques, and low power autonomous visual inspection systems; * Robotically operable structural/precision interface attachment systems; * Modeling of contact dynamics in zero gravity for capture and manipulation; * Test beds to validate robotic systems, including 6-DOF simulated weightless testing; and * Orbital mechanics optimization of libration point rendezvous for assembly and servicing. Note: Related technologies of interest but covered under other SBIR subtopics include: * Robot-mounted sensors for on-orbit assembly/construction (X1.03 Sensing and Imaging), and * Plug-and-play avionics and attachment technologies for autonomous rendezvous and docking (X8.02 Intelligent Modular Systems). X6.03 Launch Site Technologies Lead Center: KSC Participating Center(s): GSFC, MSFC The purpose of this subtopic is to develop technologies and concepts that will improve launch processing safety through the use of automated systems with limited human contact; make launch operations more cost- and time-efficient through standardization, commonality, and interoperability of launch systems and spaceport infrastructure; and improve the flexibility and adaptability of spaceport infrastructure in order to accommodate multiple vehicle types and diverse missions. Improvements in launch site operations can enable airport-like efficiencies at reduced cost and shortened processing turnaround time, thereby contributing significantly to the goal of a sustained and affordable space exploration program. Additionally, advanced launch operations technologies and concepts that may significantly improve launch vehicle specific energy or otherwise improve launch performance, affordability, and sustainability for space exploration missions are of interest. Topic areas that will be emphasized for improvements in launch site operations include: * Propellant handling systems: autonomous propellant loading; automated umbilicals; improved control of cryogenic mass loss; hazardous leak and flame detection; and improved cryogenic cooling, insulation, and sealing technologies; * Common integrated command and control system technologies for launch site operations: ground integrated health management systems, work control, configuration management, and other support systems; * Test equipment: universal avionics test equipment and automated and wireless built-in test equipment that reports launch vehicle and/or payload status; * Launch acoustic modeling and mitigation systems; and * Payload and launch vehicle systems handling equipment. Modular designs that employ open architectures and interface standards are very important to assure cost-effectiveness and flexibility of launch site technologies. These architectures should promote extensibility/evolvability and accommodate future system upgrades. Topic areas related to advanced launch operations technologies and concepts include: * Horizontal launch assist ground systems, including systems that preclude the need for vehicle take-off gear. Specific technology areas of interest include: vehicle acceleration mechanisms, vehicle structural support or levitation systems, control and stabilization systems, separation mechanisms, runway or track stability and maintenance systems, and energy storage and delivery systems; and * Other novel launch operations technologies and concepts. Focus should be on the following applications: * Earth-based launch site systems for human and robotic space exploration missions. Note: Related technologies of interest but covered under other SBIR subtopics include: * X6.01 Intelligent Operations Systems. TOPIC: X7 High Energy Space Systems (HESS) This Topic covers a range of key technology options associated with future space exploration systems and architectures that are ‘energy rich’—including high power space systems, highly efficient and reliable space propulsion systems, and the storage, management, and transfer of energy/propellants in space. It also addresses high-energy maneuvering including aero-entry, aero-braking, and other aero-assist related R&D. The affordable deployment of systems and logistics beyond low Earth orbit will depend on high-power space transportation. In addition, a broad range of future systems and technologies will be constrained or enabled by the availability (or lack) of significant power at an affordable cost. X7.01 Chemical Propulsion Systems and Modeling Lead Center: MSFC Participating Center(s): DFRC, GRC The goal of this subtopic is to develop innovative chemical propulsion systems and system concepts as well as modeling tools and capabilities that support chemical propulsion system design and analysis. Applications of interest include earth-to-orbit and in-space transportation, with a particular focus on versatile, multi-use in-space cryogenic engines with exceptionally high reliability, space-based reusability (i.e. capability for many restarts with little to no maintenance), and deep-throttling capability. These are needed for all phases of exploration missions, including trans-lunar injection, decent to the lunar surface, ascent to lunar orbit, and return to Earth. Also of interest are safe and affordable earth-to-orbit systems that enable high overall vehicle payload mass-to-liftoff mass ratios, with improvements in thrust-to-engine weight ratio, trajectory-averaged specific impulse, and overall reliability. Specific areas of interest for technology advancement and innovations include: * Propulsion system design concepts that address LOX/LH2, as well as LOX/CH4 and other LOX/Hydrocarbon engine and main propulsion systems integration issues; * Integrated chemical propulsion system concepts that integrate primary propulsion and reaction control system elements; * Design and analysis tools that significantly enhance the overall systems engineering evaluation of advanced chemical propulsion system concepts. These include tools for sensitivity analysis, quantification of system benefits to changes, propulsion system operability, "bottoms up" weight estimating, cost estimating, and reliability prediction for propulsion systems; * Manufacturing techniques that allow for significant reduction in the cost and schedule required to fabricate engine and main propulsion system components. These techniques can use current or emerging processes and manufacturing technologies to develop engine and main propulsion system components that will reduce complexity, increase reliability, and that are easier to assemble, install, and test when integrated onto the vehicle; * Concepts for solid or hybrid rockets that increase mass fraction, decrease the need for thermal insulation, and reduce or eliminate the need for staging; and * High-performance advanced propellants (as indicated by high specific impulse and high specific impulse density) and non-toxic propellants that can significantly improve safety and cost of propulsion systems operations. Note: Related technologies of interest but covered under other SBIR subtopics include: * X7.02 Chemical Propulsion Components * X8.01 Vehicle Health Management Systems X7.02 Chemical Propulsion Components Lead Center: MSFC Participating Center(s): GRC, JSC The goal of this subtopic is to develop innovative chemical propulsion component technologies that improve the safety, operability, reliability, and performance of propulsion systems required for human and robotic exploration missions. Components should be applicable to earth-to-orbit or long-duration in-space transportation systems (both primary propulsion and reaction control systems) for a variety of exploration mission phases, including trans-lunar injection, decent to the lunar surface, ascent to lunar orbit, and return to Earth. System masses will be critical in these far-reaching missions, dictating the use of lightweight components and the use of propellants harvested or manufactured on the surface of the Moon, Mars, or other destinations—an approach known as in situ resource utilization (ISRU). Candidate ISRU propellants include hydrogen, oxygen, carbon monoxide, carbon dioxide, methane, various other hydrocarbons, and compounds derived from these materials. In some scenarios, one propellant may be manufactured in situ while its oxidizer or fuel is brought from Earth. Because the use of ISRU propellants represents a departure from the state-of-the-art and from the existing base of engines and technologies, a new suite of propulsion system and component technologies will be required. These new in-space propulsion systems are expected to encounter conventional challenges such as regulator leakage, valve leakage, valve heating (on pulsing engines), solubility effects (such as combustion instabilities caused by gas bubble evolution in liquid propellants), and propellant acquisition (i.e., extracting gas-free propellant from the tank and delivering it to the engine). In-space chemical propulsion systems that incorporate long-term use of cryogenic propellants such as hydrogen, methane and oxygen present new challenges, including efficient, reliable, and durable propellant cryocooling, storage, acquisition (from tanks), transfer (through feed lines), gauging and flow measurement; however, these particular challenges are addressed by a separate sub-topic, X3.03 Cryo and Thermal Management. Chemical propulsion component technologies that demonstrate improved capabilities using a variety of propellant combinations are of interest, including: * Advanced turbopumps with wider throttle range and improved cavitation control, plus specific turbomachinery components such as bearings, turbines, and impellers that demonstrate greater reliability and lifetime; * Injectors with low thermal mass and long-duration reliability (e.g. for high duty-cycle attitude control thrusters); * Long-life combustion chambers (e.g., based on use of advanced materials); * Innovative thruster valve designs that tolerate high thermal loading due to heat soak-back during pulse mode operation; * Innovative concepts for fast acting valves to enable use of larger thrusters for small impulses (i.e. spacecraft fine pointing); * Highly-reliable long-duration seals; * Long-life, high-reliability ignition systems; * Lightweight, highly reliable gas compressors for pumping gaseous propellant into pressure vessels either in-flight or on a terrestrial surface; * Novel pressurization approaches that minimize dissolution of pressurant gas in storable propellants (e.g., nitrogen tetroxide, hydrazine, and hydrazine derivatives) * Novel concepts that increase performance or decrease mass of pressurization systems; * Development of advanced materials that exhibit high compatibility with gaseous oxygen; * Propulsion components based on microelectromechanical systems (MEMS) technology; * Advanced nozzle concepts for in-space propulsion systems; * Reaction control system thrusters that burn in situ and non-toxic propellants; * Innovative thruster designs that minimize or prevent high heat soak-back during pulse mode operation; * Highly reliable, lightweight compressors for use in gaseous propellant storage and distribution systems; * Advanced lightweight multi-use positive expulsion devices for storable propulsion systems; and * Other innovative chemical propulsion system components that improve system safety, affordability, or effectiveness. Note: Related technologies of interest but covered under other SBIR subtopics include: * X3.03 Cryo and Thermal Management * X7.01 Chemical Propulsion Systems and Modeling * X8.01 Vehicle Health Management Systems X7.03 High-Power Electric Propulsion Lead Center: GRC Participating Center(s): JPL, JSC The goal of this subtopic is to develop innovations in high-power (100 kW to MW-class) electric propulsion systems. High-power (high-thrust) electric propulsion may enable dramatic mass and cost savings for lunar and Mars cargo missions, including Earth escape and near-Earth space maneuvers. At very high power levels, electric propulsion may enable piloted exploration missions as well. Improved performance of propulsion systems that are integrated with associated power and thermal management systems and that exhibit minimal adverse spacecraft-thruster interaction effects are of interest. Innovations are sought that increase system efficiency, increase system and/or component life, increase system and/or component durability, reduce system and/or component mass, reduce system complexity, reduce development issues, or provide other definable benefits. Desired specific impulses range from a value of 2000 s for Earth-orbit transfers to over 6000 s for planetary missions. System efficiencies in excess of 50% and system lifetimes of at least 5 years are desired. Specific technologies of interest in addressing these challenges include: * Long-life, high-current cathodes (100,000 hours); * Electric propulsion designs employing fuels that are more readily available (whether from Earth or in situ space resources) and easy to store/handle; * Electrode thermal management technologies; * Innovative plasma neutralization concepts; * Metal propellant management systems and components; * Cathodes for metal propellants; * Low-mass, high-efficiency power electronics for RF and DC discharges; * Lightweight, low-cost, high-efficiency power processing units; * Low-voltage, high-temperature wire for electromagnets; * High-temperature permanent magnets and/or electromagnets; * Application of advanced materials for electrodes and wiring; * Highly accurate propellant control devices/schemes; * Miniature propellant flow meters; * Lightweight, long-life storage systems for krypton and/or hydrogen; * Fast-acting, very long-life valves and switches for pulsed inductive thrusters; * Superconducting magnets; * Lightweight thrust vector control for high-power thrusters; and * High fidelity methods of determining the thrust of ion, Hall, and advanced plasma engines without using conventional thrust-stands. Note: Related technologies of interest but covered under other SBIR subtopics include: * Low- to medium-power solar electric propulsion for planetary science missions (S8.04 Spacecraft Propulsion). X7.04 Aeroassist Systems Lead Center: JSC Participating Center(s): ARC, DFRC, LaRC The goal of this subtopic is to develop innovative human-rated aeroassist systems for missions including lunar return to Earth and precursor missions for human Mars exploration. Systems are needed to support the following flight regimes: aerocapture, entry interface to subsonic speeds, and Mach 5 to subsonic speeds. Systems must be capable of controlled flight and be compatible with pinpoint, soft landing systems, which achieve landing accuracies of 10s of meters at touchdown or powered descent initiation. These systems must be compatible with launch vehicles and transit vehicles and capable of safely discarding unneeded and constraining hardware on landing and providing surface access. Technology needs include aeroassist system design, Thermal Protection System (TPS) designs, modeling capabilities, sensor systems, and navigation technologies that support reliable aerocapture or aerobraking of multi-metric-ton-class piloted or cargo spacecraft. In particular, this subtopic seeks innovations in the following areas: * Innovative aeroassist system designs. This includes low-mass, rigid aeroassist systems based on robust, high-temperature structures and adhesives, modular or deployable/inflatable aeroshells with large surface area, and inflatable ballutes; * TPS designs for human-rated aeroassist vehicles returning to Earth from the Moon and Mars, and for Mars aerocapture and Entry, Descent and Landing (EDL). Innovative TPS concepts are solicited to reduce current TPS mass fractions by 25% to 50% and to reduce TPS costs; * Ablative and reusable TPS materials and concepts that significantly enhance performance and reduce mass. This includes development and characterization of single- and multi-use TPS materials, TPS for rigid aeroshells, and flexible TPS materials for deployable aeroshells. Thermo-chemical and mechanical properties data for probabilistic design, spallation characteristics, and accurate simulation tools to predict material behaviors and material compatibility are required. Innovative TPS concepts are solicited to reduce current TPS mass fractions by 25% to 50% and to reduce TPS costs; * Aerothermodynamic modeling tools with greater accuracy and less uncertainty: (1) Innovative and accurate computer modeling of fluid structure interactions, including flow stability and surface deflections under dynamic conditions for decelerator deployment and inflation; (2) Modeling and simulation of convection/radiation/ablation coupled three-dimensional flow fields, for both optically thick and thin shock layers and highly ionized flows; (3) Accurate prediction of wake heating including radiative heating components; (4) Accurate prediction of single and multiple rocket plume effects (e.g., reaction control system thrusters) on the vehicle aerodynamics and heating; * Innovative sensor systems which are capable of providing real-time or near real-time updates to atmospheric pressure, temperature, density, and winds to support the guidance systems used on aeroassist vehicles; * Innovative sensor systems for inflatable aeroassist vehicles capable of providing real time aerosurface temperature, strain, deflection, flight loads and other significant parameters; and * Lightweight flexible materials that will reduce the mass and increase the strength and thermal characteristics for applications to deployable aeroshells and supersonic deployed decelerators. Focus should be on aeroassist systems applied to the following mission classes: * Earth return of piloted spacecraft from the Moon. Return-to-Earth scenarios for human lunar missions include: (1) short-range direct entry and landing; (2) extended-range entry using a skip out of the atmosphere with subsequent EDL to the Earth’s surface; and (3) aerocapture into a low-energy Earth orbit followed by EDL. Inertial arrival speeds of approximately 11 km/s (up to 12 km/s for some abort scenarios) with entry masses of at least 5 metric tons are expected for normal lunar return. Acceptable sustained loads for these piloted missions are limited to about 5 gs perpendicular to the human spine in the “eye balls in” direction; and * Mars precursor missions for human exploration. These include robotic missions designed to deliver pre-deployed cargo or to conduct technology demonstrations in anticipation of follow-on human Mars missions. Candidate human mission scenarios for Mars include human and cargo aerocapture into a Mars orbit followed by EDL to the Mars surface and return to Earth. Mars aerocapture missions are expected to have arrival speeds of 6 to 8 km/s and aerocapture mass on the order of many 10s of metric tons. Return-to-Earth scenarios for human Mars missions are similar to those for lunar missions, except for higher arrival speeds (11.5 - 12.5 km/s, up to 14 km/s for some off-nominal scenarios). Note: Related technologies of interest but covered under other SBIR subtopics include: * Inflatable and other innovative structures (X2.02 Structures and Habitats); and * Aeroassist systems for deep space robotic science missions (S5.01 Low Thrust and Propellantless Propulsion Technologies). TOPIC: X8 Advanced Space Platforms and Systems This Topic covers a range of key technology options associated with future space exploration systems and architectures that are resilient, reliable, and reconfigurable through the use of miniaturization, modularization of key functions in novel systems approaches. Platforms technologies that support self-assembly and in-space assembly, as well as in-space maintenance and servicing, are included. These efforts are coordinated with in-space assembly and related R&D within the Advanced Space Operations Topic (e.g., involving extra-vehicular activity (EVA) systems, robotics, etc.). X8.01 Vehicle Health Management Systems Lead Center: ARC Participating Center(s): MSFC, JSC, SSC In order to meet the automation and autonomy requirements of the Vision for Space Exploration, innovative health management technologies are required throughout the system lifecycle including design, development, test, validation, integration, operation, maintenance, and disposition. Traditional means of supporting vehicle health such as invasive inspections are extremely limited in their utility for exploration missions. Other solutions such as ground-based monitoring of telemetry data become less useful as communication delays or bottlenecks increase. Under these circumstances, autonomous and automated solutions to systems health management provide the best means of increasing crew safety and mission success probability for future space exploration missions. Another significant concern is in mission operations. Operations models that require large numbers of ground controllers and other mission support staff will be cost prohibitive in the future. Future systems must provide appropriate levels of safety and mission success factors while reducing support staff on the ground. In addition, future space missions will have to maintain a healthy balance and seamless transition between crewed and robotic operations. Proposals should be responsive to the overall goals and objectives of the Exploration System-of-Systems as defined in Project Constellation requirements. Proposals may address specific vehicle health management capabilities required for exploration system elements (crewed spacecraft, launch systems, habitats, rovers, etc.). In addition, projects may focus on one or more relevant subsystems such as propulsion, structures, thermal protection systems, power, avionics, life support, and communications. Proposals that involve the use of existing NASA health management test beds (power, propulsion, systems integration, life support, diagnostics, networking, etc.) for technology validation are encouraged. Specific technical areas of interest related to vehicle health management systems include the following: * Methods and tools to enable concurrent design of system function and health management systems. These methods and tools should provide a means to optimize health management system design at the functional level to decide on failure detection methods, sensor types and locations, and identify additional functionality to safeguard against failures before costly design decisions have been made; * Health monitoring and management technologies to enable situational awareness of system health, safety, and margins. Solutions may include novel approaches to fault detection and isolation, diagnostics, and mitigation of system degradations and failures. Solutions may also include innovative health management system architectures that are robust to single point failures and are scalable, modular, and expandable without costly redesigns; * Methods for robust control of critical components, subsystems, and systems and robust execution of critical sequences during flight. Of special interest are robust recovery methods and innovative approaches to functional redundancy for the purpose of enhancing safety, availability, and maintainability; * System-of-systems health management concepts to provide robust cooperation of multiple Exploration elements, e.g., spacecraft constellations or rendezvous and docking operations; * Prognostic techniques able to anticipate system degradation and enable further improvements in mission success probability, operational effectiveness, human-machine teaming, and automated recovery of function; * Real-time data analysis methods for structural sensing, including detection, localization, damage assessment, and automated assessment of thermal protection system integrity; * Crew-automation interfaces that are capable of reporting quantitative/qualitative sensor readings, assessing system status, explaining current conditions, predicting likely system behaviors, and proposing corrective actions in a manner that does not exceed the capacity of human understanding, especially in high-risk situations requiring rapid human response. Innovative ways for the health management system to convey a wealth of information quickly and effectively are desired; and * End-to-end health management system architectures that are integrated with and validated on spacecraft subsystems on ground-based (or virtual) test beds. X8.02 Intelligent Modular Systems Lead Center: MSFC Participating Center(s): JSC, GSFC This subtopic will involve development and demonstration of a range of technologies for reconfigurable, intelligent, modular space subsystems, systems, and systems of systems. Technologies should focus on establishing the validity of new approaches to Earth-Moon human and robotic operations, with a view toward longer-term applications for the inner Solar System (e.g., Mars) exploration missions. Many of these future missions, systems, and capabilities imply the need for the development of large and complex systems and infrastructures in space. But, the size-constraints, mass-capability, and cost of launching large monolithic payloads into space limit the development and realization of these capabilities. If a different design approach using intelligent modular systems rather than monolithic payloads is used, these large space systems become more tractable. Also, intelligent modular systems include low system impact of a single launch vehicle loss, since modular systems are launched on multiple vehicles at multiple times. Replacement of modules over the system lifetime is, in many cases, a more reasonable approach to maintaining a system; and, graceful degradation of the system capability can be more readily managed with modular units. Hardware costs of multiple identical units can be reduced through economies of scale, and modular approaches can accommodate cost-phased programs that develop and fly a “pilot” system, which can initially prove a capability, and then be added to later as demand for capability increases. Technologies of interest include: Modular Structures (MSFC) Structural technologies of interest include inflatable, erectable, deployable, or easily connected modules to create large space structures. Assembly technology of interest may include approaches for integrating deployable modular units with larger structures such as habitation modules or propellant tanks, and approaches for assembly of erectable modules that form backbones or support trusses. Attachment technologies such as autonomous rendezvous and docking, innovative connectors and joining, bonding techniques, and module positioning and alignment systems are also of interest. Adaptable and Reconfigurable Modular Systems (GSFC) Integrated, reconfigurable modular systems incorporating multiple elements such as solar collection arrays, radiators, power, data, utility lines, science instruments, plug and play avionics, and integrated inspection and verification techniques are solicited, including modular structures using embedded sensors and actuators. Human-Robotic Modular Systems (JSC) Multi-functional robotic hardware and software systems are of interest to aide in surface and in-space operations. Robotic surface operations including exploration, assembly, fabrication, construction and transportation operations are of interest as well as similar systems for in-space operations. In addition, techniques are solicited for effective, efficient, and intuitive operation and control of robotic hardware through design and development of advanced human-computer interfaces. TOPIC: X9 Lunar and Planetary Surface Operations This Topic covers a range of key technology options associated with future lunar and planetary surface exploration and operations for a range of increasingly-ambitious human and robotic mission options through the development of in situ resource utilization technologies, highly-capable surface mobility systems, and various supporting infrastructures. Key objectives are derived from the goals of safe/reliable, affordable and effective future human and robotic lunar and planetary surface exploration in support of the U.S. Vision for Space Exploration. X9.01 In Situ Resource Utilization and Space Manufacturing Lead Center: JSC Participating Center(s): MSFC, GRC, KSC The goals of using resources that are available at the site of exploration and pursuing the philosophy of "living off the land” instead of bringing it all the way from Earth are to achieve a reduction in launch and delivered mass for exploration missions, a reduction in mission risk and cost, enable new missions not possible without in situ resource utilization (ISRU), and to expanded the human presence in space. Past studies have shown making propellants and other mission critical consumables (life support and power) in situ can significantly reduce mission mass and cost, and also enable new mission concepts (e.g., surface hoppers). Experience with the Mir and International Space Station, and the recent grounding of the Shuttle fleet, have highlighted the need for backup caches or independent life support consumable production capabilities, and a different paradigm for repair of failed hardware from the traditional orbital replacement unit (ORU) spares and replacement approach for future long duration missions. Lastly, for future astronauts to safely stay on the Moon or Mars for extended periods of time, surface construction and utility/infrastructure growth capabilities for items such as radiation protection, power generation, habitation space, and surface mobility will be required or the cost and risk of these missions will be prohibitive. However, before ISRU capabilities are incorporated into mission architectures, Earth and flight demonstrations of critical processes and systems will be required to validate performance goals and increase confidence in mission planners. Proposals for ISRU are requested in four subtopic areas: in situ Resource Extraction and Separation, in situ Resource Processing and Refining, Surface Manufacturing, and Surface Construction. Areas of interest for each of these four subtopic areas are defined below. Acceptable proposals can either address a single subtopic or can include concepts that encompass more then one subtopic into an integrated system. ISRU technologies or processes proposed for this subtopic must be shown to be beneficial compared to bringing everything from Earth. Proposals must also demonstrate an understanding of any past work, competing processes, and the current state-of-the-art with respect to the technology or process being proposed. To distinguish work supported under this subtopic from related work not using in situ resources, successful proposal must show some understanding of the native resource properties and the environmental conditions involved in their use. Proposals that can support future flight demonstrations of ISRU that are scalable to human mission requirements are encouraged, and point of departure mission information is provided below to help provide size and rate parameters for technologies and processes of interest. Proposals that support lunar ISRU applications or both lunar and Mars ISRU applications may be weighted higher then proposals that solely support Mars ISRU applications. In Situ Resource Extraction and Separation In situ Resource Extraction and Separation capabilities include resource characterization, prospecting, excavation, and delivery to resource processing units, and simple extraction and separation of desired resources from the bulk resource (including atmospheres). To be successfully implemented, in situ Resource Extraction and Separation proposals must minimize the mass which must be brought from the Earth, including the mass of the required power system and Earth-supplied processing consumables, and produce 100s of times their own mass of extracted resource in their useful lifetimes. These processes may also be required to operate in extreme temperature and abrasive environments, and in micro-g (asteroids, comets, Mars moons, etc.) or partial-g (e.g., Moon and Mars). In addition, the maintenance, human supervision, crew operation, and crew training required for process operation must be minimal and affordable. Specific areas of interest include: * Technologies, processes, and systems for robotic precursor and early human missions to the Moon in the areas of resource characterization, excavation and extraction of lunar resources (especially in the polar regions), and performing initial resource separation and collection of water, regolith volatiles, or feedstock for Surface Manufacturing, Surface Construction, or in situ Resource Processing; * Technologies, processes, and systems for robotic precursor missions to Mars in the areas of resource characterization, excavation and extraction of Mars resources, and performing initial resource separation and collection of atmospheric gases, regolith water/volatiles, or feedstock for in situ Resource Processing; and * Evaluation of granular physics in low gravity and development of models and its effect on material excavation and handling; and developing dust-insensitive excavation hardware, actuators, and bearings particularly for lunar resource extraction. In Situ Resource Processing and Refining The purpose of this subtopic is to identify and experimentally validate single and multi-step in situ Resource Processing and Refining units that have the potential for achieving the goals for ISRU stated previously. Such processes may include thermal, chemical, and electrical processing of extracted resources into useful products. In situ Processing and Refining includes efficient and economical production of propellants, fuel cell reagents, life support gases and water, manufacturing feedstock (such as silicon, aluminum, iron, and polymers) for use in Surface Manufacturing, and construction feedstock (concrete, wires, trusses, etc.) for use in Surface Construction from resources that have been extracted and separated using processes defined and developed under in situ Resource Excavation and Separation. To be successfully implemented, in situ Resource Processing and Refining proposals must minimize the mass which must be brought from the Earth, including the mass of the required power system and Earth-supplied processing consumables, and produce 100s to 1000s of times their own mass of product in their useful lifetimes. These processes may also be required to operate in extreme temperature and abrasive environments, and micro-g or partial-gravity. In addition, the maintenance, human supervision, crew operation, and crew training required for process operation must be minimal and affordable. Process evaluation metrics include: mass of product made per hour, final mass of product per mass of processor, Watts per mass of product produced per hour, percentage conversion of resources into product in single pass, and mass of Earth consumables used per mass of in situ product made. Specific areas of interest include: * Technologies, processes, and systems for robotic precursor and early human missions to the Moon in the areas of processing of lunar resources into oxygen, propellants, and feedstock for in situ manufacturing or surface construction; * Technologies, processes, and systems for robotic precursor missions or eventual human missions to Mars, which produce mission critical consumables, such as oxygen, propellants, life support gases, fuel cell reagents, and in situ manufacturing feedstock. Robotic and human missions to Mars that consider initial or evolutionary use of ISRU consumables currently assume the use of liquid oxygen and hydrocarbon fuel (methane, propane, methanol, ethanol, or low freezing point mixtures) propellants for propulsion systems and mobile fuel cell power systems; and * Developing and evaluating seals for high temperature multi-temperature and operation cycle regolith processors, water electrolysis and carbon dioxide electrolysis units; developing and evaluating low gas loss regolith inlet and outlet units (seals, augers, hoppers) for regolith processing; and developing and evaluating 0-g water separation, and separation of nitrogen from carbon dioxide are of particular interest for lunar and Mars resource processing. Surface Manufacturing w/In Situ Materials The purpose of the Surface Manufacturing element of the ISRU subtopic is to identify and experimentally validate capabilities that include production of sub-element and replacement components, assembly of complex products, and manufacturing support equipment to ensure parts/products manufactured meet required dimensions and specifications. Surface Manufacturing can use either in situ or Earth-supplied feedstock, however the long-term goal is to exclusively use in situ processed feedstock. Therefore, minimum requirements for process feedstock are advantageous to prevent excessive feedstock processing requirements (i.e., raw aluminum metal vs. specific aluminum alloy characteristics). For in situ manufacturing to be beneficial compared to bringing everything from Earth, some or all of the following attributes are required: ability to create wide variety of shapes and sizes, ability to utilize multiple feedstocks (plastic, metal, and ceramics), produce greater than its own mass of product and the mass of potential Earth supplied spares, operate in partial-g environments, and require a minimum of maintenance, human supervision, crew operation, and crew training. Specific areas of interest include: * Additive Manufacturing Techniques; * Subtractive Manufacturing Techniques; * Formative Manufacturing Techniques; and * Part Assembly/Integration. Manufacturing Support Processes Proposals that demonstrate manufacturing flexibility capabilities, such as part size, part complexity, and material feedstock for manufacturing while recognizing the mass, volume, and power limitations of future space habitats and delivery systems are highly encouraged. Surface Construction w/In Situ Materials The purpose of this subtopic is to identify and experimentally validate surface construction techniques that can be applied on the Moon and Mars for future human exploration missions. Early construction capabilities in the form of site preparation and shielding for lander plume debris, meteorites, and solar/galactic radiation can significantly reduce hardware and crew health concerns for missions exceeding several days and returning to the same site of exploration. Also, the ability to construct hardware bunkers, habitats, and power generation, management, and distribution capabilities is essential for mass efficient infrastructure growth on the Moon and Mars. These processes may also be required to operate in extreme temperature and abrasive environments, and micro-g or partial-gravity. Specific areas of interest include: * Construction techniques for robotic precursor and early human missions that support site planning and preparation and the use, manipulation, and placement of raw materials and expected feedstock materials from in situ Resource Processing and Refining for lander plume debris, meteorites, and solar/galactic radiation shielding; * Construction techniques for robotic precursor and early human missions that support bunker and habitat structure construction using and manipulating raw and expected feedstock; * Construction techniques that can be demonstrated on robotic precursor missions that demonstrate dust mitigation concepts for surface mobility around landing pads, habitats, dust-sensitive instruments, and airlocks; and * Lunar in situ fabrication techniques that can be demonstrated on robotic precursor missions that enable growth in solar power generation, storage, management, and distribution capabilities using raw materials, expected feedstock. Demonstrations can initially assume use of Earth supplied consumables in small amounts. Point of Departure Mission Information for Proposals For processing concepts that can be used on robotic precursor missions, payload masses (including rovers) are typically below 300 kilograms (kg). Robotic precursor concepts must demonstrate critical functions and must be scalable to human mission needs. Excavation and separation proposals must show supportability to future resource processing needs. Excavation, separation, and processing needs for lunar missions depend on the resource of interest, location, and concentration of the resource and the processing technology considered. Mars sample return missions that incorporate in situ propellant production require atmospheric carbon dioxide collection and possibly atmospheric or regolith water extraction to support the production of 300 kg to 2000 kg of propellant depending on the size of the sample and whether the mission is a Mars orbit rendezvous or direct Earth return mission. Breathing rates for astronauts are approximately 0.07 kg of oxygen (O2)/person/hour in habitats and 0.1 kg O2/person/hour for Extra-Vehicular Activities (EVAs). Early human lunar mission surface durations may vary from 3 to 45 days and can include from 2 to 6 crewmembers. Lunar human landers require approximately 5000 to 8000 kg of propellant for ascent and approximately 15,000 to 25,000 kg for landing and ascent combined. Mars mission surface durations are 30 to 90 days for opposition class missions and 450 to 600 days for conjunction class missions. Mars human ascent vehicles typically require 20,000 to 30,000 kg of propellant. Fuel cell reagent consumption rates depend on the power required for the application, the reagents, and the fuel cell technology used. EVA suits and small rovers can require 500W to 1 KW of power/hour, unpressurized rovers can require 3 to 6 KW of power/hour and pressurized rovers can require 10 KW/hour and above. X9.02 Surface Mobility/Mechanisms Lead Center: JPL Participating Center(s): GRC, JSC This subtopic seeks innovative mobility and mechanisms technologies for robotic systems, crew vehicles, and cargo systems for robotic lunar and Mars missions. Precursor Mobility Systems Precursor mobility systems address development of hardware and software mobility technologies for precursor lunar missions that also support missions to Mars. Topics include enabling technologies for modular robotic systems, alternative mobility systems, and the development of software to autonomously control and integrate mobility technologies. Mechanisms include traditional wheel motor and harmonic drives, distributed mechanical drives, traction drives, tracked drives, and walking mechanisms. Proposals may also focus on surface systems for autonomous robotic outposts. Emphasis is placed on the ability to test, verify, and validate such system prototypes in representative laboratory and field environments. The applicable technologies and design concepts span the full range of surface mobility including high dexterity robotic scouts, long-range navigation on the lunar surface, and robotic systems for structural construction, inspection and repair. This year, emphasis is placed on: 1) modular robotic systems and subsystems (mechanical and electrical), 2) assembly and control of modular systems, and 3) alternative mobility systems such as inflatable systems or tracked vehicles, and walking systems. Crew Mobility Systems We will also consider highly innovative mobility technology in specific support of crew and cargo vehicles. Proposals addressing this area should focus on space-relevant hardware, mobility options, crew transports over rough terrain, and logistical issues such as ingress/egress and loading/unloading. TOPIC: X10 Prometheus Technologies The primary goal of the Prometheus Nuclear Systems and Technology (PNS&T) Theme is to mature technology and develop systems to overcome current limitations of space power and propulsion in support of the Vision for Space Exploration. Developing and demonstrating safe and reliable nuclear fission-based spacecraft power and propulsion systems will enable human and robotic exploration, enhance scientific capabilities, and facilitate unprecedented levels of exploration and scientific return. Potential benefits of space nuclear power include very high total energy and total power capability, and high delta-V nuclear-electric propulsion that can enable a wide range of solar system exploration missions not possible today. To meet the goals of the Vision for Space Exploration, new exploration missions would have requirements exceeding what current power and propulsion systems can provide, particularly for surface and outer planet applications. Prometheus nuclear systems can provide a viable, enabling, alternative for those missions that have no other practical solution. The PNS&T Theme is comprised of two programs – the Nuclear Flight Systems program and the Advanced Systems and Technology program. The Nuclear Flight Systems program is focused on developing the first Prometheus demonstration of nuclear fission power in space, including development of nuclear reactor power, electric propulsion and other associated spacecraft systems. The Advanced Systems and Technology program is focused on conducting research and development of advanced systems and technologies beyond those needed for the first demonstration mission including research for advanced power and propulsion systems, materials development, integrated spacecraft systems, and other capabilities. This advanced technology development will be necessary to support NASA’s goal of more distant, more ambitious, and longer duration human and robotic exploration of Mars and other destinations. Five key program research areas include advanced nuclear electric propulsion, advanced fission-based power systems, advanced nuclear propulsion systems, advanced nuclear vehicle and spacecraft systems, and long-range nuclear reactor systems technology development. The five PNS&T subtopics are focused on these Advanced Systems and Technology program areas. X10.01 Long-Life Validation and Flight Qualification of Nuclear Space Systems Hardware Prior to Flight Use Lead Center: MSFC Participating Center(s): GRC Nuclear space systems are expected to be an integral part of the national Vision for Space Exploration. Nuclear electric power would allow human and robotic exploration to reach beyond the constraints of solar power systems and is expected to be crucial for long-duration habitation and exploration of the Moon and Mars. Nuclear propulsion systems offer the potential for significantly higher specific impulse and/or significantly higher delta-V than chemical engines, reducing the amount of propellant and associated costs needed to perform a given mission. Nuclear thermal propulsion (NTP) systems up to several hundred megawatts and nuclear electric propulsion (NEP) systems from 30 kW to hundreds of kilowatts and more, are being considered for the economical delivery of lunar and Mars cargo, rapid crew transit to Mars, and, in the case of nuclear electric propulsion, robotic exploration of the solar system and beyond. However, the long-duration performance and life testing of these high power nuclear space systems can be very expensive and poses several unique and significant challenges. The intent of this solicitation is to elicit new or significantly improved approaches that accelerate or simplify the long-life validation and flight qualification of high power nuclear space systems hardware. While the testing of nuclear reactors is clearly beyond the scope of this solicitation, proposals are invited for innovative methods that simplify, accelerate, reduce the cost, or otherwise improve upon current techniques to ground test and validate the life and performance of non-reactor high power space nuclear power and propulsion components, subsystems, and systems. Also invited are proposals that address new and innovative approaches to seamlessly integrate high power space nuclear power and propulsion hardware elements into complete systems of systems, with corresponding methods for flight qualification prior to flight use. Sample high power space nuclear power and propulsion areas that could benefit from accelerated or simplified performance and life validation include, but are not limited to: electric power conversion systems for in-space or planetary surface power; electric power management and distribution systems; accelerated testing of pulsed or steady-state high power electric thrusters or thruster arrays under appropriate vacuum and thermal conditions; performance and life testing of component materials and structures under simulated NTP hot hydrogen flows; the simulated operation, shut-down, and restart of NTP system components over simulated mission profiles in relevant vacuum, thermal, and radiation test environments; other space nuclear power and propulsion hardware elements that must operate in extreme environments over extended mission durations; and simplified or accelerated techniques for hardware integration and flight qualification of a complete system of systems prior to flight use. Proposed methods should substantially and demonstrably reduce the time and expense to validate the life and performance of space nuclear power and propulsion technologies compared to state of the art techniques. X10.02 Critical Technologies for In-Space Application of Nuclear Thermal Propulsion Lead Center: GRC Participating Center(s): MSFC, SSC NASA is interested in the development of critical technologies for first in-space applications of solid core nuclear thermal propulsion (NTP) systems for use in a variety of future exploration missions. For short, round trip, human missions to Mars, NTP systems may be enabling. It can potentially also help reduce launch mass or increase payload delivery for cargo and crewed missions to the Moon and other destinations. The first anticipated in-space application of solid core NTP systems could occur in the time frame of 2025 to 2030 and could be based on a high-thrust/high-Isp (~850 – 950s) NTP system that uses a fission reactor with U-235 fuel as its source of thermal energy. During the short primary propulsion maneuvers of a typical conceptual mission, large quantities of thermal power (100s of MWt) would be produced within the NTP system and removed using LH2 propellant that is pumped through the engine’s reactor core. The superheated hydrogen gas is then exhausted out the engine’s nozzle to generate thrust. Recent NASA studies have shown that small engines (~15-25 klbf), used individually or in clusters, could support a broad range of mission types. Representative ranges of engine performance include: 1) hydrogen exhaust temperatures ~2500-2900 K; 2) propellant flow rates ~7-13 kg/s; 3) chamber pressures ~500 –1500 psi ; and 4) nozzle expansion area ratio ~200:1-500:1. Proposals are sought to further improve safety, performance, reliability, and life factors as well as reduce projected weight and costs for the first in-space NTP systems, subsystems, and components beyond that in previously achieved ground test systems. Proposals are solicited in the following key technology/concept areas: * High temperature, radiation tolerant instrumentation and avionics for engine health monitoring. Non-invasive designs for measuring neutron flux (outside of reactor), chamber temperature, operating pressure, and H2 propellant flow rates over wide range of temperatures are desired; * Long-life, lightweight, reliable hydrogen turbopump designs and technologies; * Lightweight, long-life, high heat flux thrust chambers, regenerative-cooled nozzles and radiation–cooled skirt extensions that are compatible with hot hydrogen; * Radiation tolerant materials compatible with above engine subsystem applications and operating environments; * High temperature, low-to-moderate burn-up carbon- and ceramic-metallic (cermet)-based nuclear fuels for use in NTR and BNTR engines; * Improved chemical vapor deposition (CVD)/coating techniques for heritage “Rover/NERVA” type carbon-based fuels that reduce and/or prevent cracking, fuel element erosion via H2 attack, and release of fission product gases into the engine’s H2 exhaust stream; * Mass-optimum neutron and gamma radiation shielding materials and designs that minimize exposure/damage to key engine components and subsystems (e.g., LH2 turbopumps) and provide radiation protection for the crew; and * Dual-use shielding materials and designs that also provide habitat protection against galactic cosmic rays and solar flares are also encouraged. Note that any associated NTP simplified test approaches, power systems, and thermal management/heat rejection systems technologies should be submitted to subtopic areas X10.01, X10.03, and X10.04, respectively. X10.03 Critical Technologies for Space-Based Nuclear Fission Power Systems Lead Center: GRC Participating Center(s): JPL, MSFC, JSC NASA is interested in the development of highly advanced systems, subsystems, and components for use with high-power, fission power systems for a variety of future robotic and manned exploration missions to the Moon, Mars, and beyond. Anticipated electric power levels range from 30 to 100s of kilowatts for the nearer-term and possibly up to multi-megawatts for the far-term. Fission-based systems are anticipated to enable long duration stays of approximately 45 to 90 days over the lunar night and may have in situ resource utilization applications. Power levels needs are anticipated to be between 30-50 kWe for these early exploration missions. Potential Mars-surface human outpost applications for high-power space nuclear power systems could include habitats, resource processing, propellant production/liquefaction/maintenance, and excavating and mining equipment. These potential Mars surface human mission activities could require power in the 100 kWe range. Also, space nuclear power systems could be needed for robotic outposts as a precursor to human Mars surface exploration with 50-500 day stays. Power levels of about 30-50 kWe may be needed to support these initial robotic outposts and other science applications such as: deep drilling, resource production demonstrations, rovers, weather stations, etc. Potential electric propulsion applications include high power space nuclear power systems for primary electric propulsion, vehicle housekeeping, cryogenic propellant maintenance, orbiting power assets and science payloads. Power levels in the 100-200 kWe range are envisioned for robotic vehicles. Far-term vehicles for human missions may also be needed and could require about 1-2 MWe for high-mass cargo vehicles to the Moon or Mars and the low 10s of MWe for piloted electric propulsion vehicles. Nuclear thermal propulsion systems could also be designed to produce electric power and power levels of about 50 kWe could be needed to meet crew habitat, propellant boil-off, and other spacecraft power requirements. Proposals are sought in the following specific technologies areas: * Advanced, high-efficiency, high-temperature high-power conversion >20%, 30-200 kWe for the nearer-term, and up to MWe-unit size for the far-term (with technical issues of scaling to high power unit); * Electrical power management, control and distribution in the 1000-5000 V range; * Deployment systems/mechanisms and innovative methodologies for surface mobility systems for remote emplacement of power systems and for use of indigenous shielding materials; * Material compatibility with local environments; * Systems/technologies to mitigate lunar and planetary surface environments including dust accumulation, lunar surface temperature extremes, wind, planetary atmospheres (CO2, corrosive soils, etc.); * Power system design considerations for long life (>10 years), autonomous control and operation, including sensor technologies; and * Radiation tolerant systems and materials (including lunar, Mars and in-space environments) for robust, long-life operation. In addition to reducing overall system mass, volume and cost, increased safety, and reliability are of extreme importance. It is envisioned that these high power space nuclear power system technologies could be used on robotic and human exploration missions and it is to NASA’s advantage to develop those technologies that evolve from robotic to human exploration mission requirements with a minimum of redesign. Technologies that enable challenging missions such as, nuclear electric propulsion, planetary surface power, and in-space electric power generation are of particular interest. Technologies that easily and efficiently scale in power output and can be used in a host of applications (high commonality) are desired. Proposals for thermal management systems and innovative materials computational engineering should be proposed to X10.04 and X10.05, respectively. X10.04 Heat Rejection Technologies for Nuclear Systems Lead Center: GRC Participating Center(s): GSFC, JPL, MSFC NASA is interested in the development of advanced heat rejection subsystems for use with high-power, fission-based power and propulsion systems for a variety of future robotic and manned exploration missions to the Moon, Mars, and beyond. Anticipated electric power levels for these high-power, space nuclear systems could range from 30 to 100s of kilowatts for the nearer-term and possibly up to multi-megawatts (2-20 MWe) for the far-term. Potential applications include in-space transfer vehicles and planetary orbiters, and surface bases with global site capability on the lunar and Mars surface. The heat rejection sub-systems for any of the possible high power space nuclear power plant choices would need to be matched with the thermodynamic cycles of the power plants in a manner that will maximize space nuclear power system performance while keeping heat rejection subsystem and overall power system specific mass (kg/kW) to a minimum. The levels of heat rejection could be from about 100 kilowatts to many megawatts, and the task could be even more challenging by the long life requirements imposed by deep space missions, the extreme radiation environments possibly encountered, and the unique challenges imposed by surface missions including the effect of an atmosphere, elevated sink temperature, and particle contamination. The radiator operating temperature range can vary greatly depending on the mission, but temperatures as low as 400K and in excess of 1000K are possible. Typical heat rejection systems usually include a) a heat transport loop carrying heat to radiator surfaces for rejection to space, and b) a space radiator, which accomplishes the final heat rejection to space by thermal radiation. If the cycle working fluid is different from the radiator heat transport fluid, a “heat sink” heat exchanger and a fluid-circulating pump also need to be included in the design. Proposals are sought in the following critical technologies areas: * Low areal density heat rejection radiators (<5 kg/m2); * Innovative heat transfer approaches between heat transport loop and radiating surfaces; * Development of light weight, radiation tolerant, thermally stable, high-performance components and pump loop systems including heat pipes and pumps in the low to intermediate temperature ranges (300K to 500K), intermediate temperature ranges (450K to 650K), and intermediate to high temperature ranges (700K to 1000K and higher); * Pumped loops that take advantage of the abundance of waste heat and transport some of it to the spacecraft and payload components for thermal management. Waste heat source to spacecraft radiator distances will likely be too large for passive technologies, and pumped loops may offer a possible solution. Since rejection of megawatts of waste heat could require large radiating surfaces, loop heat pipes may provide a lightweight solution to distributing this heat over long distances. Specific areas of interest for this area include: - Long term material/working fluid compatibility, lightweight material integration, and working fluid performance for the various temperature ranges; and - High temperature, long-life pump technology, single- and two-phase systems, and thermal bus concepts involving multi-evaporators and condensers. * High temperature, lightweight heat rejection system materials. Such materials may include those to enable lightweight radiators and heat pipes. Work in this area should address harsh radiation environments, launch/landing loads, and long life issues; * Durable low-absorptivity/high-emissivity and variable emissivity coatings for radiating surfaces; * Novel and efficient deployment systems/mechanisms for radiators in zero gravity and/or non-zero gravity fields to minimize mass, complexity, and stowed area/volume; * Systems and technologies to mitigate adverse effects of planetary surface operating environments, such as cosmic and fission process induced radiation, dust accumulation, wind loading, planetary atmospheric effects due to CO2, and variable sink temperatures; * Design considerations for heat rejection subsystems should include long service life (>10 years) and autonomous operation; * Development of advanced, high temperature heat pump technologies based upon conventional vapor compression cycles, absorption/adsorption cycles, and advanced thermoelectric and/or thermo-acoustic technologies; * Advanced eutectic working fluids capable of extended duration use that would mitigate design issues related to the freezing and subsequent reuse of thermal management coolants; and * Alternate cooling technologies for the rejection of waste heat from large capacity planetary or surface nuclear power systems. Such systems may include, but are not limited to, deployable cooling towers and/or optimized radiators. In addition to reducing overall system mass, volume, radiator area, and cost, increased safety and reliability are of prime importance. Technologies are desired that readily scale in heat rejection capability for various power plant outputs, and thus can be used in a range of applications. X10.05 Computational Material Science Tools for Space Nuclear Design Systems Lead Center: GRC Participating Center(s): MSFC NASA is interested in the development of highly advanced systems, subsystems, and components for use with high-power, fission power and propulsion systems for a variety of future robotic and manned exploration missions, including in-space, lunar-surface, and Mars-surface applications. Advanced high-power space nuclear power and propulsion systems for robotic and human exploration missions involve a range of specialized materials for the reactor, heat transfer system, energy conversion system, propulsion system, and other nuclear vehicle systems. These materials may include carbon-carbon, super alloys, refractory alloys, structural ceramics, ceramic matrix composites, and other high-temperature space nuclear systems materials. Long-term stability greater than 10 years is critical for long-life space nuclear power system applications. Materials would be subjected to fission process radiation while exposed to in-space (plasma, out-gassing, etc.) and/or planetary operating environments. This subtopic is focused on the development of computational materials science tools to develop and select these specialized space nuclear systems materials. Many considerations go into selection of materials for demanding applications. These include strength, creep resistance, phase stability, oxidation/corrosion resistance, nuclear capture cross-section, and radiation tolerance. In recent years computational materials science has assisted with not only the selection of existing materials with a given set of properties but also with the development of new materials with those properties. These tools include first principles calculations of phase equilibria, computational thermodynamics (the CALPHAD technique), and creep modeling. Proposals are sought for the specific technologies areas: * A computational ‘toolbox’ for material selection with particular emphasis on space nuclear power and propulsion systems requirements; * Computational tools to address particular issues in mechanical property degradation in space nuclear power and propulsion systems over long times. This includes, but is not limited to, long-term creep modeling; * Computational tools to predict long-term oxidation/corrosion and flow-induced erosion issues in the high temperature portions of these systems, including the heat transfer system. This includes thermodynamic modeling of heat transfer media attack of alloys; * Computational tools to predict long term stability of various joining techniques used in these space nuclear systems. This includes diffusion modeling in alloys; and * Computational tools to predict interaction of the radiation environment. This includes effective capture cross-section for complex materials systems and production of secondary energy and potential impact on components. It is anticipated that Phase 1 will focus primarily on the new computational tools for material selection and development with some limited experimental verification. Later phases should involve more extensive verification, to the point where these tools could be readily utilized for the design of space nuclear systems. TOPIC: X11 Human Systems Research and Technology The crews that leave the Earth for exploration destinations must keep healthy to perform their mission and to return safely back to Earth. The subtopics seek innovative technologies that will enable crew health and performance, and that will assure there will be no unacceptably long-term consequences after returning while supporting healthy and productive sustained human presence. Proposals for technologies that will enable human space exploration are sought in the areas of Radiation Health and Radiation Shielding; Human Health Countermeasures including artificial gravity, exercise, pharmacology and nutrition, cell and tissue-based analog systems, and physiological countermeasures; Exploration Biology, including the science, spaceflight systems, and technologies that support human exploration; Autonomous Medical Care including technologies of prevention, monitoring, diagnosis, and treatment of human medical problems. Research should be conducted to demonstrate technical feasibility during the Phase 1 contract and show a path toward a Phase 2 specific deliverable. The contractor will then, when appropriate, deliver a demonstration unit of the instrumentation for NASA testing before the completion of the Phase 2 contract. X11.01 Radiation Health Lead Center: JSC Participating Center(s): ARC, LaRC, MSFC The goal of the NASA Space Radiation Research Program is to assure that we can safely live and work in the space radiation environment, anywhere, any time. Space radiation is distinct from terrestrial forms of radiation, being comprised of high-energy protons and heavy ions and their secondaries produced in shielding and tissue. The Radiation Program Element uses the NASA Research Announcement as a primary means of soliciting research to reduce the uncertainties in risk projections; however, there are specific areas where the SBIR technologies can potentially contribute to NASA’s overall goal: Ground-Based Heavy Ion Accelerator Research Support Equipment NASA utilizes facilities at Brookhaven National Laboratory (BNL) to conduct fundamental radiobiology and shielding experiments. However, the facilities at BNL were not developed with NASA’s high number of investigators in mind, thus there are areas where technology developments can improve efficiency and throughput. Technologies of specific interest include, but are not limited to, the following: * Advanced animal support equipment, sample holders, live imaging of samples on the beam line during heavy ion irradiation, or specimen transport systems that allow remote transport into and out of the target areas, and precise positioning of specimens in the beam line with minimal human interaction in the target areas; * Environmental control for cell studies while in the beam line and automated fixation capabilities to perfuse small cell and tissue samples directly after exposure to the ion beam; * Controlled beam line access that provides safe, but rapid and reliable human access to the beam target areas and lockout during specimen exposure; and * Advanced detector systems to provide rapid assessments of elemental fluence spectra and neutron fluence spectra following heavy ion irradiation of biological or shielding samples. High Throughput Genomic Analysis Techniques Following low-dose irradiation of cells by protons and heavy ions, damage is localized to only a very few cells. The ability to separate cells with or without genetic changes in an automated manner is of interest. Current technologies are inefficient in identifying small-scale genetic changes (less than several thousand base-pairs (Mbp)) under these conditions. Technologies of interest are: * Complementary technologies to the fluorescence in situ hybridization (FISH) method used to score large scale (>1 Mbp) genetic changes to chromosomes following low dose irradiation in order to rapidly score small-scale genetic changes (<1 Mbp); and * Imaging techniques to rapidly identify with high accuracy undamaged cells from a cell population irradiated at low doses. Radiation Shielding and Fabrication The NASA Space Radiation Research Program uses the NASA Research Announcement (NRA) as the primary means of soliciting research to conceive and radiation-test new radiation shielding materials concepts. The materials concepts include new and innovative lightweight radiation shielding materials to shield humans in crew exploration vehicles, large space structures such as space stations, orbiters, landers, rovers, habitats, and spacesuits. The materials emphasis is on non-parasitic radiation shielding materials, or multifunctional materials, where one of the functions is the radiation shielding, but also serves as structural and other functional components of flight and/or habitat systems. The specific areas in which SBIR-developed technologies can contribute to NASA’s overall mission requirements for advanced radiation shielding materials technologies are: * Characterization of the physical, chemical and relevant functional properties and the validation and qualification of such multi-functional radiation shielding materials; * New and innovative manufacturing techniques for producing quality-controlled advanced radiation shielding products and structural components, including innovative scale-up methods for producing quality-controlled viable quantities of advanced radiation shielding materials; * New and innovative processing methods for producing quality-controlled advanced radiation shielding materials of all forms - resins, fibers, fabrics, composites and fiber-reinforced composite materials; * New and innovative fabrication techniques for fabricating advanced radiation shielding materials into useful products and structural components; and * New and innovative commercialization strategies to introduce advanced radiation shielding materials technologies into the marketplace to enable availability of the technologies for use by NASA and the space exploration community. Reliable Radiation Dosimeters for Manned and Unmanned Spaceflight Current environment dosimeters have exceeded their designed lifetimes and should be replaced. These include small, active dosimeters to monitor individual astronauts’ exposure, Tissue Equivalent Proportional Counters (TEPC), Charged Particle Directional Spectrometer (CPDS) capable of internal and external deployment, and externally deployed electron and neutron detectors. New software needs to be fault tolerant and updated to current operating systems; new hardware and software must be fully documented (schematics, etc.). Areas of interest are: * Advanced spaceflight detector systems to provide reliable environment data for a specific spectrum of energies, including: real time dosimetry providing dose and particle types and energies and cumulative dosimeters for characterizing space environments for use onboard spacecraft and planetary surfaces as well as alarm systems for Solar Particle Events; and * Microdosimetry for operational and research applications, including implantable dosimeters for biological studies, that translate particle counts into biologically relevant dose or damage. X11.02 Human Health Countermeasures Lead Center: JSC Participating Center(s): ARC, GRC, MSFC In order for humans to live and function safely and efficiently in space or in the hypogravity of the Moon (1/6g) or Mars (3/8g), a good understanding of the effects of micro- and hypogravity and other factors associated with the space environment on human physiology and human responses to the space and extra planetary environments is required. A variety of countermeasures must be developed to oppose the deleterious changes that occur in space and upon subsequent exposure to other gravitational fields. The ability to monitor the effectiveness of countermeasures and alterations in human physiology during space exploration missions, particularly when several countermeasures are used concurrently, is equally important. This subtopic seeks innovative technologies in several very specific key areas. Since launch costs relate directly to mass and volume, instruments and sensors must be small and lightweight with an emphasis on multi-functional capabilities. Low power consumption is a major factor, as are design enhancements to improve the operation, design reliability, and maintainability of these instruments in the environment of space and on planetary surfaces. As the efficient use of time is extremely important, innovative instrumentation setup, ease of usage, improved astronaut (patient) comfort, noninvasive sensors, and easy-to-read information displays are also very important considerations. Extended shelf life and ambient storage conditions of consumables are also key necessities. Ability to operate in 0g, 1/6g, and 3/8g becomes more important as we march towards human Moon and Mars missions. Exercise and Related Hardware Development of an immersive visual display system is required to be interfaced with treadmill exercise devices. This system may not be head-mounted but could be free standing and provide at least a 180° field of view. This visual display would allow visual flow patterns to be displayed to a non-encumbered subject during in-flight or on-surface treadmill exercise. In addition, miniaturized exercise hardware (treadmill or resistance exercise); physiological monitoring devices; and metabolic gas (carbon dioxide and oxygen) analysis systems for use with exercise and miniaturized interactive feedback and entertainment systems. A tool or toolkit should simulate and visualize the exercise device design and performance. A comprehensive, scaled 3D/virtual human model interface would be valuable to show biomechanical and kinetic effects of the exercise device. Relative physiological data from anthropometry to stress/fatigue to trauma/insult onset should be targeted. If in-flight/on-orbit micro gravitational and planetary surface gravitational forces can be simulated, this could help produce germane simulations with which to implement new designs and products. A time-delay algorithm would be advantageous in helping provide for latency-moderated haptics (force-feedback) and long-distance teleoperative control. This will allow remote teleoperation with force-feedback despite the high latencies involved. Noninvasive Pharmacotherapy and Monitoring Development of innovative technologies resulting in noninvasive methods for diagnosis, treatment, and therapeutic drug monitoring is needed to facilitate effective pharmacotherapy of humans in space. Many questions remain about the effectiveness of pharmaceuticals in micro- and hypo-gravity environments, which may interfere with their activity by sensitizing or desensitizing the crewmember or interfering in other ways with the desired physiological effect. Micro-encapsulation of drugs, radio contrast agents, crystals, and development of novel drug delivery systems wherein immiscible liquid interactions, electrostatic coating methods, and drug release kinetics from microcapsules or liposomes can be altered under microgravity. Devices for continual monitoring of physiology during pharmacotherapy would also be advantageous to ensure that on-orbit expression of therapies relates to on-Earth histories. Device for Providing Increased Neuromuscular Activation during Spaceflight Astronauts returning from spaceflight exhibit post-flight postural and gait instabilities that are a result of neural adaptation to microgravity. A small, lightweight countermeasure device is required to stimulate somatosensory receptors on the plantar surface of the feet during in-flight exercise with the goal of increasing neuromuscular activation and enhancing sensorimotor integration. This system would integrate with in-flight exercise hardware and coupled with visual stimulation systems would allow a more complete sense of immersion to enhance in-flight postural and locomotor training. Device for Measuring Body Fluid Shift A body impedance device to measure fluid shifts in four segments of the body associated with a short-radius centrifuge. The device should measure the following parameters, namely, resistance, change in resistance and rate of change of resistance and reactance. The device should withstand g forces (5g) produced by centrifugation and meet safety standards such as subject isolation. MEMS-Based Human Blood Cell Analyzer Development of a small, automated and micro- and hypo-gravity capable instrument that will analyze micro liter quantity of human whole blood and provide a complete blood cell count (RBC, WBC, platelet, hemoglobin concentration, hematocrit, WBC differential, and calculated RBC indices) that correlates with traditional ground-based impedance or light-scattering technologies is needed. Likely devices based on MEMS will employ a biocompatible combination of micro fluidics, micromechanics, micro-optics, microelectronics, and data telemetry capabilities in an integrated handheld package with a user-friendly operator interface. Cell/Tissue Analog Studies Cell/Tissue analog studies in ground-based, microgravity-analog bioreactors allow us to understand the ill-effects of microgravity and radiation on human tissues—especially, bone, muscle, and cardiac and immune response. Technologies that allow automated biosampling, lyophilization of mammalian cells, miniaturized protein microarray analyzer, tools derived from Bionanotechnology relevant to the understanding are of interest. X11.03 Autonomous Medical Care Lead Center: JSC Participating Center(s): ARC, GRC Exploration missions require a healthy, well-performing crew supported by a robust infrastructure for the monitoring, diagnosis, and treatment of medical conditions. Since return time to Earth and communications delays during such missions will greatly reduce the effectiveness of Earth-involvement, the crew must be capable of performing the majority of medical activities independently. Therefore, this system of autonomous medical care must provide the capability for patient care as well as measure and assess fitness levels for duty during a mission with little or no real-time support from Earth. The objective of this subtopic is to sponsor applied research leading to the development of such an infrastructure with the associated medical devices and procedures that will mitigate crew health, safety, and performance risks during future flight missions to the Moon and Mars. Medical diagnostic, treatment, and monitoring devices are critical for providing health care and medical intervention during missions, particularly extended-duration spaceflight to the Moon and Mars. Of particular interest are devices with minimized mass, volume, consumables, and power consumption that are capable of multiple functions in both micro-g and sub-g environments. Design enhancements that improve the operation, reliability, flexibility, and maintainability of medical devices in the space environment are also sought. Additional considerations include innovative approaches to human-device interactivity and interface, automation of device functions, improved ease of use, and astronaut comfort. Device for Body Chemistry Assessment Development of an integrated, adaptable laboratory analysis system/sensor system for in-flight assessment of body fluids (including blood) and solids is desired. This system would be used to obtain quantitative measurement of dissolved gases, calcium ions, and other electrolytes, proteins, lipids, hormones, carbohydrates, vitamins, minerals and clinical drug levels with minimal or no consumables usage or specimen preparation skill. Likely candidates will be based on MEMS technology and will employ a biocompatible combination of micro fluidics, micromechanics, micro-optics, microelectronics, and data telemetry capabilities in an integrated handheld package with a user-friendly operator interface. Voice- and Gesture-Actuated Interactive Procedures Astronauts working in space or on the lunar or Martian surface will require a hands-free, interactive, step-by-step environment for performing flight medical procedures. This system should have the capability to utilize links, prepare textual or graphical indication of progress through a procedure, return to previous steps, page forward/page backward, and automatically annotate verbal input relative to subject response during procedure or treatment. An inventory capability must exist for obtaining and stowing required items (including medications) as well as a mechanism to assess the resulting consumables status after a procedure has been completed. Ground-monitoring capability is also required, at least in the early stages. Closed Loop Medical Respirator A closed loop flight and human certified medical respirator with real-time remote monitoring and remote control capability is required. This respirator must incorporate a function to limit the amount of O2 leaking into the space vehicle or surface habitat. Current O2 limits range from ~20/21% at sea level with maximum levels of 30% in a 10.2 psi environment. (This upper limit mitigates flammability concerns and is dictated by ambient pressure.) The system should incorporate real-time remote monitoring and control capabilities. Medical Grade Water Generation Methods and technologies for in-flight creation of medical grade water from any available water source are required. Because some pharmacological preparations appear to degrade in the space environment, it is highly desirable, from both a consumables perspective as well as from the standpoint of mass, to fly desiccated pharmacological substrates whenever possible and to reconstitute them only when needed. For this reason, medical grade water is required along with a low-g (e.g., 0 g, 1/3 g, and 1/6 g) system to deliver generated water to the substrate and mix as necessary. The general requirements of low mass, user-friendly interface, reliability, and automation are critical to this system. There should be a mechanism included to verify that the water produced meets standard requirements for the medical grade designator. Diagnostic Imaging Capability During long duration flights, it will be important to have medical imaging capability available to assist in diagnosis, treatment, and monitoring during and after medical events. This capability is likely to be an ultrasonic, low power, portable device that provides for diagnostic assistance via data processing algorithms. These algorithms would be expected to provide guidance for the crewmember administering the exam as well as identifying probable diagnoses options and possible treatments for each. The system should be flexible enough to provide fracture analysis, bone density levels, and body cavity status. In-Flight Suction Long duration missions must have the capability to provide medical suction for patients in the event of injury or serious illness. This system must be capable of providing suction for a variety of body orientations in multiple reduced gravity environments. It should be a stand-alone system that does not require oversight by another crewmember. In the event of malfunction, it should provide an audio alert, a display of the malfunction type, plus a safing algorithm. The contents of the suction system must be easily disposed of safely and without release of contents into the environment. Biomedical Signal Processing Assessment of an ill or injured crewmember may sometimes be accomplished in large part by the status of the biomedical signal, or EKG. This will have to be a “smart” system, which analyzes sensor placement, sensor health, signal monitoring, signal normalcy, and signal analysis. It is required that the biomedical signal be capable of monitoring cardiac health and physiological state. The processor must be fail-safe and must annunciate an audible alarm when a malfunction occurs. A display should provide a readout of the anomaly type and the system must safe itself when malfunctions occur. (NOTE: There may be a subset of malfunctions {e.g., loose lead} that will not require a shut-off or self-safing function.) The system must be volumetrically small with minimal mass. Intelligent Software Modules Software modules with the capability to review medical data in a SQL compliant database, assign or suggest appropriate SNOMED CT codes, and store the suggested codes in electronic format with discrete elements is highly desirable to avoid having to train hierarchical nomenclature to crewmembers. The hierarchical relationships between SNOMED codes should be maintained and stored in the output. TOPIC: X12 Life Support and Habitation Achieving sustained human presence in space and on lunar and Martian sites requires innovative life support and habitation technologies. Proposals are sought that improve life support and habitation systems in the areas of: Advanced Life Support including closed loop, and to a lesser extent, open loop technologies for air revitalization (including lunar dust abatement technologies), water reclamation, solid waste management (including small disposal units for human waste), food management systems (including galley), and biomass production; Extra Vehicular (EVA) technologies including suit assembly, life support systems, power communications and information handling; Contingency Response technologies including fire prevention, detection and suppression, in situ fabrication and repair, and in situ resource utilization; Advanced Environmental Monitoring and Control including air, water and surface monitoring, external environment monitoring, and life support integrated control. X12.01 Advanced Life Support: Air and Thermal Lead Center: JSC Participating Center(s): ARC, GRC, KSC, MSFC Advanced life support systems will be essential to enable human planetary missions as outlined in the Vision for Space Exploration. Innovative, efficient, and practical concepts are needed for regenerative air revitalization, ventilation, temperature, and humidity control. Requirements include safe operability in micro- and partial-gravity, ambient and reduced-pressure environments, high reliability, regeneration and minimal use of expendables, ease of maintenance, and low-system volume, mass, and power. Proposals should explicitly describe how their work is expected to improve power, volume, mass, logistics, crew time, safety and reliability, with comparisons to existing state-of-the-art technologies. Information and documentation on advanced life support systems can be found at http://advlifesupport.jsc.nasa.gov. Air Revitalization The management of cabin atmosphere in spacecraft and habitats includes concentration, separation, and control techniques for oxygen, carbon dioxide, water vapor, particulates and trace chemical components. This includes processing and recovering resources derived from waste streams and from in situ planetary resources. Technologies focused at closing the air loop will have higher priority. Areas of emphasis include: * Atmosphere revitalization process integration to achieve energy and logistics mass reductions; * Separation of carbon dioxide from a mixture primarily of nitrogen, oxygen, and water vapor to maintain carbon dioxide concentrations below 0.3% by volume;. * Recovery of oxygen from carbon dioxide including approaches to deal with by-products of the process; * Regenerable processes for removing trace chemical components from cabin air and/or gas product streams from other systems (e.g., water reclamation, waste management, etc.); * Regenerable, re-usable, particulate filters for air; * Novel approaches to suspended particulate matter removal from cabin and habitat atmospheres, including approaches to isolating cabin and habitat living areas from external dust sources such as Martian or lunar soil; and * Methods of storage and delivery of atmospheric gases to reduce mass and volume and improve safety. Advanced Thermal Control Systems Thermal control is an essential part of any space vehicle, as it provides the necessary thermal environment for the crew and equipment to operate efficiently during the mission. A primary goal is to provide advanced technologies for temperature and humidity control; however, advanced active thermal control also includes technologies in the areas of heat acquisition, transport, and rejection. Areas of emphasis include: * Liquid-to-liquid heat exchangers that provide two physical barriers preventing inter-path leakage; * Advanced technologies to control cabin temperature and humidity in microgravity. Condensate that is collected must be able to be recovered and transported to the water recovery system; * Alternate methods of atmospheric humidity control that do not use liquid-to-air heat exchanger (dependent on the spacecraft active thermal control system) or mechanical refrigeration technology; * Technologies to inhibit microbial growth on wetted surfaces. Applications include condensate collection surfaces for humidity control and heat exchangers resident in water loops; * Lightweight, versatile, and efficient heat acquisition devices including flexible cold plates, to provide cooling to electronics, motors, and other types of heat producing equipment that is internal to the cabin; * Lightweight, controllable, evaporative heat rejection devices that can operate in environments ranging from space, Mars' atmosphere, and Earth's atmosphere; * Alternative heat transfer fluids that are non-toxic, non-flammable, and have a low freezing temperature; * Energy storage devices that maintain the integrity of food or science samples. For maintenance of temperatures of -20°C, -40°C, -80°C or -180°C; * Highly accurate, remotely monitored, in situ, non-intrusive thermal instrumentation; and * Low-energy, low-noise, high-capacity fans or similar devices for moving air. Component Technologies Energy efficient, low mass, low noise, low vibration, or vibration isolating, fail-safe, and reliable components for handling gases, fluids, particulates, and solids applicable to spacecraft environmental control and air revitalization, including actuators, fans, pumps, compressors, coolers, tubing, ducts, fittings, heat exchangers, couplings, quick disconnects, and valves that operate under varied levels of gravity, pressure, and vacuum. Mass flow monitoring and control devices that have similar attributes and that are easily calibrated and serviced. X12.02 EVA Technologies Lead Center: JSC Participating Center(s): ARC Advanced Extravehicular Activity (EVA) systems are necessary for the successful support of future human exploration space missions. Advanced EVA systems include the space suit pressure garment, the portable life support system, tools and equipment, and mobility aids such as rovers. Exploration EVA missions require innovative approaches for maximizing human productivity and for providing the capability to perform useful work tasks. Top-level requirements include reduction of system weight and volume, increased hardware reliability, maintainability, durability, and operating lifetime, increased human comfort, and less-restrictive work performance capability in the space environment, in hazardous ground-level contaminated atmospheres, or in extreme ambient thermal environments. Areas in which innovations are solicited include the following: Environmental Protection * Radiation protection technologies that protect the suited crewmember from radiation; * Puncture protection technologies that provide self-sealing capabilities when a puncture occurs and minimizes punctures and cuts from sharp objects; * Dust and abrasion protection materials or technologies to exclude or remove dust and withstand abrasion; and prevent dust adhesion; and * Flexible space suit thermal insulation suitable for use in vacuum and low ambient pressure. EVA Mobility * Space suit low profile bearings that maximize rotation necessary for partial gravity mobility requirements and are lightweight. Life Support System * Long-life and high-capacity chemical oxygen storage systems for an emergency supply of oxygen for breathing; * Low-venting or non-venting regenerable individual life support subsystem(s) concepts for crewmember cooling, heat rejection, and removal of expired water vapor and CO2; * Fuel cell technology that can provide power to a space suit and other EVA support systems; * Lightweight convection and freezable radiators for thermal control; * Innovative garments that provide direct thermal control to crewmember; * High reliability pumps and fans that provide flow for a space suit but can be stacked to give greater flow for a vehicle; * CO2 and humidity control devices that, while minimizing expendables function in a CO2 environment; and * Variable conductivity flexible suit garment that can function as a radiator for high metabolic loads and as an insulator during period of low physical activity and low metabolic rates. Sensors, Communications, Cameras, and Informatics Systems * Space suit mounted displays for use both inside and outside the space suit—outside mounted displays will be compatible with the space environment; * CO2, bio-med (heart rate and blood oxygen level), radiation monitoring, and core temperature sensors with reduced size, lightweight, increased reliability, decreased wiring, and packaging flexibility; * Visible spectrum camera that provides environment awareness for crewmembers and the public and are integratable into a spacesuit that is lightweight and low power; * Lightweight sensor systems that detects N2, CO2, NH4, O2, ammonia, hydrazine partial pressures, including self-powered sensors; * Lightweight, low power, radio and laser communications with the capability to integrate audio, video, and data on the same data stream to provide reliable communications between the crew and a lander or habitat; and * Low power, lightweight, radiation hardened, or radiation tolerant informatics computer systems with standard graphics outputs and standard audio inputs and outputs, capable of running commercial operating systems and applications. Integration * Robot control by EVA crewmember via voice control or other methods; * Minimum gas loss airlocks providing quick exit and entry and can accommodate an incapacitated crewmember; and * Work tools that assist the EVA crewmember during operations in zero gravity and at worksites; specifically, devices that provide temporary attachments, which rigidly restrain equipment to other equipment and the EVA crewmember, and that contain provisions for tethering and storage of loose articles such as tool sockets. EVA Navigation and Location * Systems and technologies for providing an EVA crewmember real-time navigation and position information while traversing on foot or a rover; and * Systems and technologies for managing and locating tools during planetary surface science and maintenance EVA sorties. X12.03 Contingency Response Technologies Lead Center: GRC Participating Center(s): JSC, MSFC Decades of experience in manned space flight have demonstrated that during any mission, unexpected events will occur. If the crew is adequately equipped to address such contingencies during exploration missions, the chances of successfully completing that mission can be greatly increased. The objective of this subtopic is to develop technologies in the areas of fire prevention, detection, and suppression (FPDS) and in situ fabrication and repair (ISFAR) that will support the crew in the event of a fire or if a critical component breaks during a mission, respectively. These technologies may be in the form of devices, models, and/or instruments for use in microgravity and/or for commercial applications on Earth. The top-level requirements for a viable technology include the reduction of system hardware weight and volume and increased hardware reliability, durability, and operating lifetime. Research conducted during the Phase 1 contract should focus on demonstrating the technical feasibility of the FPDS or ISFAR protocol/system and show a path toward a Phase 2-specific deliverable. The contractor will, when appropriate, deliver a demonstration unit of the instrumentation for NASA testing before the completion of the Phase 2 contract. Fire Prevention, Detection, and Suppression The objective of the Fire Prevention, Detection, and Suppression (FPDS) subtopic is to develop technologies that, when incorporated into the design philosophy and functional design of exploration vehicles and habitats, will quantitatively reduce the likelihood of a fire and reduce the impact to the mission should a fire occur. The element is composed of four major theme areas including: fire prevention and material flammability, fire signatures and detection, fire suppression and response, and analysis of fire scenarios. Innovations are sought in the following theme areas: * Quantifying the effects of microgravity, 1/6-g (lunar) and 1/3-g (Martian) on the ignitability of materials and the subsequent flame spread, particularly related to determining relevant low-gravity behavior from normal gravity tests; * Improving the performance of spacecraft fire safety systems through the development of advanced fire detection and suppression systems and strategies as well as predicting the effects of smoke and precursor generation and transport; and * Developing techniques for creating and analyzing the effectiveness of fire resistant materials and coatings, including fire prevention techniques, for spacecraft structures, radiation shielding materials, paneling, fabrics (cotton, paper, synthetics), foams, etc. In Situ Fabrication and Repair In Situ Fabrication and Repair develops technologies for life support system maintenance and integrated habitat radiation shielding fabrication with a focus on contingency response and maximization of in situ resource utilization to reduce launch mass and volume. The manufacture or repair of components during a mission is essential to human exploration and development of space. Fabrication and repair beyond low Earth orbit is required to reduce resource requirements, spare parts inventory, and to enhance mission security. Proposals are sought in the technical themes listed below: * Application of Free Form Fabrication (FFF) methods to low gravity (3/8 and 1/6 g level) manufacturing of near net shape products and spare parts from in situ derived resources or provisional feedstock; * Processes for extracting in situ resources into raw materials and feedstock for use with rapid prototyping technology; * Extension of fused deposition methods to the use of binderless metal wire feed stock; * Adaptation of ultrasonic consolidation methods to use narrow ribbon metal feedstock to reduce subsequent machining operations and waste; * Novel and innovative in situ repair methods such as but not limited to: welding, composite repair, and self healing materials; * Development of highly automated habitat construction methods that incorporates in situ materials on surface or primary structure may use in situ construction; * Development of dust mitigation techniques applicable to planetary habitat construction; * Integration of radiation shielding materials into habitat construction methods; and * Innovative approaches for recycling of materials for secondary uses. X12.04 Advanced Environment Monitoring and Control Lead Center: JPL Participating Center(s): GRC, JSC This subtopic addresses monitoring and control technologies, which support the operation of an Advanced Life Support (ALS) system for future long duration space missions. There are two application areas: Acoustics Monitoring and Environmental Controls. Acoustics Monitoring Section The objective is a proof-of-concept acoustic sensor system consisting of fixed and crew-worn transducers. At least ten fixed transducers shall be distributed in a habitable volume of at least 2x2x6m. The goal for the fixed microphones is to provide sound pressure level measurements with Type I measurement accuracy over the Octave Band frequency range from 63 Hz through 20 kHz. The system shall be capable of measuring 1/3 Octave Band, Octave Band, and Narrow Band sound pressure levels averaged over a specified interval with user defined data acquisition parameters. The fixed microphones shall also operate as an acoustic dosimeter with Type III accuracy and shall measure and log the maximum, A-weighted, Overall Sound Pressure Level every 30 seconds for at least 24 hours. The system shall also detect Hazard Levels of 85+ dBA and generate an alarm. The crew-worn transducer, clipped to a shirt collar, shall operate as a Type III acoustic dosimeter and shall measure and log the maximum, A-weighted, Overall Sound Pressure Level every 30 seconds for at least 24 hours. The size and mass of the device shall be comparable to COTS dosimeters. All system measurements shall be carried out remotely and the data managed by software. The system shall be demonstrated in a mock-up, and calibrations and comparisons made with appropriate instruments and methods. Environmental Controls Advanced Environmental Controls - the development of advanced control system technologies is necessary for the integrated operation of environmental systems for future long-duration human space missions. The interdependence of advanced environmental processing systems requires a non-avionics requirements process that allows design for controllability. This year particular emphasis is placed on the following: * Control strategies for closed-loop systems - closed loop and biological systems have different constraints and control paradigms than conventional processes. There is a need for new control algorithms, analyses, design methodologies, strategies, and techniques to provide this capability; * Ontologies for integrated operations - human exploration missions involve hundreds of systems developed by dozens of organizations. To develop software that can integrate across these systems and integrate with operations requires the use of common terminology across multiple disciplines. A common ontology must be developed to enable the integration of control of advanced life support systems; and * Development and integration of autonomous system and inter-system control with crew and ground operations - there is a need for tools, architectures, and technologies that can support the integration of operations between crew, ground operators, ground applications, and on-board applications. X12.05 Advanced Life Support: Food Provisioning and Biomass Lead Center: JSC Participating Center(s): ARC, GRC, KSC, MSFC Exploration missions beyond low Earth orbit greatly limit allowable consumables and require development of innovative low maintenance, reconfigurable, reusable, or self-sufficient food production. Advancements are necessary to develop a combination of extended duration shelf life stored foods augmented with fresh foods grown within the spacecraft. Crop systems, in addition to producing fresh vegetables, storage roots, grains and legumes may contribute to air revitalization and utilize wastes from water recovery and waste management systems. Crop Systems The production of biomass (in the form of edible food crops) in closed or nearly closed environments is essential for the future of long-term planetary exploration and human settlement in lunar and Mars base applications. These technologies will lead not only to food production but also to the reclamation of water, purification of air, and recovery of inedible plant resources in the comprehensive exploration of interplanetary regions. Areas in which innovations are solicited include: * Crop lighting, such as LED, solar collectors and innovative technologies. Lighting transmission and distribution systems, luminaries, fiber optics, water jackets, and other heat removal technologies are also areas of interest; * Water and nutrient management systems such as hydroponics and/or solid substrates for food production and separation of nutrients from waste streams are solicited. In this area, regenerable media for seed germination plant support are also of interest as is separation and recovery of usable minerals from wastewater and solid waste products for use as a source of mineral nutrients. Consideration should be given tor systems operation in microgravity and hypogravity (1/6 g on Moon, 3/8 g on Mars) environments; and * Other areas of interest: crop mechanization and automation, facility or system sanitation, crop health measurement, flight equipment support, structures and environmental monitoring and control technologies that are specific to crop systems (e.g., ethylene detection and removal, sensors for root zone oxygen and water content, etc.). Food Provisioning * Safe, nutritious, acceptable, and varied shelf-stable foods with a shelf life of 3 to 5 years will be required to support the crew during future exploration missions to the Moon or Mars. Shelf-life extension may be attained through food preservation methods and/or packaging. Packaging materials must provide sufficient oxygen and water barrier properties to maintain shelf life. Food packaging technologies are needed that minimize a potentially significant trash management problem by using packaging with less mass and volume and/or by using packaging that is biodegradable, recyclable, or reusable; * Processing crops or bulk ingredients into edible food ingredients or table-ready products will be necessary to provide a self-sustaining food system for an exploration mission. Equipment that is highly reliable, safe, automated, and minimizes crew time, power, water, mass, and volume will be required. Equipment for processing raw materials must be suitable for use in hypogravity (e.g., 1/6g on Moon, 3/8g on Mars) and in hermetically sealed habitats; * Food preparation systems will be required to heat and rehydrate the shelf stable food items and to prepare meals from the processed and re-supplied items. Technologies to support on-orbit crew meal storage, preparation, dining activities, and trash dispensing are being sought;and * Food quality and safety are essential components in the maintenance of crew health and well being. Efforts should be focused on control of food spoilage and food quality throughout the entire shelf life of the food. Effects of radiation on crop functionality and the stored food system quality are also needed. X12.06 Habitation Systems Lead Center: JSC Participating Center(s): ARC, GRC, KSC, MSFC Habitation Systems Habitation systems for future crewed micro-gravity transits, reduced gravity planetary lunar or Martian surfaces, and long duration, deep-space environments are requested. Products can include basic research, system analysis, mockup evaluation, functionality demonstrations/tests, and actual prototype hardware. Exploration missions away from low Earth orbit greatly limit allowable consumables and require development of innovative low maintenance, re-configurable, and reusable systems. Minimal volume configurations (or dual use) during non-use mission phases are highly desirable. Habitation systems should consider the following broad themes: re-configurable crew volumes for multi-gravity environments (micro and reduced gravity), multi-use work stations, multi-gravity translation strategies, crew radiation exposure mitigation, physically and psychologically ergonomic personal volumes, automated deployment, quiescent operations between missions, multi-purpose stowage systems for food/trash, advanced hygiene systems, and automated housekeeping/self-repairing habitat surfaces, durability, commonality of hardware/systems, and low total life-cycle costs. Specific areas in which advanced habitability system innovations are solicited include: Wardroom Systems: Erectable or inflatable systems that support crew dinning, conference, external viewing (windows), illumination, and relaxation activities. Includes off-nominal uses (emergency medical or repair) while maintaining hygienic conditions. Galley Systems: Systems requiring minimal crew preparation (heating, cooling, and rehydration) for food heating and accurate water dispensing. Specific areas include systems that allow individual crew meal flexibility and high-energy efficiency. Crew Hygiene Systems: Low maintenance/self-cleaning fecal, urine, menstrual, emesis, hand/body wash, and grooming systems. Specific areas include non-foaming separatorsand no-rinse/non-alcohol hygiene products. Toilet systems should consider air, liquid, vacuum, and low-gravity transport methods. Collected waste should be prepared for recovery or long-term stabilization. Integrated hygiene systems should provide, acoustic and odor isolated private crew volumes compatible with multi-gravity interfaces. Crew Accommodation Systems: Reconfigurable, deployable, or inflatable integrated crew accommodations that provide visual and acoustical isolated crew volumes for sleeping, audiovisual communication/entertainment, personal stowage, quiet ventilation/thermal control, and radiation exposure reduction/safe-haven. Clothing Systems: Low mass reusable or long usage clothing options that meet flammability, out gassing, and crew comfort requirements. Used clothing cleaning/drying systems with low-water usage and non-toxic detergents/enzymes compatible with biological water reclamation systems or non-water cleaning methods. Stowage Systems: Interior/exterior stowage systems for partial gravity environments that maximize usable volume and include contents identification and inventory control systems. Long-term external stowage for biological or other wastes on a planetary surface that safe and consistent with planetary protection policies. X12.07 Advanced Life Support: Water and Waste Processing Lead Center: JSC Participating Center(s): ARC, GRC, KSC, MSFC Regenerative closed-loop life support systems will be essential to enable human planetary exploration as outlined in the Vision for Space Exploration. These future systems must provide additional mass balance closure to further reduce logistics requirements and to promote self-sufficiency. Recovery of useful resources from liquid and solid wastes will be essential. Requirements include safe operability in micro- and partial-gravity, ambient and reduced-pressure environments, high reliability, regeneration and minimal use of expendables, ease of maintenance, and low-system volume, mass and power. Proposals should explicitly describe how the work is expected to improve power, volume, mass, logistics, crew time, safety and/or reliability, giving comparisons to existing state-of-the art technologies. Additional documentation and information can be found at http://advlifesupport.jsc.nasa.gov, including the expected composition of solid wastes and wastewater, which can be found within the "Baseline Values and Assumptions Document". Water Reclamation Efficient, direct treatment of wastewater and product water consisting of urine, brines, wash water, humidity condensate, and or product water derived from in situ planetary resources, to produce potable and hygiene water supplies. Technologies that contribute to closing the water loop will be given higher priority. Areas of emphasis include: * Novel methods of process design and integration to minimize trace contaminant carryover from the cabin atmosphere leading to reduced logistics needs; * Physicochemical methods for primary wastewater treatment to reduce total organic carbon from 1000 mg/L to less than 50 mg/L and/or total dissolved solids from 1000 mg/L to less than 100 mg/L; * Post-treatment methods to reduce total organic carbon from 100 mg/L to less than 0.25 mg/L in the presence of 50 mg/L bicarbonate ions, 25 mg/L ammonium ions and 25 ppm other inorganic ions; * Methods for the phase separation of solids, gases, and liquids in a microgravity environment that are insensitive to fouling mechanisms; * Methods for the recovery of water from brine solutions; * Methods to eliminate or manage solids precipitation in wastewater lines; * Disinfection technologies for potable water storage and point-of-use. Residual disinfectants for potable water that is compatible with processing systems including biological treatment; and * Techniques to minimize or eliminate biofilm and microbial contamination from potable water and water treatment systems, including components such as pipes, tanks, flow meters, check valves, regulators, etc. Solid Waste Management Wastes (trash, food packaging, feces, biomass, paper, tape, filters, water brines, clothing, hygiene wipes, etc.) must be managed to protect crew health, safety, and quality of life, to avoid harmful contamination of planetary surfaces (Moon, Earth, and Mars), and to recover useful resources. Treatment methods can include both oxidative and non-oxidative approaches. Areas of emphasis include: * Volume reduction of wet and dry solid wastes; * Small and compact fecal collection and/or treatment systems; * Water recovery from wet wastes (including human fecal wastes, food packaging, brines, etc.); * Stabilization, sterilization, and/or microbial control technologies to minimize or eliminate biological hazards (to the crew, to Mars, to Earth) associated with waste; * Mineralization of wastes (especially fecal) to ash and simple gaseous compounds (e.g. CO2, CH4); * Containment of solid wastes onboard the spacecraft that incorporates odor abatement technology; * Containment devices or systems, with low volume and mass, that can maintain isolation of disposed waste on planetary surfaces (such as Mars); and * Microgravity-compatible technologies for the containment and jettison of solid wastes in space. Component Technologies Energy-efficient, low-mass, low-noise, low-vibration or vibration isolating, fail-safe, and reliable components for handling fluids, slurries, biomass, particulates, and solids applicable to spacecraft wastewater treatment and solid waste management, including particle size reduction technologies (0.2 cm to 100 microns), actuators, pumps, conveyors, tubing, ducts, bins, fittings, tanks, couplings, quick disconnects, and valves that operate under varied levels of gravity, pressure, and vacuum. TOPIC: X13 Human Systems Integration Long-term presence in space in confined, isolated, and foreign environments may lead to impairments of human performance and behavioral health problems. Proposals are sought in the areas of space human factors engineering such as physical, cognitive, and team performance; behavioral health and performance including psychosocial, neurobehavioral adaptation as well as cognitive task performance, and sleep and Circadian rhythms. The topics include, but are not limited to: design and verification tools that provide predictions of human-system performance; tools that facilitate designing human-system interfaces or environments; tools useful in verifying human-system requirements; psychological factors relevant to crew selection and performance; pre-launch and in-flight crew training systems; self-sufficient operations in case of emergency and without external resources; technology that can assist the mission control operations: design of workflow in vehicle maintenance, preparation checkout, and launch control. X13.01 Space Human Factors Engineering Lead Center: JSC Participating Center(s): ARC The long-term goal for this subtopic is to enable planning, designing, training, and carrying out human space missions of up to 5 years with crew independence, without re-supply and without real-time communications to Earth. Specifically, this subtopic's focus is the development of innovations in crew equipment; and the development of technologies for assessment, modeling, and enhancement of human performance; and the development of design tools for engineers to incorporate human factors engineering requirements into hardware and software. Proposals are solicited that seek to develop technologies that address these specific needs: * Monitoring and maintaining human performance non-intrusively. Specifically, minimally invasive and unobtrusive devices and techniques to monitor the behavior and performance (physical, cognitive, perceptual, etc.) of individuals and teams during long-duration space flights or analog missions. Embedded measures to detect significant changes in crew readiness to perform physical or cognitive tasks; * Predicting human performance: methods and models for predicting effects on physical performance of encumbrances of clothing, space suits, etc. Models for predicting effects of physical environment (e.g., lighting, noise, temperature, contaminants) on human performance. Models to simulate and optimize interactions between humans and equipment/vehicle. Capability to implement time-delay algorithm and functionality into simulation for higher fidelity and effectiveness. Models for predicting effects of cognitive changes on performance; * Tools to aid in design and evaluation of human-system interfaces for speed, accuracy, and acceptability in a cost-effective and reliable manner: automated analysis of computer-user interfaces for complex display systems to conduct objective review of displays and controls, and to determine compliance with guidelines and standards. Quantitative measures of the effectiveness of user interfaces to be used for task-sensitive evaluations; * Tools that facilitate the user interface design for human computer interfaces, and for facilitators such as procedures, labels, and instructions. Tools should assist the designer in incorporating contextual information such as the user’s task, the user’s knowledge, and the system limitations; and * Tools to build just-in-time system and operational information software to aid human users conducting routine and emergency operations and activities. Such tools might include effective and efficient job aids (e.g., "intelligent" manuals, checklists, and warnings) and support for designing flexible interfaces between users and large information systems. Methods for development of “facilitators” (procedures, labels, etc.) adapted for the development of space vehicle and payload applications. X13.02 Behavioral Health and Performance Lead Center: ARC Behavioral Health and Performance provides the necessary technology, techniques, capabilities, and knowledge that will support mission success, during human exploration flight and return to Earth. This will be accomplished by optimizing the behavioral health and performance of each astronaut and crewmember, and by mitigating psychosocial, neurobehavioral, sensorimotor, cognitive, and sleep chronobiology risks. Behavioral health and performance research contributes to medical standards, guidelines, and requirements and produces design tools and diagnostic measures for the Chief Health and Medical Officer, flight surgeons, and astronauts. The technical areas supported by this program include performance readiness, effective and efficient teamwork for pre-, in-, and post-flight expedition missions, and psychological selection validated criteria, tools, and procedures. Prolonged missions and the associated adaptation and de-conditioning due to microgravity, as well as significant time delays between Earth and the space environment increase the likelihood of serious crew conflict as well as behavioral health and performance decrements. Proposals are solicited that seek to develop core knowledge, predictive models, and enabling technologies that address these specific needs: * Non-intrusively monitoring and maintaining human performance. Specifically, minimally invasive and unobtrusive devices and techniques to monitor the behavior and performance (physical, cognitive, perceptual, sensorimotor, etc.) of individuals and teams during long-duration space flights or analog missions. Embedded measures to detect significant changes in crew readiness to perform physical or cognitive tasks; and * Monitoring and maintaining non-intrusively behavioral health. For example, self assessment tools for determining levels of stress, fatigue, conflict, and anxiety of an individual crewmember and training techniques for coping and on-board support tools for behavioral health. X13.03 Systems Engineering and Requirements Lead Center: JSC Participating Center(s): ARC, KSC The goal of effective Human Systems Integration challenges many areas of technology, including distributed data management and control, sensor interpretation, planning and scheduling, modeling and simulation, and validation and verification of autonomous systems. These various technology areas must eventually be integrated into a system-of-systems. Particular emphasis is placed on the following: System Engineering Tools Technologies, tools, and methodologies are needed that assure development activity is congruent with Exploration Mission capability requirements. Decision support tools are needed to help in the visualization of portfolio balance and clear representation of complex systems as well as a capture method for the interactions/interdependencies/ interfaces between system elements. System Simulation Tools The ability to analyze, synthesize, and develop integrated function-based and simulation-based system architectures in support of Human Systems. Key to this requirement is either the further extension/enhancement of current available SE tools or acquisition/development of tools that will allow for system level concept development and concept simulation. System Integration Tools The ability to enable human system integration for exploration missions is strongly affected by the structure and architecture of the systems used to sustain and protect the crew. There is a need for the development and evaluation of control architectures and strategies for determining relative benefit, risk, and costs of the utilization of candidate system architectures. Tools for capturing state knowledge of the entire portfolio by project, including dependencies, maturity, and relationships to requirements are also needed. Capability-based requirements methods require tools and methodologies that enable capture of current practice for information integration between ground-based systems, on-board systems, and crew systems; goal analysis; surveys of existing and proposed technologies; mapping of technology to tasks; prototyping; integrated testing and evaluation criteria; and development of experienced personnel. Integration Test Bed Tools and Applications Integrated ground tests for human exploration missions will provide a test bed for development of hardware, requirements, hardware acquisition strategies, novel system concepts, and management. Tools are needed that provide techniques for real-time analysis; techniques for planning, scheduling, and conducting complex integrated mission simulations; tools to develop system-level mathematical models of missions; and systems engineering and analysis tools for mission architecture studies. Human-System Integration for Manufacturing and Launch Site Operations Human-System Integration of Manufacturing and Launch Site Operations addresses the following functional areas: Manufacturing, Spacecraft Processing, Launch Control, Landing and Recovery, Repair and Refurbishment, and Enabling Operations. Specific areas of interest include intelligent work instruction systems; maintainer/launch controller situational awareness; human/robotic maintainer on-board capability; reduced size ground crew training modules; and predictive labor requirement models. Research should be conducted to demonstrate technical feasibility during the Phase 1 contract and show a path toward a Phase 2 hardware and software demonstration. The contractor will, when possible, deliver a demonstration unit of the monitoring instrumentation for NASA testing before the completion of the Phase 2 contract. TOPIC: X14 Space-Based Industry Enabling Technologies The goal of this topic is to enable the optimization of investments made in technologies for the development of systems to support and maintain space-based industries and for benefiting NASA’s exploration mission infrastructures. As stated in the Report of the President’s Commission on Implementation of United States Space Exploration Policy, “This new space industry will reduce the cycle time for critical technology innovation. It will immeasurably augment NASA’s ability to explore the universe.” It is anticipated that, in order to go to the Moon and beyond, a sizable in-space commercial infrastructure will be required. NASA will need this commercially driven infrastructure to build upon in order to further exploration that is affordable and sustainable. This topic seeks breakthrough technologies, concepts, and methods that reduce the cost and risks of the expansion of space-based industries. Innovative approaches are needed that identify what the space-based industries might be doing and their needed infrastructures as well as the technologies required to achieve the infrastructures. X14.01 Space-Based Industries Lead Center: MSFC Innovative techno-economic research proposals are sought for space-based industries ideas that identify their purpose, basic required infrastructures, and how they might complement NASA’s exploration missions. The Phase 1 work must sufficiently develop one or more industry ideas to show they are sufficiently feasible, both technically and economically, for Phase 2 demonstrations of their viability. The demonstrations may use physical and mathematical modeling and other research techniques. Each industry idea may have infrastructures that include a wide variety of needed innovations that will be common to NASA’s exploration goals as well as to space industries that have a wide variety of purposes like tourism, servicing and maintenance of satellites, food production, energy production, fuels and propellants production, entertainment, in-space fabrication, workshops, hotels and habitats, life support systems, vehicles, freight and warehousing, roads, and spaceports. The research should include economic business models, cost feasibility examination, and analyses that can show how innovations that are common to the multiple goals can save money for NASA as well as space industries. The technical innovations may include, but are not limited to: materials, fabrication processes, power and power distribution, communications, waste management, robotic support, and more. It is expected that the technical innovative ideas will go further than the specific exploration topics and subtopics requests made elsewhere in this 2005 solicitation due to the broader scope of applications. X14.02 Multi-Use Microgravity and Software Lead Center: JSC The purpose of this subtopic is to develop technologies, methodologies, and tools that can support the integrated development of the software system-of-systems necessary for exploration missions. Human space flight challenges many areas of software technology, including distributed data management and control, sensor interpretation, planning and scheduling, modeling and simulation, and validation and verification of autonomous systems. This subtopic focuses on the development portion of the mission life cycle and the dependence of the eventual mission solutions on the processes and methods used to define and build vehicles and support operations. The need for such technologies, methodologies, and tools is evidenced by the low success rate of commercial and government systems, where failure occurs at delivery rather than during operation. Management of the development of such large systems is essential to integration. Software Architecture and Systems Integration The challenges of human system integration for exploration missions is strongly affected by the structure and architecture of the software systems required to provide control and status pathways to ground support systems and personnel; to support mission planning and operation; to provide crew interfaces for status, control, and operation of the vehicle systems, science, and operations, including communications, planning, task management, interpersonal activity, system configuration management, inventory, food, workflow, resource management, experiments, and vehicle operation and maintenance. Onboard software must integrate, and be interoperable with the ground support systems for planning, logistics, operations, science, medical, and engineering, as well as with subsequent exploration spirals. This requires the development of structures and methods for determining relative benefits, risks, and costs of the utilization of various engineering approaches. Project management tools are needed that can conduct and manage Exploration Mission capability and technology gap analysis; provide technology-to-capability mapping; map technology gaps to research initiatives; and provide decision support. Systems Engineering Support to Human Systems There is a need for new tools to support the development of non-avionic control systems throughout the program life cycle. This includes tools for managing prototyping, requirements, design, design knowledge capture, testing, and growth and maintenance across multiple development teams. Particular emphasis is placed on design methods that address the interdependencies between systems. Adapting the Joint Capabilities Integration and Development System (JCIDS) approach to systems engineering requires development of tools and methodologies that enable: surveys of current information integration practices between ground-based systems, on-board systems and crew systems; goal analysis (software task analysis); surveys of existing and proposed technologies; mapping of technology to tasks; prototyping to drive out design constraints and detailed requirements; development of testing and evaluation criteria for advanced or untried architectures and technologies and maturation of those technologies into an integrated system of systems; tracking lessons learned, methods, and processes; and development of an experienced personnel base. Research should be conducted to demonstrate technical feasibility during the Phase 1 contract and show a path toward a Phase 2 demonstration. The contractor will, when possible, deliver a demonstration unit of the hardware and software for NASA testing before the completion of the Phase 2 contract. . 9.1.3 SCIENCE The National Aeronautics and Space Administration's (NASA) Vision, To improve life here, to extend life there, and to find life beyond, and its Mission, To understand and protect our home planet, To explore the Universe and search for life, and To inspire the next generation of explorers ... as only NASA can, allow the science objectives of the NASA Science Mission Directorate to be clearly defined as the orderly pursuit of the Agency's strategic goals and strategic objectives. Responsibility for achieving several of NASA's strategic objectives (The New Age of Exploration - NASA's Direction for 2005 and Beyond, available at http://www.nasa.gov) belongs, in whole or in part, to the Science Mission Directorate (SMD), including: * Undertake robotic and human lunar exploration to further science and to develop and test new approaches, technologies, and systems to enable and support sustained human and robotic exploration of Mars and more distant destinations; * Conduct robotic exploration of Mars to search for evidence of life, to understand the history of the Solar System, and to prepare for future human exploration; * Conduct robotic exploration across the Solar System for scientific purposes and to support human exploration – in particular, explore Jupiter's moons, asteroids, and other bodies to search for evidence of life; to understand the history of the Solar System; and to search for resources; * Conduct advanced telescope searches for Earth-like planets and habitable environments around other stars; * Explore the universe to understand its origin, structure, evolution, and destiny; * Conduct a program of research and technology development to advance Earth observation from space, improve scientific understanding, and demonstrate new technologies with the potential to improve future operational systems; * Explore the Sun-Earth system to understand the Sun and its effects on Earth, the Solar System, and the space environmental conditions that will be experienced by human explorers, and demonstrate technologies that can improve future operational Earth observation systems; and * Use NASA missions and other activities to inspire and motivate the nation's students and teachers, to engage and educate the public, and to advance the scientific and technological capabilities of the nation. The following SBIR topics and subtopics seek to develop technology to enable science missions in support of these strategic objectives. http://science.hq.nasa.gov/ TOPIC: S1 Robotic Exploration of the Moon and Mars 127 S1.01 Detection and Reduction of Biological Contamination on Flight Hardware (JPL) 127 S1.02 Mars In Situ Robotics Technology (JPL) 128 S1.03 Long Range Optical Telecommunications (JPL) 129 S1.04 Entry, Descent and Landing (JPL) 129 S1.05 Sample Return Technologies (JPL) 130 TOPIC: S2 Robotic Exploration Throughout the Solar System 132 S2.01 Science Instruments for Conducting Solar System Exploration (JPL) 132 S2.02 Extreme High Temperature/High Pressure Environment (JPL) 133 S2.03 Nanosensors (JPL) 134 S2.04 Deep Space Power Systems (GRC) 134 S2.05 Astrobiology (ARC) 135 S2.06 Advanced Flexible Electronics (JPL) 136 S2.07 Risk Modeling and Analysis (JPL) 137 TOPIC: S3 Astronomical Observatories to Seek Earth-like Extrasolar Planets and Environments 137 S3.01 Precision Formations for Interferometry (JPL) 137 S3.02 High Contrast Astrophysical Imaging (JPL) 138 S3.03 Precision Deployable Lightweight Cryogenic Structures for Large Space Telescopes (JPL) 139 S3.04 Large-Aperture Lightweight Cryogenic Telescope Components and Systems (MSFC) 140 TOPIC: S4 Exploration of the Universe Beyond Our Solar System 140 S4.01 Infrared and Sub-mm Sensors and Detectors (JPL) 140 S4.02 Terrestrial and Extra-Terrestrial Balloons and Aerobots (GSFC) 141 S4.03 Cryogenic Systems for Sensors and Detectors (GSFC) 142 S4.04 Optics and Optical Telescopes (including X-Ray, UV, Visual, IR) (GSFC) 143 S4.05 Sensor and Detector Technology for UV, X-Ray, Gamma-Ray and Cosmic-Ray Instruments (GSFC) 145 S4.06 Technologies for Gravity Wave Detection (GSFC) 146 TOPIC: S5 Sun-Solar System Connection 147 S5.01 Low Thrust and Propellantless Propulsion Technologies (MSFC) 147 S5.02 Accommodation and Mitigation of Space Environmental Effects (GSFC) 149 S5.03 Technologies for Particles and Fields Measurements (GSFC) 150 TOPIC: S6 Earth-Sun System Instrument and Sensor Technology 151 S6.01 Passive Optics (LaRC) 151 S6.02 Lidar Remote Sensing (LaRC) 151 S6.03 Earth In Situ Sensors (GSFC) 153 S6.04 Passive Microwave (GSFC) 154 S6.05 Active Microwave (JPL) 155 S6.06 Passive Infrared - Sub Millimeter (JPL) 157 S6.07 Thermal Control for Instruments (GSFC) 158 TOPIC: S7 Earth-Sun System Data Applications 159 S7.01 Geospatial Data Analysis Processing and Visualization Technologies (SSC) 159 S7.02 Innovative Tools and Techniques Supporting the Practical Uses of Earth Science Observations (SSC) 160 S7.03 Wireless Technologies for Spatial Data, Input, Manipulation and Distribution (SSC) 160 TOPIC: S8 Science Spacecraft Systems Technology 161 S8.01 Guidance, Navigation and Control (GSFC) 161 S8.02 Command and Data Handling (GSFC) 162 S8.03 Long Range and Near Earth RF Communications (JPL) 163 S8.04 Spacecraft Propulsion (GRC) 163 S8.05 Energy Conversion and Storage for Space Applications (GRC) 164 S8.06 Platform Power Management and Distribution (GRC) 165 TOPIC: S9 Advanced Modeling, Simulation, and Analysis for Science 165 S9.01 Automation and Planning (ARC) 165 S9.02 Distributed Information Systems and Numerical Simulation (ARC) 166 S9.03 Data Management and Visualization (GSFC) 167 S9.04 On-Board Science for Decisions and Actions (ARC) 168 TOPIC: S1 Robotic Exploration of the Moon and Mars NASA is aggressively pursuing the search for resources on the Moon necessary to sustain prolonged human habitation and water and life on Mars using robotic explorers. NASA will augment this program and prepare for the next decade of research missions by investing in key capabilities to enable advanced robotic missions to the Moon and Mars. This suite of technologies will enable NASA to rapidly respond to discoveries this decade and pursue the search for water and life at Mars wherever it may lead. The technologies developed and tested in each mission will help enable even greater achievements in the missions that follow. See URL: http://mars.jpl.nasa.gov/technology/ for additional information on Mars Exploration technologies. Key goals are to 1) conduct robotic expeditions to further science and to test new exploration approaches, technologies, and systems that will enable future human exploration of the Moon and Mars, and 2) conduct sustained, long-term robotic exploration of Mars to understand its history and evolution, to search for evidence of life, and to expand the frontiers of human experience and knowledge. S1.01 Detection and Reduction of Biological Contamination on Flight Hardware Lead Center: JPL Participating Center(s): ARC As solar system exploration continues, NASA remains committed to the implementation of its planetary protection policy and regulations. A Mars sample return mission is being planned for the next decade. Other missions will seek evidence of life through in situ investigations far from Earth. One of the great challenges, therefore, is to develop or find the technologies or system approaches that will make compliance with planetary protection policy routine and affordable. Planetary protection is directed to 1) the control of terrestrial microbial contamination associated with robotic space vehicles intended to land, orbit, flyby, or otherwise be in the vicinity of extraterrestrial solar system bodies, and 2) the control of contamination of the Earth by extraterrestrial solar system material collected and returned by such missions. The implementation of these requirements will ensure that biological safeguards, to maintain extraterrestrial bodies as biological preserves for scientific investigations, are being followed in NASA's space program. Methods for the detection and reduction of biological contamination are also frequently applicable to non-biological particulate and molecular contamination. To fulfill its commitment, NASA seeks technologies and systems approaches that will support mission compliance with planetary protection requirements. Examples of such technologies include: * Techniques for cleaning of organics to the level of nanograms per square centimeter on complex surfaces (nondestructively and without residues) and for validation of cleanliness at this level or better; * Nonabrasive cleaning techniques for narrow aperture occluded areas on spacecraft; * Techniques for in situ (i.e., at the exploration site) cleaning and sterilization to prevent cross-contamination between planetary surface samples; * Nondestructive and highly efficient sampling methods for detection of the remnants of microbial, particles, and molecular contamination on cleaned spacecraft surfaces; * Methodology for the quantitative detection of viable microbial cells in the interior of non-metallic space-craft materials; * Rapid cleaning validation methods with ultra high sensitivity for the major classes of biomolecules: proteins, amino acids, DNA/RNA, lipids, polysaccharides, etc.; * A device or methodology for controlled measurement of microbial reduction at temperatures from 200-300°C to enable generation of microbial lethality curves. Rapid ramp-up and cool-down rates are critical to minimize the microbial killing that occurs during the ramp periods; * Device or methodology for direct observation and evaluation of particles and biological contamination on spacecraft parts; * Device or methodology for quantitative and homogeneous deposition of particles, microbial cells, and bio-molecules on material surfaces for cleaning, sampling, and contamination transport studies; * System design concepts to enable facile and rapid use of cleaning and sterilization technologies during flight hardware assembly; * System design concepts to maintain the integrity of cleaned and sterilized complex flight systems and/or subsystems; and * System concepts that would facilitate spacecraft sterilization at the system level just before launch or in flight. Research should be conducted to demonstrate technical feasibility during Phase 1 and to show a path toward a Phase 2 hardware and software demonstration. The research will, when possible, deliver a demonstration unit or software package for JPL testing before the completion of the Phase 2 contract. S1.02 Mars In Situ Robotics Technology Lead Center: JPL Participating Center(s): LaRC During future exploration of planets, moons, and small solar system bodies (such as comets and asteroids), developments are needed in new innovative robotic technologies for surface operations, subsurface access, and autonomous software for each. Because of limited spacecraft resources, elements must be robust and have low power, volume, mass, computation, telemetry bandwidth, and operational overhead requirements. Successful technologies will have to operate in environments characterized by extremes of temperatures, pressures, gravity, high-gravity landing impacts, vibration, and thermal cycling. In particular, this subtopic seeks technology innovations in the following areas: Subsurface Access Research should be conducted to develop complete, lightweight, dry drilling systems with a penetration depth of 10–50 m and have the capability of penetrating both regolith and rocks. The development should focus on significant reduction in mass from the currently available state-of-the-art interplanetary drilling systems as well as the automation required for real-time control and fault diagnosis and recovery. In addition, because of the lack of water in most of the environments of interest, the drilling should be performed without a lubricant between the bit and rock. Of interest also is the development of ice penetrators, designed with explicit consideration of limited computation and power, which use heat to melt their way through the surface. Rover Technology Long-range autonomous navigation systems that focus on long distance (greater than 5 km) traverses through natural terrain, using no a priori knowledge of the subject terrain. Inflatable rover technology with a focus on the development of low-mass, highly capable platforms for exploration of extreme terrain through innovations in novel mechanisms and the automation required for real-time control. Concepts for new mobility systems or components, such as innovative wheel or suspension designs. Instrument placement with a focus on improved tools for the design of manipulation systems, to perform contact and noncontact operations such as drilling, grasping, sample acquisition, sample transfer, and contact and noncontact science instrument placement and pointing. Modular robotic joints that are small (0.5 kg), low power, low mass and can be used to build prototype manipulators and/or legs. Quick changeout mechanisms for planetary manipulators that can enable changing of tools or instruments on the end of a manipulator. Of particular interest is infrastructure for research, including low-cost, mass producible, research-quality rovers and supporting elements. The development of a low-cost, Rocker-Bogie style, six-wheel steerable, robotic research platform that can drive around in rough terrain is desired. Research should be conducted to demonstrate technical feasibility during Phase 1 and show a path toward a Phase 2 hardware and software demonstration that will, when possible, deliver a demonstration unit or software package for JPL testing at the completion of the Phase 2 contract. S1.03 Long Range Optical Telecommunications Lead Center: JPL Participating Center(s): GRC, GSFC This subtopic seeks innovative technologies for long range optical telecommunications supporting the needs of space missions. Proposals are sought in the following areas: * Space-qualifiable, efficient (greater than 20% wall plug), lightweight, variable repetition-rate (1–60 MHz), tunable (± 0.1 nm) pulsed 1064-nm transmitter sources (diode-pumped fiber amplifier or bulk crystal la-ser/amplifier) with greater than 1 kW of peak power per pulse (over the entire pulse-repetition rate), and greater than 10 W of average power, and narrow (<10 pm) spectral width; * Space-qualifiable, high-peak power (> 1.2 W), average-power (> 300 mW), operating wavelength less than 1000 nm single-mode-fiber pigtailed laser diode transmitters (includes necessary modulator; internal or external driver) with narrow spectral width (< 100 pm) supporting 4-ary pulse-position-modulation for data rates of 0.5 - 1000 Mbps with high wall-plug electrical-efficiency (> 25%); * Space-qualifiable, reliable (> 3 years at 100 Mega photons per second continuous photon flux), photon counting 1064 nm and/or 1550 nm detectors with the gain greater than 1000, detection efficiency greater than 50%, very low (<0.1 MHz) additive noise, about 0.5 mm in diameter, bandwidth greater than 500 MHz, saturation levels >50Mcounts/s. and non-gated (continuous operation); * Lightweight, compact, high precision (less than 0.1 micro-radian), high bandwidth (0–2kHz), inertial reference sensors (angle sensors, gyros) for use onboard spacecraft; * Novel schemes for stray-light control and sunlight mitigation, especially for large (> 5 m) ground-based optical telescopes that must operate when pointed to within a few (about 3) degrees of the Sun; * Low-cost, lightweight, efficient, r pigtailed laser diode transmitters including compact, high precision (one micro-radian accuracy) star-trackers for spaceflight application that can be integrated with an optical communications terminal; * Novel techniques and technologies that will enable very low cost, large aperture (>5m equivalent aperture diameter) telescopes for ground or space-borne use; * High power ground-based, relatively low-cost diode-pumped laser technology capable of reaching 100 kW average power levels in a TEMoo mode, for uplink to spacecraft; * Artificial laser guide-star and beam compensation techniques capable of removing all significant atmospheric turbulence distortions (tilt and higher-order components) on an uplink laser beam; * Novel techniques to reduce the development cost and risk of future space-borne optical communications transceivers (e.g. automatic focusing or alignment techniques); * High BW Intersatellite Links (ISL) in Earth orbit and deep space ISL or possibly satellite to ground communications; and * Systems and technologies relating to sub-microradian pointing, acquisition, and spacecraft vibration. Research should be conducted to demonstrate technical feasibility during Phase 1 and show a path toward a Phase 2 hardware demonstration that will, when appropriate, deliver a demonstration unit for testing at the completion of the Phase 2 contract. S1.04 Entry, Descent and Landing Lead Center: JPL Participating Center(s): LaRC, ARC, JSC Entry, Descent, and Landing (EDL) systems are an enabling component of future planetary surface and airborne explorations. EDL systems are naturally comprised of a wide variety of tightly integrated subsystems. These subsystems can include, but are not limited to: entry body, thermal protection, avionics for guidance during entry and/or powered descent (including terrain sensors), aerodynamic decelerators including supersonic or subsonic parachutes, and touch-down systems. In addition to these hardware specific subsystems, algorithms for guidance and hazard detection are an integral element of future EDL systems. Innovations are sought that provide benefits in the following general areas: increased payload delivery mass, improved delivery accuracy, and improved hazard detection and avoidance. The intended outcome of these improvements is to develop the capability to land safely within 100m or less of a preselected landing site and to deliver larger payloads for future Mars missions. In particular, this subtopic seeks technology innovations in the following areas: * Entry body systems and subsystems including lightweight aeroshells and thermal protection; * Entry guidance algorithms/methods/techniques capable of reducing uncertainty in parachute deployment altitude, for missions employing bank-only control (i.e., no control of angle of attack) during hypersonic entry; * Aerodynamic decelerator systems including supersonic and subsonic parachutes. Particular areas of interest include approaches that hold promise for delivering increased mass to the surface (e.g., increasing the Mach-Q deployment envelope beyond Viking-heritage capability) and techniques of reducing the cost of testing/validating the performance of new aerodynamic decelerator systems for use at Mars. Also of interest are para-guidance techniques for pinpoint landing; * Terrain hazard detection approaches that provide real-time three-dimensional terrain mapping capability during parachute descent and powered terminal descent. In addition, compact, low-mass, high accuracy, and high bandwidth GNC sensors such as attitude and velocity sensors are highly desirable; and * Lightweight, low-cost, hazard-tolerant touchdown system approaches including (but not limited to) airbag, shock struts, and structural crush zones; allowing landings in moderately cratered terrains with surface rock distribution encountered over a wide variety of Martian landing sites. S1.05 Sample Return Technologies Lead Center: JPL Participating Center(s): JSC The NASA Mars Exploration Program has recently adopted a plan that includes a Mars Sample Return mission. Such a mission would require breaking the chain of contact with Mars: the exterior of the sample container must not be contaminated with unsterilized Mars material. One mission concept involves placing a grapefruit sized sample container in Mars orbit where it can be picked up by an orbiting spacecraft for return to Earth. Tenuous issues of contamination of the sample container exterior with Mars dust must be dealt with as well as contamination-free handling of the return sample in the receiving facility. Receiving Facility Sample Handling Technologies The items described briefly below would find eventual utilization in a sample receiving facility whose basic functions are to do physical and chemical characterizations, bio-hazard detection, and life detection, within a series of double-walled containment vessels. The facility would be operated with significant utilization of robotics, operated either in situ, or remotely, or both. * Demonstrate fine-scale manipulations, either in situ or remotely, of a strawman 6-axis ultra-clean robot within the confines of a double-walled containment vessel. The robot can be current state-of-art. Demonstrate the use of different end effectors to manipulate small samples for observation. The task may require use and/or modification of current state-of-the-art control software. * Demonstrate a sample container/carrier, possibly adapted from a container/carrier currently in use by semiconductor and/or pharmaceutical industries; that has the capability to be identified (labeled) and tracked, for use in cataloging, transporting, and tracking samples of various kinds; generally of approximately 100-micron size, and consisting of fines, dust, individual grains, and very small rocks, or gases; following the certification of these samples for release to a facility for long-term curation and distribution; * Develop double-walled gloves for use within a double-walled containment vessel. Such gloves would perhaps require self-healing and/or warning systems, in case of a breach, and be compatible with ports developed for double-walled containment vessels; and * Identify specific sterilization methods and techniques for use in sterilization of extraterrestrial samples. Determine the sterilization levels achieved for sample coupons defined and/or provided by a NASA-sponsored science/biosafety working group. Miniature Leak Detector Proposals are sought for the development of a miniature, low-mass, low-power leak detection sensor that can be used to indicate a loss of pressure from a container with a volume of 0.5 liter, that has a pressure of 6 torr, as expected on Mars. Areas of interest include: * A sensor, driver, and the power source designed for placement inside the container that is made of metal. The metal alloy that will be used will be determined at a later time; * The sensor and its control electronics that provides power, data processing, and communications should not exceed the volume of 5-cm3; * The device should be operational at temperatures that are as low as -70°C and as high as room temperature; and * A miniature battery as power source is acceptable. Preferably, a wireless power transfer mechanism and a rechargeable battery that is designed for placement inside the container, would be preferred. Sample Containerization and Protection Proposals are sought for the development of a robust method of sealing a sample that would be acquired from an extraterrestrial surface for possible return to Earth in future NASA missions. Areas of interest include: * A simple and reliable process of hermetically seaming and sealing a “coffee-cup” size container with a rock or soil sample; * The process needs to simultaneously perform sterilization of the container sealed area and its external surface while releasing the container into an area that simulates a clean section of a lander; * This process should “break-the-chain” of contact of an acquired soil or rock sample from the original area that simulates the environment of an extraterrestrial planet; * The required process needs to simultaneously seal the contained sample while destroying any potential biological materials that may contaminate the external surface of the container; * The process to sterilize the surface of a grapefruit-sized sample container in Mars orbit (e.g., pyrotechnic paint) requiring minimal power and minimizing effect on the sample container interior; * The contained sample should be protected from any mechanical, chemical, or thermal damage during or after the activation of the “break-the-chain” process; * The process needs to be computer simulated and allow a high degree of control of its parameters; and * Demonstrate probability of success of the feasibility to seal the container while performing sterilization. Sample Acquisition Proposals are sought for mechanisms to acquire clean core samples for Mars rocks and regolith including development of low-mass, low-normal-force, 10x1 cm coring tool, low-mass core sampling tool integrated with sample containment, acquire Mars dust samples, and development of six-axis force-torque sensor (ranges about 160 Newtons, 15 N-m) operating in Mars ambient. TOPIC: S2 Robotic Exploration Throughout the Solar System NASA's program for Solar System Exploration seeks to answer fundamental questions about the Solar System and life: How do planets form? Why are planets different from one another? Where did the makings of life come from? Did life arise elsewhere in the solar system? What is the future habitability of Earth and other planets? The search for answers to these questions requires that we augment the current remote sensing approach to solar system exploration with a robust program that includes in situ measurements at key places in the solar system, and the return of materials from them for later study on the Earth. We envision a rich suite of missions to achieve this including a comet nucleus sample return, a Europa lander, and a rover or balloon-borne experiment on Saturn's moon, Titan, to name a few. These robotic explorers will pursue compelling scientific questions, demonstrate breakthrough technologies, identify space resources, and extend an advanced telepresence that will send stunning imagery back to Earth. Numerous new technologies will be required to enable such ambitious missions. This topic includes investments in technology to enable the delivery and access of scientific instruments to planetary surfaces and atmospheres. This includes landing, flying, roving, and digging, as well as sample acquisition for delivery to instruments. This topic will also address Earth entry vehicles for sample return missions, planetary protection, and contamination control for in situ missions. The planetary bodies of interest are the Moon, Mars, Venus, Titan, and the icy satellites of the outer planets. S2.01 Science Instruments for Conducting Solar System Exploration Lead Center: JPL Participating Center(s): ARC This subtopic supports the development of advanced instruments and instrument technology to enable or enhance scientific investigations on future planetary missions. New measurement concepts, advances in existing instrument concepts, and advances in critical components are all of interest. Proposers are strongly encouraged to relate their proposed technology development to future planetary exploration goals. Instruments for both remote sensing and in situ investigations are required for NASA’s planned and potential solar system exploration missions. Instruments are required for the characterization of the atmosphere, surface, and subsurface regions of planets, satellites, and small bodies. These instruments may be deployed for remote sensing, on orbital or flyby spacecraft, or for in situ measurements, on surface landers and rovers, subsurface penetrators, and airborne platforms. In situ instruments cover spatial scales from surface reconnaissance to microscopic investigations. These instruments must be capable of withstanding operation in space and planetary environmental extremes, which include temperature, pressure, radiation, and impact stresses. Examples of instruments that will meet the goals include, but are not limited to, the following: * Instrumentation for definitive chemical, mineralogy, and isotopic analysis of surface materials: soils, dusts, rocks, liquids, and ices at all spatial scales, from planetary mapping to microscopic investigation. Examples include advanced techniques in reflectance spectroscopy, wet chemistry, laser-induced breakdown spectrometers, water and ice detectors, novel gas chromatograph and mass spectrometry, and age-dating systems; * Instrumentation for the assessment of surface terrain and features. Examples include lidar systems and advanced imaging systems; * Geophysical sensing systems to determine the near-surface and subsurface structure, textures, bulk components, and composition, such as seismic sensors, porosity measurement devices, permeameters, and surface penetrating radars; * Instruments and components that will rely on, and take advantage of, high power capabilities (up to 100 kW) for measurements of planetary surfaces. The instruments may make direct or indirect use of the power, long duration observations, or extremely high data rates; * Instrumentation focused on assessments of the identification and characterization of biomarkers of extinct or extant life, such as prebiotic molecules, complex organic molecules, biomolecules, or biominerals; * Instrumentation for the chemical and isotopic analysis of planetary atmospheres; * Advanced detectors for solar absorption spectrometry. One example is a detector that is fast and linear, i.e., does not saturate under high photon fluxes; * Environmental sensing systems, such as meteorological sensors, humidity sensors, wind and particle size distribution sensors, and sounders for atmospheric profiling; * Particles and fields measurements, such as magnetometers, and electric field monitors; and * Enabling instrument component and support technologies, such as laser sources, miniaturized pumps, sample inlet systems, valves, integrated bulk sample handling and processing systems, and fluidic technologies for sample preparation. Research should be conducted to demonstrate technical feasibility during Phase 1 and show a path toward a Phase 2 hardware and software demonstration, and when possible, deliver a demonstration unit or software package for JPL testing at the completion of the Phase 2 contract. S2.02 Extreme High Temperature/High Pressure Environment Lead Center: JPL Participating Center(s): GRC Proposals are sought for technologies to enable operation and survivability in high-temperature/high-pressure space environments. These technologies service the needs of the future in situ exploration of Venus as well as the atmospheric probes for giant planets. Venus features a dense, CO2 atmosphere completely covered by clouds with sulfuric acid aerosols, a surface temperature of 486şC, and a surface pressure of 90 atmospheres. Although already explored by various orbiters and short-lived atmospheric probes and landers, Venus retains many secrets pertaining to its formation and evolution. NASA is interested in expanding its ability to explore the deep atmosphere and surface of Venus through the use of long-lived (days or weeks) balloons and landers. Survivability in extreme high temperatures (380°C) and high pressures (>100 bar) is also required for deep atmospheric probes to giant planets. Technology needs for high-temperature and high-pressure environments include: * Advanced passive and active thermal control for Venus missions, including lightweight (50 kg/m3), high strength/stiffness, high buckling stress resistant pressure vessels to protect the electronics and instruments for several hours; new lightweight thermal insulation materials with conductivity less than 0.1 W/mK at 486şC, thermal storage systems with 300–1000 kJ/kg energy density, thermal switches with a switching ratio of at least 100:1 between “On” and “Off” modes, and high temperature heat pipe systems operating over a temperature range of 25 to 500şC. Refrigeration systems capable of pumping heat from a 25 to 75şC source to the Venus sink temperature of 486şC; * Science and engineering sensors able to operate at 486şC and 100 bar, including for example, high temperature imagers, hybrid imaging system that utilizes high temperature fiber optics, seismometers, and pressure sensors; * High-temperature, low-power, and ultra low-power electronics and electronic packaging technology for sensor and actuator interfaces at 486şC, including low-noise (10 nV/sqHz) preamplifiers, power amplifiers and transmitters (S-band), temperature stable oscillators, drivers (with 0–100 V digital output for driving piezoelectric, electrostatic, or electromagnetic actuators), and high value (on the order of one to hundreds of micro Farad) capacitors; * Computer Aided Design (CAD) tools for predicting the performance, reliability, and life cycle for high-temperature electronic systems and components; * High-temperature primary batteries (200 Whr/kg)) for operation at 380şC and 486şC; * Actuators for sample handling and acquisition systems including high-temperature drills, motors, and actuators able to operate in the 486şC, 90 atmosphere surface environment of Venus; and * Anticorrosive coatings to protect optical systems and spacecraft structures from corrosive agents present in the upper levels of Venus’ atmosphere (sulfuric acid clouds) or near surface (besides carbon oxide and nitrogen, the atmosphere contains sulfuric acid, hydrochloric acid, and hydrofluoric acid). Research should be conducted to demonstrate technical feasibility during Phase 1 and show a path toward a Phase 2 hardware/software demonstration, and when possible, deliver a demonstration unit or software package for JPL testing at the completion of the Phase 2 contract. S2.03 Nanosensors Lead Center: JPL Participating Center(s): ARC The subtopic seeks to leverage breakthroughs in the emerging fields of nano-technology and biotechnology to develop advanced sensors and actuators with increased sensitivity and small size for solar system exploration. Technologies should provide enhanced capabilities over the current state-of-the-art and be able to operate in an extreme environment. This harsh environment includes steady operation and cycling in the temperature range of -180 degrees Centigrade to 100 degrees Centigrade, and high radiation. Of particular interest are harsh environment-operable nanosystems for single molecule sensing and manipulation, on-chip biomolecular analysis, and semiconductor laser diodes in the 2-5 um wavelength range, and detectors in the greater than 15 um wavelength range. S2.04 Deep Space Power Systems Lead Center: GRC Participating Center(s): GSFC, JPL, JSC Innovative concepts using advanced technology are solicited in the areas of energy conversion, power electronics, and power system materials. Power levels of interest range from milliwatts to 1 KW. NASA Space Science missions in deep space environments require energy systems with long life capability, high radiation tolerance, reliability, and low overall costs (including operations) which can operate in high and low temperatures and over wide temperature ranges. Advanced technologies are sought in the following areas: Energy Conversion All proposed energy conversion technologies must be able to show substantial increases over state-of-the-art in efficiency and specific power (W/kg) and to operate in deep-space environments with high radiation and wide-temperature operations (-200°C to 300°C). Long-life (>14 years), highly reliable advanced energy conversion technologies are sought that keep manufacturability in mind. Advances in photovoltaic technology are sought, including high power solar arrays and ultra lightweight, thin film, and concentrator arrays. Advances in radioisotope thermal to electric power conversion technology (milliwatt/multiwatt and 100W-1KW classes with efficiencies (state-of-the-art) are sought. This includes advances in thermophotovoltaics, thermoelectrics, Brayton, Rankine, and Stirling technologies as well as compact heat exchangers. Innovative control methods are also sought. Power Electronics Advanced power electronic materials and devices for deep-space power systems are sought. The materials of interest include soft magnetics, dielectrics, insulation, and semiconductors. Devices of interest include transformers, inductors, electrostatic capacitors, high-power semiconductor switches and diodes, and integrated control and driver circuits. Proposed technologies must improve upon the following characteristics: high temperature operation (>200°C), low-temperature (cryogenic) operation, wide-temperature operation (-125°C to 200°C), and/or high levels of space radiation (>150 krad) resistance. Electronics Packaging and Materials Advanced electronics packaging technologies that reduce volume and mass capable of either high temperature, cryogenic, wide temperature operation, and/or space radiation resistance for use in space power systems are of interest. Advances are sought in power electronics packaging materials, surfaces, and components that are durable for soft X-ray, electron, proton, and ultraviolet radiation and thermal cycling environments. S2.05 Astrobiology Lead Center: ARC Participating Center(s): JPL Astrobiology includes the study of the origin, evolution, and distribution of life in the universe. New technologies are required to enable the search for extant or extinct life elsewhere in the solar system, to obtain an organic history of planetary bodies, to discover and explore water sources elsewhere in the solar system, and to detect microorganisms and biologically important molecular structures within complex chemical mixtures. Biomarkers produced by microbial communities are profoundly affected by internal biogeochemical cycling. The small spatial scales at which these biogeochemical processes operate necessitate measurements made using microsensors. The search for life on other planetary bodies will also require systems capable of moving and deploying instruments across, and through, varied terrain to access biologically important environments. A second element of Astrobiology is the understanding of the evolutionary development of biological processes leading from single-cell organisms to multi-cell specimens and to complex ecological systems over multiple generations. Understanding of the effects of radiation and gravity on lower organisms, plants, humans, and other animals (as well as elucidation of the basic mechanisms by which these effects occur) will be of direct benefit to the quality of life on Earth. These benefits will occur through applications in medicine, agriculture, industrial biotechnology, environmental management, and other activities dependent on understanding biological processes over multiple generations. A third component of Astrobiology includes the study of evolution on ecological processes. Astrobiology intersects with NASA Earth Science studies through the highly accelerated rate of change in the biosphere being brought about by human actions. One particular area of study with direct links to Earth Science is microbe–environment interactions. NASA seeks innovations in the following technology areas: * For Mars exploration, technologies that would enable to provide a broad survey of areas in the vicinities of a rover or lander to narrow a field of search for biomarkers; * For Mars exploration, technologies that (using X-ray, neutron, ultrasonic, and other types of tomography) would enable a noninvasive, nondestructive analysis of the subsurface environment and areas inside rocks and ice to depths 10–20 cm with spatial resolutions of 2–10 microns. Such technologies should provide the capability for analysis of structures inside opaque matrices created by endolithic organisms or fossil structures and possible elemental analysis of such structures; * Technologies that would enable the aseptic acquisition of deep subsurface samples, the detection of aquifers, or enhance the performance of long-distance ground roving, tunneling, or flight vehicles are required; * For Europa exploration, technologies to enable the penetration of deep ice are required; * Desirable features for both Mars and Europa exploration include the ability to carry an array of instruments and imaging systems, to provide aseptic operation mode, and to maintain a pristine research environment; * Low-cost, lightweight systems to assist in the selection and acquisition of the most scientifically interesting samples are also of significant interest; * High sensitivity, (femtomole or better) high-resolution methods applicable to all biologically relevant classes of compounds for separation of complex mixtures into individual components; * Advanced miniaturized sample acquisition and handling systems optimized for extreme environment applications; * High sensitivity (femtomole or better) characterization of molecular structure, chirality, and isotopic composition of biogenic elements (H, C, N, O, S) embodied within individual compounds and structures; * High spatial resolution (5 angstrom level) electron microscopy techniques to establish details of external morphology, internal structure, elemental composition, and mineralogical composition of potential biogenic structures; * Innovative software to support studies of the origin and evolution of life. The areas of special interest are (1) biomolecular and cellular simulations, (2) evolutionary and phylogenetic algorithms and interfaces, (3) DNA computation, and (4) image reconstruction and enhancement for remote sensing; * Technologies capable of measuring a range of volatile compounds at small spatial scales. Improved sensor designs for a wide range of analytes, including oxygen, pH, sulfide, carbon dioxide, hydrogen, and small molecular weight organic acids both on and near surfaces that could serve as habitats for microbes; * Biotechnology – determining mutation rates and genetic stability in a variety of organisms as well as accurately determining protein regulation changes in microgravity and radiation environments; * Automated chemical analytical instrumentation for determining gross metabolic characteristics of individual organisms and ecologies as well as chemical composition of environments; * Spectral and imaging technology with high resolution and low power requirements; * Habitat support – technologies for supporting miniature closed ecosystems, data collection, and transmission technologies in concert with the automated chemical instrumentation described above; * Miniature-to-microscopic, high-resolution, field-worthy, smart sensors, or instrumentation for the accurate and unattended monitoring of environmental parameters that include, but are not limited to, solar radiation (190–800 nm at <1 nm resolution), ions and gases of the various oxidation states of carbon and nitrogen (at the nanomolar level for ions in solution and at the femtomolar or better level for gases), in a variety of habitats (e.g., marine, freshwater, acid and alkaline hot springs, and permafrost); * High-resolution, high-sensitivity (femtomole or better) methods for the isolation and characterization of nucleic acids (DNA and RNA) from a variety of organic and inorganic matrices; * Mathematical models capable of predicting the combined effects of elevated pCO2 (change in CO2 over the eons) and solar UV radiation on carbon sequestration and N2O emissions from experimental data obtained from field and laboratory studies of C-cycling rates, N-cycling rates, as well as diurnal and seasonal changes in solar UV; * Microscopic techniques and technologies to study soil cores, microbial communities, pollen samples, etc., in a laboratory environment for the detailed spectroscopic analysis relevant to evolution as a function of climate changes; and * Robotic systems designed to provide access to environments such as deep-ocean hydrothermal vents. S2.06 Advanced Flexible Electronics Lead Center: JPL Electronically steerable L-band, phased array antennas are needed for missions to the Moon, Mars, Titan, and Venus. L-band provides the capability to detect surface and subsurface topology including ice or features hidden by the surface dust. Flexible, lightweight active arrays enable better packaging efficiency for the antenna and are critical for these missions. Currently, manufacturing reliable passive arrays with required tolerances is challenging and the only method for integration of the electronics is to attach and interconnect the electronic components on the surface. This method is expensive, unreliable, and impractical for large arrays. Technologies enabling large area flexible antennas, including flexible electronics, are needed. State-of-the-art, flexible, printable electronics have low switching frequencies. Innovative new materials or processes will be needed to enable devices that can handle the gigahertz frequencies needed for radar. In addition, large area manufacturing methods are needed to manufacture these passive and active antennas. Research should be conducted to demonstrate technical feasibility during Phase 1 and show a path toward a Phase 2 hardware and software demonstration, and when possible, deliver a demonstration unit or software package for JPL testing at the completion of the Phase 2 contract. S2.07 Risk Modeling and Analysis Lead Center: JPL Participating Center(s): LaRC The purpose of this subtopic is to advance the state-of-the-art in risk modeling and analysis, particularly for use in early design (formulation) phases. Of particular interest would be methods for risk characterization and modeling that extend beyond typical technical aspects, including software, programmatic, operations, organization, and management elements. This subtopic includes tools and methods, visualization techniques, and process enhancements. Technical areas to address include: * Uncertainty modeling including both epistemic and aleatory uncertainties; * Attribute-driven risk identification; * Risk reduction modeling that includes both preventative and mitigative activities; * Methods for aggregation and/or integration of quantitative and qualitative risks; * Methods for characterization and integration of software, organizational, operations, and other non-physics based risks; * Integration of risks and risk insights into the trade and formal design processes, including new techniques for risk visualization and new methods for directly trading risk against other design aspects; * Development of risk model library elements and techniques for selecting, maintaining, and integrating the elements; * Methods for cost-effective adaptation and utilization of PRA and other probabilistic methods in early design (e.g., conceptual design) which can be integrated directly into the design process (i.e., can be utilized directly by the system designers without additional analyst support); and * Methods for risk-based margin determination and management. TOPIC: S3 Astronomical Observatories to Seek Earth-like Extrasolar Planets and Environments The NASA Science Missions Directorate seeks to conduct advanced telescope searches for Earth-like planets and habitable environments around neighboring stars. This topic will consider technologies necessary to enable future telescopes and observatories collecting all electromagnetic bands, ranging from X-rays to millimeter waves, and also include gravity waves. The subtopics will consider all technologies associated with the collection and combination of any observable signals. S3.01 Precision Formations for Interferometry Lead Center: JPL This subtopic seeks hardware and software technologies necessary to establish, maintain, and operate hyper-precision spacecraft constellations to a level that enables separated spacecraft optical interferometry. Also sought are technologies for analysis, modeling, and visualization of such constellations. In a constellation for large effective telescope apertures, multiple, collaborative spacecraft in a precision formation collectively form a variable-baseline interferometer. These formations require the capability for autonomous precision alignment and synchronized maneuvers, reconfigurations, and collision avoidance. It is important that, in order to enable precision spacecraft formation keeping from coarse requirements (relative position control of any two spacecraft to less than 1 cm, and relative bearing of 1 arcmin over target range of separations from a few meters to tens of kilometers) to fine requirements (micron relative position control and relative bearing control of 0.1 arcsec), the interferometer payload would still need to provide at least 1–3 orders of magnitude improvement on top of the S/C control requirements. The spacecraft also require onboard capability for optimal path planning and time optimal maneuver design and execution. Innovations that address the above precision requirements are solicited for distributed constellation systems in the following areas: * Integrated optical/formation/control simulation tools; * Distributed, multi-timing, high fidelity simulations; * Formation modeling techniques; * Precision guidance and control architectures and design methodologies; * Centralized and decentralized formation estimation; * Distributed sensor fusion; * RF and optical precision metrology systems; * Formation sensors; * Precision microthrusters/actuators; * Autonomous reconfigurable formation techniques; * Optimal, synchronized, maneuver design methodologies; * Collision avoidance mechanisms; * Formation management and station keeping; and * Six degrees of freedom precision formation test beds. S3.02 High Contrast Astrophysical Imaging Lead Center: JPL Participating Center(s): ARC This subtopic addresses the unique problem of imaging and spectroscopic characterization of faint astrophysical objects that are located within the obscuring glare of much brighter stellar sources. Examples include, planetary systems beyond our own and the detailed inner structure of galaxies with very bright nuclei. Contrast ratios of one million to one billion over an angular spatial scale of 0.05–1.5 arcsec are typical of these objects. Achieving a very low background against which to detect a planet requires control of both scattered and diffracted light. The failure to control either amplitude or phase fluctuations in the optical train severely reduces the effectiveness of any starlight cancellation scheme. This innovative research focuses on advances in coronagraphic instruments, interferometric starlight cancellation instruments, and potential occulting technologies that operate at visible and infrared wavelengths. The ultimate application of these instruments is to operate in space as part of a future observatory mission. Much of the scientific instrumentation used in future NASA observatories for the Origins Program theme will be similar in character to instruments used for present day space astrophysical observations. The performance and observing efficiency of these instruments, however, must be greatly enhanced. The instrument components are expected to offer much higher optical throughput, larger fields of view, and better detector performance. The wavelengths of primary interest extend from the visible to the thermal infrared. Measurement techniques include imaging, photometry, spectroscopy, coronography, and polarimetry. There is interest in component development, and innovative instrument design, as well as in the fabrication of subsystem devices to include, but are not limited to, the following areas: Starlight Suppression Technologies * Advanced starlight canceling coronagraphic instrument concepts; * Advanced aperture apodization and aperture shaping techniques; * Pupil plane masks for interferometry; * Advanced apodization mask or occulting spot fabrication technology controlling smooth density gradients to 10-4 with spatial resolutions ~1 µm; * Metrology for detailed evaluation of compact, deep density apodizing masks, Lyot stops, and other types of graded and binary mask elements. Development of a system to measure spatial optical density, phase inhomogeneity, scattering, spectral dispersion, thermal variations, and to otherwise estimate the accuracy of masks and stops is needed; * Interferometric starlight cancellation instruments and techniques to include aperture synthesis and single input beam combination strategies; * Fiber optic spatial filter development for visible coronagraph wavelengths; * Single mode fiber filtering from visible to 20-µm wavelength; * Methods of polarization control and polarization apodization; and * Components and methods to insure amplitude uniformity in both coronagraphs and interferometers, specifically materials, processes, and metrology to insure coating uniformity. Wavefront Control Technologies * Development of small stroke, high precision, deformable mirrors (DM) and associated driving electronics scalable to 104 or more actuators (both to further the state-of-the-art towards flight-like hardware and to explore novel concepts). Multiple DM technologies in various phases of development and processes are encouraged to ultimately improve the state-of-the-art in deformable mirror technology. Process improvements are needed to improve repeatability, yield, and performance precision of current devices; * Reliability and qualification of actuators and structures in deformable mirrors to eliminate or mitigate single actuator failures; * Multiplexer development for electrical connection to deformable mirrors that has ultra-low power dissipation. The most promising DM technology may be sensitive to temperature, so developing a MUX that has very low thermal hot spots, and very uniform temperature performance will improve the control of the mirror surface; and * High precision wavefront error sensing and control techniques to improve and advance coronagraphic imaging performance. S3.03 Precision Deployable Lightweight Cryogenic Structures for Large Space Telescopes Lead Center: JPL Participating Center(s): MSFC Planned future NASA Origins Missions and Vision Missions such as the Single Aperture Far-IR (SAFIR) telescope, Life Finder, and Submillimeter Probe of the Evolution of Cosmic Structure (SPECS), require 10–30 m class telescopes that are diffraction limited at wavelengths between the visible and the near IR, and operate at temperatures from 4–300 K. The desired areal density is 3–10 kg/m2. Wavefront control may be either passive (via a high stiffness system) or active control. Potential architecture implementations must package into an existing launch volume, deploy and be self-aligning to the micron level. The environment is expected to be L2. This topic solicits proposals to develop enabling component and subsystem technology for these telescopes in the areas of precision deployable structures, i.e., large deployable optics manufacture and test; innovative concepts for packaging integrated actuation systems; metrology systems for direct measurement of the structure; deployment packaging and mechanisms; active control implemented on the structure (downstream corrective and adaptive optics are not included in this topic area); actuator systems for alignment (2 cm stroke actuators, lightweight, submicron dynamic range, nanometer stability); mechanical and inflatable deployable technologies; new thermally-stable materials for deployables; new approaches for achieving packagable structural depth; etc. The goal for this effort is to mature technologies that can be used to fabricate 20 m class, lightweight, cryogenic flight-qualified telescope primary mirror systems. Proposals to fabricate demonstration components and subsystems with direct scalability to flight systems (concept described in the proposal) will be given preference. The target volume and disturbances, along with the estimate of system performance, should be included in the discussion. A successful proposal shows a path toward a Phase 2 delivery of demonstration hardware on the scale of 3 m for characterization. S3.04 Large-Aperture Lightweight Cryogenic Telescope Components and Systems Lead Center: MSFC Participating Center(s): JPL, GSFC Planned future NASA infrared, far infrared, and submillimeter missions, such as the Single Aperture Far-IR (SAFIR) telescope, Interferometric Terrestrial Planet Finder (TPF-I), Infrared Origin's Probes, Space Infrared Interferometric Telescope (SPIRIT), and Submillimeter Probe of the Evolution of Cosmic Structure (SPECS) require both 10–30 m and 2–4 m class telescopes that are diffraction limited at 5–20 mm and operate at temperatures from 4–10 K. The desired areal density is 3–10 kg/m2. Wavefront control may be either passive (via a high stiffness system) or active control (via mechanisms and deformable mirrors). Potential architecture implementations include 2 m class segments, 4 m class mirrors, or membrane systems. Component and system testing techniques are a particular challenge for low areal density or cryogenic specific architectures. It is anticipated that active cooling will be required. Potential telescope system architectures require transporting 1 W of heat at 15 K with 5 W/K, while others require 100 mW at 4 K with 1 W/K. This topic solicits proposals to develop enabling component and sub-system technology for cryogenic telescopes, including but not limited to: large-aperture lightweight cryogenic optic manufacture and test; thermal management, distributed cryogenic cooling and multiple heat lift; structure, deployment, and mechanisms; deployable cryogenic coolant lines; active wavefront control; etc. The goal for this effort is to mature technologies that can be used to fabricate 2–4 m and 10–30 m class lightweight cryogenic flight-qualified telescope primary mirror systems at a cost of less than $300,000 per square meter. Proposals to fabricate demonstration components and subsystems with direct scalability to flight will be given preference. TOPIC: S4 Exploration of the Universe Beyond Our Solar System The Universe division of the NASA/GSFC is charged with exploring the universe beyond the solar system – out to its very edges. To do this, requires ever more powerful missions (beyond Chandra, Spitzer, and Hubble) with larger and better optics and detector systems. Future mission may include optics that fold and deploy and can be assembled on orbit, as well as larger arrays of detectors, bolometers, microcalorimeters (superconducting), and room temperature semiconductors. Our missions cover the full range of the electromagnetic spectrum and gravitational waves. Some of our major science goals are to identify dark matter, to understand dark energy, to produce a census of black holes, to image material in the accretion disks around black holes, and to measure gravitational waves from a wide range of sources. In addition, we are exploring new technologies for sub-orbital platforms including long duration balloons, tethered balloons, and airships. We are soliciting ideas and concepts in six areas covering optical systems, UV, visible, IR and sub-mm detectors, X-ray and Gamma-ray detectors, lasers for gravitational wave measurements, and sub-orbital platforms. The subtopics in this area are described in detail in each subtopic section. S4.01 Infrared and Sub-mm Sensors and Detectors Lead Center: JPL Participating Center(s): MSFC NASA astrophysics missions currently under development, such as Sofia, Herschel, and Planck (http://science.hq.nasa.gov/missions/phase.html) have been enabled by improvements in sensors and detectors. Beyond 2007, expected advances in detectors, readout electronics, and other technologies, particularly those enabling polarimetry and large format imaging arrays for the far IR/submm and spectroscopy with unprecedented sensitivity. These advances may enable future mission concepts such as the Single Aperture Far Infrared (SAFIR) Observatory (http://safir.jpl.nasa.gov/technologies/index.asp), SPICA (http://www.ir.isas.ac.jp/SPICA/), and CMBPOL. Space science sensor and detector technology innovations are sought in the following areas: Mid/Infrared, Far Infrared and Submillimeter Future space-based observatories in the 10-40 micron spectral regime will be passively cooled to about 30 K. They will make use of large, sensitive detector arrays with low-power dissipation array readout electronics. Improvements in sensitivity, stability, array size, and power consumption are sought. In particular, novel doping approaches to extend wavelength response, lower dark current and readout noise, novel energy discrimination approaches, and low noise superconducting electronics are applicable areas. Future space observatories in the 40 micron to 1 mm spectral regime will be cooled to even lower temperatures, frequently <10 K, greatly reducing background noise from the telescope. In order to take advantage of this potentially huge gain in sensitivity, improved far infrared/submillimeter detector arrays are required. The goal is to provide noise equivalent power less than 10-20 W Hz-1/2 over most of the spectral range in a 100x100 pixel detector array with low-power dissipation array readout electronics. The ideal detector element would count individual photons and provide some energy discrimination. For detailed line mapping (e.g., C+ at 158 micron), heterodyne receiver arrays are desirable, operating in the same frequency range near the quantum limit. Space Very Long Baseline Interferometry (VLBI) The next generations of VLBI missions in space will demand greatly improved sensitivity over current missions. These new missions will also operate at much higher frequencies (at first to 86 GHz and eventually to 600 GHz). These thrusts will require development of improved space-borne, low-power, ultra-low-noise amplifiers and mixers to serve as primary receiving instruments. S4.02 Terrestrial and Extra-Terrestrial Balloons and Aerobots Lead Center: GSFC Participating Center(s): JPL Innovations in materials, structures, and systems concepts have enabled buoyant vehicles to play an expanding role in NASA's Science Mission Directorate and Exploration Systems Mission Directorate. A new generation of large, stratospheric balloons, based on advanced balloon envelope technologies, will be able to deliver payloads of several thousand kilograms to above 99.9% of the Earth's absorbing atmosphere and maintain them there for months of continuous observation. NASA is seeking innovative and cost-effective solutions in support of terrestrial balloons in the following areas: * Innovative concepts for reducing the UV degradation of flight components including balloon membranes, load carrying members, and parachute components; * Innovative concepts for the measurement of strain in a thin film during flight; * Innovative sensor concepts for balloon gas or skin temperature measurements; * Innovative concepts for trajectory control and/or station keeping for effectively maneuvering large terrestrial balloons in either the horizontal latitude or vertical altitude plane or both; * Innovative low-mass, high-density, and high-efficiency power systems for terrestrial balloons that produce 2 kW or more continuously; * Innovative power systems that enable long duration, sunlight independent missions for durations of 30 days or more; * Innovative floatation systems for water recovery of payloads; * Innovative guided or gliding parachutes systems for use in thin atmospheres; * Innovative balloon design concepts for long duration missions that can provide any or all of the following: reduced material strength requirements, increased reliability, enhanced performance, reduced manufacturing time, reduced manufacturing cost, or improved mission flexibility; and * Smaller scale, but similarly designed, balloons and airships will also carry scientific payloads on Mars, Venus, Titan, and the outer planets in order to investigate their atmospheres in situ and their surfaces from close proximity. Their envelopes will be subject to extreme environments and must support missions with a range of durations. Proposals are sought in the following areas: Aerobot Surface Sample Acquisition Device NASA is soliciting concepts and prototypes for surface sample acquisition devices that can be used on aerobots to collect icy material from Titan and Mars. Typical sample volumes range from 1 to 2 cubic centimeters, with preference for a solid ice core as well as possible granular material. Collection depths of 0 to 2 cm are desired. Preferred techniques do not require close proximity of the aerobot balloon skin to the ground to reduce the probability of damaging the vehicle during sample acquisition. Examples include tethered collection devices deployed from modest altitudes (10s to 100s of meters) or short duration “touch and go” sampling from directional and/or altitude controlled aerobots. Proposed devices can be disposable (single use), but if reusable must avoid cross-contamination between samples. All devices must include solid sample transfer functionality to an analysis chamber on the aerobot itself. Concepts will be preferred that feature low mass (few kilograms or less), small volume (~1 liter) and low electrical power consumption drawn from the aerobot (<10 W) devices. Apex Valve for Montgolfiere Balloons Solar-heated Montgolfiere balloons are an attractive platform for the exploration of Mars, particularly the polar regions which experience long periods of solar illumination during summer solstice. These balloons can be altitude controlled through selective venting of the heated gas through a valve located at the apex of the balloon. Proposals are sought for concepts and prototypes for this valve to be used on a solar-heated balloon on Mars. Typical specifications include large flow area (10 m2), low mass (few kilograms), packaged into a small volume for transport to Mars (<0.1 m3) and consume minimal electrical energy (<5 W). Aerial Deployment Modeling Tool Planetary aerobots at Mars, Titan, and Venus will likely be aerially deployed and inflated during parachute descent after arrival at the destination. Proposals are sought that would provide computer modeling tools that can simulate this complex process. Of particular importance is the ability to model the balloon shape and material stresses as a function of time, taking into account the aerodynamic forces generated by the parachute and by the uninflated or partially inflated balloon, as well as transient loads during balloon deployment from its storage container. The balloons can be either polymer films or polymer film plus reinforcing fabric laminates. Metal Bellows for High Temperature Venus Balloons Cylindrically-shaped metal bellows are a potential solution to the problem of making balloons that can tolerate the 460°C temperatures near the surface of Venus. Commercial off-the-shelf metal bellows are limited in diameter to approximately 0.4 m. NASA seeks proposals for metal bellows technology that can produce prototypes in the range of 1-2 m in diameter and 5-10 m long; tolerant of sulfuric acid; good fatigue properties at 460°C; and areal densities of up to 1 kg/m2. S4.03 Cryogenic Systems for Sensors and Detectors Lead Center: GSFC Participating Center(s): JPL, MSFC Stored cryogenic systems have long been used to perform cutting edge space science, but at high cost and with a limited lifetime. Improvements in cryogenic system technology enable further scientific advancement at lower cost, lower risk, reduced volume, and/or reduced mass. Lifetime, reliability, and power requirements of the cryogenic systems are critical performance concerns. Of interest are cryogenic coolers for cooling detectors for scientific instruments and sensors on advanced telescopes and observatories as well as lunar and planetary exploration. The coolers should have long life, low vibration, low mass, low cost, and high efficiency. Specific areas of interest include: * Highly efficient coolers in the range of 4-10 Kelvin as well as at 50 milli-Kelvin and below, and cryogen-free systems which integrate these coolers together; * Highly reliable, efficient, low-cost Stirling and pulse tube cooler technologies in the 15 Kelvin and 35 Kelvin regions; * Essentially vibration-free cooling systems such as reverse Brayton cycle cooler technologies; * Highly efficient magnetic and dilution cooling technologies, particularly at very low temperatures; * Hybrid cooling systems that make optimal use of radiative coolers; and * Miniature, MEMS, and solid-state cooler systems. S4.04 Optics and Optical Telescopes (including X-Ray, UV, Visual, IR) Lead Center: GSFC Participating Center(s): JPL, MSFC With the reorganization of NASA activities into the Exploration Mission Directorate (EMD) and the Space Mission Directorate (SMD), there is a renewed call for novel optical technologies that extend the state-of-the-art across wavelength bands from far-IR to Gamma-ray. Missions to study the Earth and Sun, the other solar system planets and objects, and the origins and fate of the universe are proposed to operate from low Earth orbit to L2 or drift-away trajectories depending on their system of study and environmental requirements. Among other areas of study, future planet finder missions will require lightweight optical apertures of tens of square meters with sub-nanometer surface figure errors. Infrared versions will require cooling optics to cryogenic temperatures (to 4 K). Telescopes studying the Sun and its environment in the UV and EUV (20-300 nm wavelength) require novel optical coatings and filters, high precision aspheric optics, and high-density uniform and variable line density diffraction gratings. And high-energy X-ray telescopes will study the origins and fate of the universe with <10 arcsec resolution and effective areas of square meters. Many of these missions have apertures so large that they will require multiple spacecraft to fly in formation, either to combine their optical apertures or to perform sparse interferometric observations. For all missions, low-mass optics and deployment structures are extremely important. Also, wavefront sensing and control systems are sought that may alleviate the stringent mass and stiffness requirements of such large optics. Finally, advanced, low-cost manufacturing, metrology, and modeling techniques will be required to make these missions possible. The previous year's Optical Technologies (S2.04) and UV and EUV Optics (S1.06) have been merged to form this year's Optics and Optical Telescopes subtopic. All previously relevant areas of research are invited in this new subtopic including: Optics * Ultra-smooth (2–3 Angstroms rms) replicated optics that are rigid and lightweight; * Lightweight, high modulus (e.g., silicon carbide) optics and structures; * Ultra-stable optics over time periods from minutes to hours; * Cryogenic optics, structures, and mechanisms for space telescopes and interferometers; * High-performance, diamond turned optics (including freeform optical surfaces); * Large, thin, ultra-lightweight grazing incidence optics for X-ray mirrors with angular resolutions less than 5 arcsec. (>100 cm2, <1 mm thick, and <10 kg/m2 areal density); * Wide field-of-view optics using square pore slumped microchannel plates or equivalent; * Large, ultra-lightweight optical mirrors (<1 kg/m2 at near-IR through visible), including membrane optics for very large aperture space telescopes and interferometers; * UV and EUV Imaging mirrors with simultaneously large aperture (1-4 m diameter), low mass (5-20 kg/m2), accurate figure (~0.01 wave rms or better at 632 nm), and low micro-roughness (<1 nm @ <1 mm period). Figure accuracy must be maintained through launch and on-orbit (including, for mirrors subjected to direct or concentrated solar radiation, the effects of differential heating); and * Smooth sub-mm scale image slicer and microlens array component technologies to allow fabrication of integral field spectrographs in the UV and visible, for simultaneous spectroscopy of two spatial dimensions and one spectral dimension. Filters * Large area, thin blocking filters with high efficiency at low energy X-ray energies (<600 eV); * Ultraviolet filters with deep blocking (<1 part in 105) of longer and shorter wavelengths, including "solar blind" performance; novel near- to far-IR filters with increased bandwidth, stability, and out-of-band blocking performance; * FUV and EUV coatings (filters) with improved reflectivity (transmission) and selectivity (narrow bands, broad bands, or edges). Technologies include multilayers, transmission gratings, and Fabry-Perot etalons, among others; and * Improved X-ray and Gamma-ray modulation optics and coded aperture masks (sub-arcsecond resolution at 10 keV to 10 arcsecond resolution at 1 MeV). Gratings * Fabrication techniques for ultra-thin-flat silicon (or like material) for grating substrates for X-ray energies <0.5 keV; * High resolving power diffraction gratings (>4000 lines/mm) at acceptable focal lengths and pixel sizes; and * Improvements in grating manufacturing technologies, such as high efficiency/low scatter gratings, variable line spacing, improved echelle gratings, active grating surfaces (gratings replicated onto deformable substrates), and gratings ruled onto concave, aspheric surfaces. Metrology * Low-cost, high quality, large optics fabrication processes and test methods including active metrology feedback systems during fabrication, and artificial intelligence controlled systems; * Portable and miniaturized state-of-the-art optical characterization instrumentation and rapid, large-area surface-roughness characterization techniques are needed. Calibrated processes for determination of surface roughness using replicas made from the actual surface. Traceable surface roughness standards suitable for calibrating profilometers over sub-micron to millimeter wavelength ranges are needed; and * Instruments capable of rapidly determining the approximate surface roughness of an optical surface, allowing modification of process parameters to improve finish, without the need to remove the optics from the polishing machine. Techniques for testing the figure of large, convex, aspheric surfaces to fractional wave tolerances in the visible. Wavefront Sensing and Control * Optical systems with high-precision controls, active and/or adaptive mirrors, shape control of deformable telescope mirrors, and image stabilization systems; and * Advanced, wavefront sensing and control systems including image based wavefront sensors; * Nanometer to sub-picometer metrology for space telescopes and interferometers. Optical Design * Advanced analytical models, simulations, and evaluation techniques, and new integrations of suites of existing software tools allowing a broader and more in-depth evaluation of design alternatives and identification of optimum system parameters including optical, thermal, structural, and dynamic performance of large space telescopes and interferometers. S4.05 Sensor and Detector Technology for UV, X-Ray, Gamma-Ray and Cosmic-Ray Instruments Lead Center: GSFC Participating Center(s): MSFC The next generation of astrophysics observatories for the infrared, ultraviolet (UV), X-ray, and Gamma-ray bands require order-of-magnitude performance advances in detectors, detector arrays, readout electronics, and other supporting and enabling technologies. Although the relative value of the improvements may differ among the four energy regions, many of the parameters where improvements are needed are present in all four bands. In particular, all bands need improvements in spatial and spectral resolutions in the ability to cover large areas and in the ability to support the readout of the thousands to millions of resultant spatial resolution elements. Innovative technologies are sought to enhance the scope, efficiency, and resolution of instrument systems at all energies and wavelengths: * The next generation of gravitational missions will require greatly improved inertial sensors. Such an inertial sensor must provide a carefully fabricated test mass, which has interactions with external forces (i.e., low magnetic susceptibility, high degree of symmetry, low variation in electrostatic surface potential, etc.) below 10–16 of the Earth's gravity, over time scales from several seconds to several hours. The inertial sensor must also provide a housing for containing the proof mass in a suitable environment (i.e., high vacuum, low magnetic and electrostatic potentials, etc.); * Advanced Charged Couple Device (CCD) detectors, including improvements in UV quantum efficiency and read noise, to increase the limiting sensitivity in long exposures and improved radiation tolerance. Electron-bombarded CCD detectors, including improvements in efficiency, resolution, and global and local count rate capability. In the X-ray, we seek to extend the response to lower energies in some CCDs, and to higher, perhaps up to 50 keV, in others; * Significant improvements in wide band gap (such as GaN and AlGaN) materials, individual detectors, and arrays for UV applications; * Improved microchannel plate detectors, including improvements to the plates themselves (smaller pores, greater lifetimes, alternative fabrication technologies, e.g., silicon), as well as improvements to the associated electronic readout systems (spatial resolution, signal-to-noise capability, and dynamic range), and in sealed tube fabrication yield; * Imaging from low-Earth orbit of air fluorescence, UV light generated by giant airshowers by ultra-high energy (E >1019 eV) cosmic rays require the development of high sensitivity and efficiency detection of 300–400 nm UV photons to measure signals at the few photon (single photo-electron) level. A secondary goal minimizes the sensitivity to photons with a wavelength greater than 400 nm. High electronic gain (~106), low noise, fast time response (<10 ns), minimal dead time (<5% dead time at 10 ns response time), high segmentation with low dead area (<20% nominal, <5% goal), and the ability to tailor pixel size to match that dictated by the imaging optics. Optical designs under consideration dictate a pixel size ranging from approximately 2 x 2 mm2 to 10 x 10 mm2. Focal plane mass must be minimized (2 g/cm2 goal). Individual pixel readout. The entire focal plane detector can be formed from smaller, individual sub-arrays; * For advanced X-ray calorimetry improvements in several areas are needed, including: - Superconducting electronics for cryogenic X-ray detectors such as SQUID-based amplifiers and their multiplexers for low impedance cryogenic sensors and superconducting single-electron transistors and their multiplexers for high impedance cryogenic sensors. - Micromachining techniques that enhance the fabrication, energy resolution, or count rate capability of closely-packed arrays of X-ray calorimeters operating in the energy range from 0.1–10 keV; and - Surface micromachining techniques for improving integration of X-ray calorimeters with read-out electronics in large-scale arrays. * Improvements in readout electronics, including low-power ASICs and the associated high-density interconnects and component arrays to interface them to detector arrays; * Superconducting tunnel junction devices and transition edge sensors for the UV and X-ray regions. For the UV, these offer a promising path to having "three-dimensional" arrays (spatial plus energy). Improvements in energy resolution, pixel count, count rate capability, and long wavelength rejection are of particular interest. We seek techniques for fabrication of close-packed arrays, with any requisite thermal isolation, and sensitive (SQUID or single electron transistor), fast, readout schemes and/or multiplexers; * Arrays of CZT detectors of thickness 5–10 mm to cover the 10–500 keV range, and hybrid detector systems with a Si CCD over a CZT pixelated detector operating in the 2–150 keV range; * For improvements to detector systems for solar and night-time UV and EUV (approx. 20–300nm) observing. the following areas are of interest: large format (4 K x 4 K and larger); high quantum efficiency; small pixel size; large well depth; low read noise; fast readout; low power consumption (including readout); intrinsic energy and/or polarization discrimination (3d or 4d detector); active pixel sensors (back-illumination, UV sensitivity); and high-resolution image intensifiers, UV and EUV sensitive, insensitive to moisture; * Space spectroscopic observations in the UV, visible, and IR requiring long observation times would be much more sensitive with high quantum efficiency (QE) and zero read noise. Techniques are sought which improve the QE of photon counters, or eliminate the read noise of solid-state detectors; and * X-ray and Gamma-ray imaging with higher sensitivity, dynamic range and angular resolution requires innovations in modulation collimators and detection devices. The energy range of interest is from a few kilo-electron Volts to hundreds of milli-electron Volts for observations of solar flares and cosmic sources. Collimators with size scales down to a few microns and thicknesses commensurate with photon absorption over a significant fraction of this energy range are required. Low-background detectors capable of <~keV energy resolution, with or without spatial resolution, are required to record the modulated photon flux. The ability to measure fluxes over a wide dynamic range. The capability to determine the polarization of the photon flux is also desirable. S4.06 Technologies for Gravity Wave Detection Lead Center: GSFC Participating Center(s): JPL, MSFC Laser Technologies for Gravitational Wave Detection NASA is now developing the Laser Interferometer Space Antenna (LISA) mission to search for gravitational waves from astrophysical phenomena such as the Big Bang, mergers of supermassive black holes, and galactic binary inspirals. Detection of gravitational waves would open a new astrophysical window on the universe with great potential for unexpected discoveries. A number of gravitational wave follow-on missions to LISA are also under study. The disturbance caused by the passage of a gravitational wave is expected to be very small (of order picometers) and will be measured with laser interferometry. The technology areas below deal with technical problems in these measurements. Because the systems will be deployed in space, the technologies to be considered must have credible paths toward space flight qualification. Background information on LISA, along with preliminary technology discussions, can be found in the Proceedings of the 5th International LISA Symposium, , Penn State University, 19-24 JULY 2002, published in the Classical and Quantum Gravity Journal, Vol 20, Number 10, 21 May 2003. Issues of Space Qualification of LISA Laser: the LISA laser must produce >1W CW of 1.06 micron light with fiber coupled output (for example, a combination of a lower-power master oscillator {eg, NPRO} with suitable amplifier). The laser will have the following characteristics: * 10 year lifetime; * Power stability <0.1% (10 Hz to 2 MHz); and * Linewidth <5 kHz (over 1 msec). This task will involve investigating the issues of space qualification of the system, experimentally studying the relevant problems, and proposing a realistic plan of development of this system. Given the magnitude of the effort to develop a space qualified LISA laser, it is not expected that the outcome of this task will result in a space qualified laser; rather, the outcome should be a sufficient understanding of the important technical issues in space qualification (e.g., diode lifetime, thermal and vibrational robustness, etc.) so that a clear path towards the development of a fully space qualified system can be identified. LISA Electro-optical Modulator: produce a phase modulator for a 1 W continuous laser beam, providing 10% power modulation depth at frequencies from 1.9 to 2.1 GHz. The modulator should be fiber coupled (input and output), at 1.06 micron wavelength. The modulator must be space qualified. LISA Telescope Articulator: produce a mechanical actuator that can articulate the LISA telescope over a 5 mm dynamic range with a 0.1 nm resolution. The actuator must be space qualified and have noise <0.01 nm. TOPIC: S5 Sun-Solar System Connection The strategic priorities of the Sun-Solar System Connection derive from a stated NASA Strategic Objective, namely: “Explore the Sun-Earth system to understand the Sun and its effects on Earth, the solar system, and the space environmental conditions that will be experienced by human explorers, and demonstrate technologies that can improve future operational systems.” SSSC has identified three science and exploration objectives. The program will provide the knowledge needed to: 1) open the frontier to space environment prediction: understand the fundamental physical processes of the space environment – from the Sun to Earth, to other planets, and beyond to the interstellar medium; 2) understand the nature of our home in space: understand how society, technological systems, and the habitability of planets are affected by the variable space environment; 3) safeguard our outbound journey: maximize the productivity and safety of human and robotic explorers by developing predictive capability for the extreme and dynamic conditions in space. S5.01 Low Thrust and Propellantless Propulsion Technologies Lead Center: MSFC Participating Center(s): GRC, GSFC, JPL, JSC, LaRC Spacecraft propulsion technology innovations are sought for upcoming deep-space science missions. Propulsion system functions for these missions include primary propulsion, maneuvering, planetary injection, and planetary descent and ascent. Innovations are needed to reduce spacecraft propulsion system mass, volume, and/or cost. Applicable propulsion technologies include advanced chemical, solar sails, aerocapture, and emerging technologies. Advanced Chemical Propulsion Innovations in low-thrust chemical propulsion system technologies are being sought for deep-space, scientific, robotic mission applications. Delta Vs for the missions of interest range from 1000 m/sec to 3000 m/sec. Technologies of interest are bipropellant engines with Isp greater than 360 seconds, both pressure-fed and pump-fed, with chamber pressures ranging from 100 to 500 psia. Throttling capability is desired for engines used for planetary ascent, descent, and orbit insertion maneuvers. Passive long-term storage (greater than 5 years) for advanced bipropellant propulsion systems for deep space missions are of interest. Reliable ignition systems are needed for non-hypergolic propellants. Activities in development of lightweight, compact, and low-power propellant management components, such as valves, flow control/regulation, fluid isolation, and lightweight tankage are also solicited. Advanced materials to allow development of systems for use with advanced bipropellants (higher Isp, higher pressure) are also solicited. Solar Sail Propulsion Solar sails have been studied for a variety of missions and have the potential to provide cost-effective, propellantless propulsion that enables longer on-station operation, increased scientific payload mass fraction, and access to previously inaccessible orbits (e.g., non-Keplerian, high solar latitudes, etc.). NASA missions enabled and enhanced by solar sail propulsion include those that can provide: 1) situational awareness for human and robotic exploration in the Earth-Moon system (e. g., Heliostorm, L1 Diamond); 2) comprehensive monitoring of the inner heliosphere (e.g., Solar Sentinels, Solar Polar Imager, Particle Acceleration Solar Observatory); and 3) pathfinder exploration beyond the solar system (Interstellar Probe). The technology required for these missions can further be classified into two categories: 1) near-term (<15 years) for use in orbits that are between 0.9 AU and 0.5 AU with a propulsive area of greater then 1 x 104 m2; and 2) far-term (>15 years) for use in orbits at <0.25 AU with a propulsive area of greater then 1 x 105 m2. A solar sail propulsion system includes the sail membrane and support structure, the thrust vector control subsystem, the health and monitoring diagnostic subsystem, and the launch stowage structure. Three parameters that are used as sail performance metrics in mission applications are: sail size, sail durability in its orbital environment, and areal density (ratio of sail system mass to propulsive area of the sail). In addition, important programmatic metrics are cost, benefit, and risk. Innovations are sought that will lower the cost and risk associated with sail system development through advancements in: manufacturing, fabrication, and assembly; durable lightweight materials, structures, and mechanisms; comprehensive simulations of maneuvering, navigation, trajectory control, propulsive performance, and operations; and integrated diagnostic health monitoring. Tether Technologies This effort focuses on technologies supporting innovative and advanced concepts for propellantless propulsion based upon space tethers concepts. The categories under Tether Technologies include, but are not limited to: ElectroDynamic (ED) tether propulsion, Momentum eXchange Electrodynamic Reboost (MXER) tethers or its subsystems, Jovian tether mission concepts, Earth orbiting telescope ED tether reboost, and other innovative in space tether technologies. In general, the electrodynamic tether propulsion method exchanges momentum with a planet's rotational angular momentum through electrodynamic interaction with the planetary magnetic field. Momentum exchange tethers or MXER concepts use orbital energy to provide a high thrust to a payload in LEO. Distinctive variations of existing propulsion methods or chief subsystem component improvements are also suitable for submission. Proposals should provide the development plan of specific innovative technologies or techniques supporting the planned research. Identification of the fundamental technology to be developed is also crucial. A clear plan for demonstrating feasibility, noting any test and experiment requirements, is recommended. Key to each idea is an unambiguous knowledge of past research/concepts conducted on related work and specifically how this new proposal differs from, or enhances, the existing tether roadmaps, particularly for robotic mission support. Aeroassist Aeroassist is a general term given to various techniques to maneuver a space vehicle within an atmosphere using aerodynamic forces in lieu of propulsive fuel. Aeroassist systems enable shorter interplanetary cruise times, increased payload mass, and reduced mission costs. Subsets of aeroassist are aerocapture and aerogravity assist. Aerocapture relies on the exchange of momentum with an atmosphere to achieve a decelerating thrust leading to orbit capture. This technique permits spacecraft to be launched from Earth at higher velocities, thus providing a shorter overall trip time. At the destination, the velocity is reduced by aerodynamic drag within the atmosphere. Without aerocapture, a substantial propulsion system would be needed on the spacecraft to perform the same reduction of velocity. Aerogravity assist is an extension of the established technique of gravity assist with a planetary body to achieve increases in interplanetary velocities. Aerogravity assist involves using propulsion in conjunction with aerodynamics through a planetary atmosphere to achieve a greater turning angle during planetary fly-by. In particular, this subtopic seeks technology innovations that are in the following areas: Aerocapture Thermal Protection Systems: development of advanced thermal protection systems and insulators for planetary aerocapture. Low Temperature/High Temperature Adhesives Trade Study: aerocapture inflatable decelerators are currently proposed to be manufactured from thin film materials and/or high temperature fabrics, stowed during transport, and inflated prior to atmospheric entry for aerocapture applications at planetary destinations. * Prior to the aerocapture maneuver, the inflatable decelerator will be stowed for many years (up to 10) in an uncontrolled space environment (-130oC) during transport to outer solar system destinations; * Before atmospheric entry, the inflatable decelerator will be unstowed and inflated; and * During the aerocapture maneuver, up to 24 hours after the inflation process, the inflatable decelerator will experience temperatures to 500oC (or higher). Conduct a thorough study of the adhesives trade space and select and test adhesive candidates that will maintain bond strength during the temperature extremes and long-term space exposure experienced by inflatable decelerators. The product of this study will be a report thoroughly documenting sample preparation, test procedures, and test results of all materials investigated. This report will be disseminated to inflatable decelerator developers. S5.02 Accommodation and Mitigation of Space Environmental Effects Lead Center: GSFC Participating Center(s): GRC, JPL, KSC, MSFC This subtopic is concerned with improving the capability to accommodate or mitigate the effects of the space environment on spacecraft design and operations. It will achieve its goal by designing and building flight investigations, developing models, collecting data from investigations in space and from ground tests, and analyzing data to improve the models, tools, and/or databases used for spacecraft design and operations. The resulting products will reduce the design margins and uncertainties in the induced environment definition (i.e., the environment in the presence of a spacecraft) and its effects on spacecraft design and operations. The environments to be considered include planetary-trapped radiation, solar proton events, cosmic rays, the plasma environment at planets and in the solar wind, magnetic fields, EUV/VUV, and the interplanetary meteoroid environment. The investigations selected have the opportunity to be integrated on the Space Environment Testbed (SET) Carrier. The SET Project opportunities for flight will be in orbits other than LEO. Investigations do not need to fly with the SET Carrier if an investigator makes arrangements for other access to space. Examples of investigations and models that would satisfy those requirements are described below. A more detailed description, with examples of investigation needs, can be found at: http://lws-set.gsfc.nasa.gov/Opportunities.htm. Areas for which proposals are sought include: * Characterization of the space environment, both natural and induced, in the vicinity of a spacecraft; * Definition of the mechanisms for material and materials applications degradation and the performance characterization of materials (such as coatings, optical properties, composites, etc.) in the space environment; * Accommodation and/or mitigation of charging/discharging effects on spacecraft and spacecraft components; * Methods for performance improvement of radiation tolerance of microelectronics used in space, including reduction of single event upsets and other single particle-induced soft errors, and elimination of single event latch-ups and other single particle-induced destructive conditions; * Development of novel methods for increasing crew safety and system performance relative to the effects of the natural space environment; and * Development of novel methods of increasing ground-based systems performance and reliability by reducing the effects of the natural space environment on those systems (e.g., space environment-induced soft errors in the power grid). S5.03 Technologies for Particles and Fields Measurements Lead Center: GSFC The SEC theme encompasses the Sun with its surrounding heliosphere carrying its photon and particle emissions and the subsequent responses of the Earth and planets. This requires remote and in situ sensing of upper atmospheres and ionospheres, magnetospheres and interfaces with the solar wind, the heliosphere, and the Sun. Improving our knowledge and understanding of these requires accurate in situ measurements of the composition, flow, and thermodynamic state of space plasmas and their interactions with atmospheres, as well as the physics and chemistry of the upper atmosphere and ionosphere systems. Remote sensing of neutral atoms are required for the physics and chemistry of the Sun, the heliosphere, magnetospheres, and planetary atmospheres and ionospheres. Because instrumentation is severely constrained by spacecraft resources, miniaturization, low power consumption, and autonomy are common technological challenges across this entire category of sensors. Specific technologies are sought in the following categories. Plasma Remote Sensing (e.g., neutral atom cameras) This may involve techniques for high-efficiency and robust imaging of energetic neutral atoms covering any part of the energy spectrum from 1 eV to 100 keV, within resource envelopes less than 5 kg and 5W. * Miniaturized, radiation-tolerant, autonomous electronic systems for the above, within resource envelopes of 1–2 kg and 1–2 W. In Situ Plasma Sensors * Improved techniques for imaging of charged particle (electrons and ions) velocity distributions as well as improvements in mass spectrometers in terms of smaller size or higher mass resolution; * Improved techniques for the regulation of spacecraft floating potential near the local plasma potential with minimal effects on the ambient plasma and field environment; * Low power, digital, time-of-flight analyzer chips with subnanosecond resolution and multiple channels of parallel processing; and * Miniaturized, radiation-tolerant, autonomous electronic systems for the above, within resource envelopes of 1–2 kg and 1–2 W. Fields Sensors * Improved techniques for measurement of plasma floating potential and DC electric field (and by extension, the plasma drift velocity), especially in the direction parallel to the spin axis of a spinning spacecraft; * Measurement of the gradient of the electric field in space around a single spacecraft or cluster of spacecraft; * Improved techniques for the measurement of the gradients (curl) of the magnetic field in space local to a single spacecraft or group of spacecraft; * Direct measurement of the local electric current density at spatial and time resolutions typical of space plasma structures such as shocks, magnetopauses, and auroral arcs; and * Miniaturized, radiation-tolerant, and autonomous electronic systems for the above within resource envelopes of 1–2 kg and 1–2 W. Electromagnetic Radiation Sensors * Radar sounding and echo imaging of plasma density and field structures from orbiting spacecraft; and * Miniaturized, radiation-tolerant, and autonomous electronic systems for the above within resource envelopes of 1–2 kg and 1–2 W. TOPIC: S6 Earth-Sun System Instrument and Sensor Technology NASA's Earth-Sun Systems (ESS) Division is committed to studying how our global environment is changing. Using the unique perspective available from spaceborne and airborne platforms, NASA is observing, documenting, and assessing large-scale environmental processes with emphasis on atmospheric composition, climate, carbon cycle and ecosystems, the Earth's surface and interior, the water and energy cycles, and weather. A major objective of ESS instrument development programs is to implement science measurement capabilities with small or more affordable spacecraft so development programs can meet multiple mission needs and therefore make the best use of limited resources. The rapid development of small, low-cost remote sensing and in situ instruments is essential to achieving this objective. Consequently, the objective of this SBIR topic is to develop and demonstrate instrument component and subsystem technologies that reduce the risk, cost, size, and development time of Earth observing instruments and to enable new Earth observations measurements. The following subtopics are concomitant with this objective and are organized by measurement technique. S6.01 Passive Optics Lead Center: LaRC Participating Center(s): ARC, GSFC, MSFC The following technologies are of interest to NASA in the remote sensing subtopic “passive optics.” Passive optical remote sensing generally requires that deployed devices have large apertures and large throughput. NASA is interested primarily in instrument technologies suitable for aircraft or space flight platforms, and these inherently also prefer low mass, low power, fast measurement times, and a high degree of robustness to survive vibrations in flight or at launch. Wavelengths of interest range from ultraviolet through the far infrared. Development of techniques, components and instrument concepts that can be developed for use in actual deployed devices and systems within the next few years is highly encouraged. Technologies and components that are not clearly suitable for use in high throughput remote sensing instruments are not applicable to this subtopic. Technical and scientific leads at NASA have given careful consideration to the technology areas described below; responses are solicited for these topics. * Technology leading to visible/NIR narrowband optical filters exhibiting greatly improved degradation properties over existing filters and minimal spectral drift for long-term space-based applications; * Technology leading to significant improvements in capability of large format (>1 inch diameter), very narrow band (<5 cm-1 full-width at half-maximum [FWHM]), polarization insensitive, high-throughput infrared (0.7–15 µm) optical filters; * Large format (>1 inch diameter), high-transmission, far infrared filters. Technology and techniques leading to filters operating at wave numbers between 500 and 5 cm-1 with FWHM less than 2 cm-1 are of immediate interest, though technology leading to very high transmission edge filters (long and short pass) is also solicited. The filters must be capable of operating in a vacuum at cryogenic temperatures; and * High-performance, four-band two-dimensional (2D) arrays (128x128 elements) in the 0.4 – 2.5 µm wavelength range with high quantum efficiencies (60%–80% or higher) in all spectral bands, low noise, and ambient temperature operation. S6.02 Lidar Remote Sensing Lead Center: LaRC Participating Center(s): GSFC High spatial resolution, high accuracy measurements of atmospheric parameters from ground-based, airborne, and spaceborne platforms, require advances in the state-of-the-art lidar technology with emphasis on compactness, reliability, efficiency, low weight, and high performance. Innovative technologies that can expand current measurement capabilities to airborne, spaceborne, or Unmanned Aerial Vehicle (UAV) platforms are particularly desirable. Development of components that can be used in actual deployed systems within the next few years is highly encouraged. Technologies and components that are not clearly suitable for effective lidar remote sensing or field deployment are not applicable to this subtopic. This subtopic considers components that enable Earth-sun system measurements such as: * Cloud and aerosols with emphasis on aerosol optical properties; * Wind profiles using direct-detection lidar, or coherent-detection (heterodyne) lidar, or both; * Land topography (vegetation, ice, land use); and * Molecular species (ozone, water vapor, and carbon dioxide). Innovative component technologies that directly address the measurement needs above will be considered. Dual-use technologies addressing Planetary Exploration are highly desirable (see subtopics X1.03 and S1.04). For the PY05 SBIR, we are soliciting component technologies described below. 1. Pulsed, single frequency, diode-based seed laser MOPA systems are desired due to inherent robustness, efficiency, thermal and alignment stability. If the cost per unit is reasonable, and the size is small, then many of these can be installed on a spacecraft for either parallel operation or as backup units to lengthen the life of the mission. Systems with the following specifications are solicited: * Single frequency 1064 nm operation. * Small, pinned package(s) that can generate CW powers in the 100's of mW and higher pulse powers yielding at least 10 nJ pulse energies. * Gaussian pulsewidths between 100 ps and 5 ns. * MOPA design configuration is desired where the pulse production cavity is short and more readily impedance matched for the fast rise times, gain switching, etc. * A semiconductor amplifier, or possibly a small cm-scale Yb:fiber amplifier, can be coupled to the oscillator chip’s output, itself contained in a hermetic butterfly or similar package. * Repetition rates as low as 100 Hz and as high as 10 kHz is needed, with pulsed lifetimes in the trillion shot regime (1012). * Single mode, PM fiber output is needed. * Short term drift less than 1 MHz. 2. CW, dual frequency, diode-based seed laser systems are desired for high power solid-state laser cavity feedback and locking at 1064 nm. If two wavelengths are produced, one must be 1064 nm and another single wavelength 5 nm or more offline (in either direction). Systems with the following specifications are solicited: * Simultaneous dual frequency operation; 1064 nm and a second wavelength at least 5 nm (either plus or minus) from 1064 nm. * Small, pinned package(s) that can generate CW powers in the 100s of mW and higher pulse powers. * CW output powers of >10 mW in each wavelength. Individual tunability is not required, but tunability of the 1064 nm output is required. * Dual PM, single mode fiber output is desired, but not absolutely required. * 5 MHz or less short term drift over 30 sec. 3. Efficient and compact single frequency solid state or fiber lasers operating at 1.5 and 2.0 micron wavelength regimes. Suitable for coherent lidar applications, these lasers must meet the following general requirements: pulse energy 2 mJ to 100 mJ, repetition rate 10 Hz to 200 Hz, and pulse duration of approximately 200 nsec. 4. Shared aperture, angle-multiplexed holographic or diffractive optical elements having several fields of view, each with angular resolution of 50 µrad or better for the Nd:YAG or Nd:YLF laser harmonics, and diffraction limited resolution for the Ho:YLF fundamental wavelength. Wide, flat, focal planes with low off-axis aberrations is of importance to terrain and vegetation mapping lidar applications. Hybrid designs using both 2053 nm or 1064 nm and 355 nm simultaneously are needed for dual wavelength Doppler wind lidar applications. Materials and technologies are needed that can be scaled up to 1 m apertures and larger and space qualified. Designs using lightweight materials, such as composites or membranes and deployable folded architectures, are also desired to decrease system size and weight. 5. Novel, high-power laser diodes capable suitable for pumping Holmium-based solid state lasers: * Quasi-CW laser diode arrays operating in 1939 nm or 1906.8 nm wavelengths with pulse duration of at least 1 msec, peak power in 10s watts regime, and duty cycle of greater than 2%; * Quasi-CW fiber-coupled laser diode pump arrays operating in 785 nm or 792 nm wavelengths with pulse duration of at least 1 msec, peak power in 100s watts regime, and duty cycle of greater than 2%; and * CW fiber-coupled laser diode pump arrays operating in 1939 nm or 1906.8 nm wavelengths. 6. Lightweight, compact lidar telescopes operating at one or more of the primary laser wavelengths in 1.0 to 2.0 micron wavelength region. The general requirements are: optical quality better than 1/6 wave at 632 nm, mass density less than 12