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NASA 2006 SBIR Phase 1 Solicitation

PROPOSAL NUMBER:	06-I A1.01-9056
SUBTOPIC TITLE:	Vehicle-Centric 4D Trajectory and Mission Management
PROPOSAL TITLE:	MILP-Based 4D Trajectory Planning for Tactical Trajectory Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aurora Flight Sciences Corporation
9950 Wakeman Drive
Manassas, VA 20110-2702

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Paduano
jpaduano@aurora.aero
One Broadway, 14th Floor
Cambridge,  MA 02142-1187

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aurora Flight Sciences proposes to develop specialized algorithms and software decision-aiding tools for four-dimensional (4D) vehicle-centric, tactical trajectory management (TTM), derived from algorithms developed at the Massachusetts Institute of Technology (MIT) to perform similar functions in military scenarios. These algorithms, based on the concept of receding horizon mixed-integer linear programming (RH-MILP), will be specifically tailored to the problem of optimizing the trades between multiple 4D trajectories (4DTs) in the dynamic airspace environment. In particular, the innovation that Aurora proposes is to model and address the stochastic nature of weather and associated airspace and resource restrictions in the flight path, respecting the fact that the time horizon over which sufficiently accurate weather estimates are available may be short compared to the overall TTM request-assign-update cycle (as envisioned by planners of the Next Generation Air Transportation System). The general problem of increasing uncertainty as planning horizons increase will be a central focus of algorithm development. This innovation addresses the needs for rapidly accommodating dynamic changes in aircraft tactical situations and responding to detected external hazards, for introducing any-time planning algorithms, and for generation and specification of 4D trajectories. Currently algorithms that directly address these needs in the context of the NGATS concept of operations (CONOPS) are in the early development stages; technology transition from related military approaches as described herein will therefore greatly benefit the state of the art in national airspace system (NA) operational tools.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application for our TTM decision-aiding software is the Next Generation Air Transportation System. Aurora also expects the software to be developed, or derivatives thereof, to have capabilities in the area of vehicle management in the NAS, which will lead to other applications within NASA. Given Aurora's specialization in UAV systems, applications of specific interest will include situations involving ferrying and/or operate UAVs in the NAS. This vision is consistent with Aurora's strategic plan to continue to evolve from a company that primarily provides unmanned aerial vehicles (UAVs), to one that provides unmanned aircraft systems (UASs). Increased levels of autonomy in our vehicles, as well as increased levels of operability in the NAS, is focus for future UAVs, which will benefit from the algorithms that Aurora will develop here.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other applications for MILP-based planning tools abound. Multi-vehicle planning in experimental, fire response, and homeland security applications will benefit from some of the core algorithms to be brought to bear in this program. Aurora also foresees the opportunity to play a role in flight-deck automation. Since the current proposal is focused on 4DT generation and assignation from the perspective of air traffic management, the focus is on the multi-vehicle problem. Understanding how this problem is posed and solved will provide insight into the best methods for creating and updating flight plans on the flight deck. This is important when vehicles are performing autonomous (a.k.a. 'free flight') operations, and will also streamline NGATS operations, because of compatibilities on the flight deck versus centralized TTM planners.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Guidance, Navigation, and Control
Autonomous Reasoning/Artificial Intelligence
Expert Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing, NJ 08618-2302

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Keller
jeff@continuum-dynamics.com
34 Lexington Avenue
Ewing,  NJ 08618-2302

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes a system for detecting upset conditions and providing the corresponding control recovery actions to maintain flight integrity for general application to aircraft. To maintain and improve aircraft safety as air capacity grows as part of the Next Generation Air Transportation System (NGATS), it is necessary to address the primary causes leading to in-flight loss of control accidents, including aircraft upsets, degraded flight operations, and environmental disturbance effects. A model-based upset detection and recovery control architecture is proposed that combines fault detection algorithms to identify the onset of an upset condition with optimal and near-optimal control responses. On-line parameter identification algorithms are used to adapt the core detection and recovery algorithms for degraded flight operations and/or modeling uncertainties. Distributed MEMS-based sensing and SMA-driven control effectors are used to augment the installed aircraft state measurements and control capability for rapid detection of and recovery from upset conditions. During Phase I, preliminary system design and application to a small unmanned aircraft will be performed, including flight test demonstration of the upset detection and control algorithms and hardware. This work will form the foundation for subsequent development of a family of aircraft upset mitigation systems for both manned and unmanned aircraft.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary outcome of this research and development will be control algorithms and flight hardware that will provide for the detection and mitigation of aircraft upset conditions. Aircraft upsets, which may occur due to degraded flight conditions, aerodynamic disturbances, and environmental effects, are a common cause of in-flight loss-of-control accidents. Potential NASA applications of this technology include development of an aircraft upset warning system, flight director, or flight control law, which will address NASA goals of improving safety attributes of new and legacy air vehicles, in particular key metrics such as fatal aircraft accident rates. Applications will also be found in supporting NASA unmanned aircraft operations by enhancing reliability and expanding science mission capability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to improving safety of existing and future manned aircraft, the results of this research and development will also benefit unmanned aviation. Detection and mitigation of upset conditions for unmanned air vehicles (UAVs) will directly impact military operations in which UAV accident rates are one to two orders of magnitude greater than for manned aircraft. Furthermore, by decreasing the susceptibility of UAVs to upset-induced losses through increased autonomy, a significant hurdle impeding public acceptance of UAV operations in the civil airspace will be overcome, opening the door for commercial and civil applications of unmanned aircraft systems.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Pilot Support Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nastec, Inc.
5310 West 161st Street , Suite G
Brook Park, OH 44142-1610

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Klein
dickc123@earthlink.net
5310 West 161st Street , suite G
Brook Park,  OH 44142-1610

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
It is proposed to develop an accurate in-service aircraft engine life monitor system for the prediction of remaining component and system life for aircraft engines. Once proven in the aircraft engine environment, this life monitoring system will be used in a wide variety of airborne and land-based air-breathing engine systems. The aircraft engine life monitoring system will include three separate algorithms: an in-flight service monitoring algorithm, a pre-flight and post flight engine analysis algorithm, and a component-life tallying algorithm. The in-flight service monitor will treat the engine as a whole in response to sampling data of torque, speed, temperature and time. The engine analysis algorithm will determine the engines' operation parameters from those of its components. It also will determine the life and reliability of individual components based on the service monitoring algorithm's output. The component-life algorithm will accumulate life and reliability tables. The Phase I effort will develop the life-monitoring and supporting life-estimation and reliability algorithms. In Phase II effort, the full life-estimating system will be specifically tailored, assembled and tested with a commercial aircraft engine.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The work is in support of NASA's aircraft long-range goals. It impacts every aspect of safety and integrated resilient aircraft control. The successful completion of this project can improve aviation safety, reliability, and mitigation of failure. It will affect cost-effective design and manufacturing for new production engines and can reduce life cycle and maintenance costs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The cost-effective, reliable use of expansive aerospace and land-based air-breathing engine systems can be extended with more accurate knowledge of the remaining component and system fatigue life. By improving the in-service life estimation associated with these devices, longer reliable service life can be obtained. The high cost associated with surprise failures and unscheduled emergency maintenance procedures can be reduced substantially with the use of an in-service life monitor such as one proposed herein.

TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data Management
Pilot Support Systems
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Database Development and Interfacing
Expert Systems
Portable Data Acquisition or Analysis Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-0807

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Ward
barron@bainet.com
1410 Sachem Place, Suite 202
Charlottesville,  VA 22901-2559

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed SBIR Phase I plan of research seeks to develop and demonstrate an integrated architecture designed to compensate for combined propulsion, airframe, effector, and structural damage caused by catastrophic system failure or an intentionally hostile act. Whereas prior damage-adaptive control work focused on reconfiguring from unforeseen aerodynamic changes (e.g., effector or airframe damage), the proposed damage-adaptive control approach also accounts for the current health of the propulsion systems and key structural elements. The integrated controller merges available system identification and diagnostic information to compute a new "safe" operating envelope for the vehicle that accounts for identified changes in structural integrity/dynamics. Once this envelope is computed, the controller then proceeds to compute (1) an achievable flight path for landing the aircraft, and (2) a set of inceptor (or effector) and propulsion commands that will track the computed achievable reference trajectory in a decoupled way – all the while assuring that, if physically possible, the aircraft will not excite dangerous structural modes or create structural loads that would risk further damage. The research will also investigate advisory and retrofit implementations of the proposed approach that will enable early V&V and implementation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology directly addresses the IRAC element of the NASA Aviation Safety Program. Additionally, by integrating structural health monitoring with inner- and outer-loop control, the approaches developed here would also be suitable for life extending control (i.e., using effector redundancy to minimize wear on key structural elements). Finally, the technology is directly applicable to NASA's space exploration mission in that it provides trajectory generation and control algorithms that are capable of compensating for unforeseen failures or massive uncertainties in atmospheric conditions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The immediate Non-NASA application is algorithms, software, and tools for the civil aviation industry. Additionally, the technology is well suited for high-level autonomous operations of unmanned vehicles (air and otherwise). The proposer has an excellent track record transitioning algorithms of this nature for industry for use in commercial and defense-related applications.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Guidance, Navigation, and Control
On-Board Computing and Data Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
RHAMM Technologies, LLC
332 Skyland Drive
Bellbrook, OH 45305-8717

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ronald Hinrichsen
Hinrichsen@RHAMM.com
332 Skyland Drive
Bellbrook,  OH 45305-8717

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's Integrated Resilient Aircraft Control (IRAC) Project, Preliminary Technical Plan Summary identifies several causal and contributing factors that can lead to loss of aircraft control. Among these are adverse conditions and uncommanded motions which may be the result of vehicle or propulsion system failures or damage. One possible source of projectile damage is uncontained engine debris. This proposal focuses on development of a robust methodology for predicting the damage to aircraft structures from uncontained engine debris. The two objectives of this phase of the work proposed are: 1. Development of rigorous criteria and methodology for determining projectile sizes, shapes, velocities, and weights resulting from uncontained engine debris. 2. Research and development of techniques to predict realistic damage sizes and shapes resulting from projectile impacts on aircraft structure. The Phase I SBIR is intended to be a proof of concept and demonstration of the feasibility of interfacing UEDDAM with LSDYNA. One of the main products of the effort will be to well prepared plan for proceeding to Phase II. Whereas the Phase I product will be a proof of concept, it will not be ready for commercialization. It will be a prototype that does not have the user-friendly features such as graphical user interface (GUI). Nor will it have the ability to account for composite materials in the target. Thus the Phase II effort will focus on these two issues.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This product has direct application to NASA's Integrated Resilient Aircraft Control (IRAC) Project. As the IRAC project evolves, RHAMM feels that realistic damage states will be critical to the success of the overall program, since simulation will necessarily be a large part of it. Furthermore, as wind tunnel testing is being planned and executed, these realistic damage states and sizes will be important in bounding the problem and in leading the fabrication of experimental models. The UEDDAM-LSDYNA interface will be an integral part of the IRAC modeling and simulation effort. RHAMM also believes that the UEDDAM-LSDYNA interface could contribute greatly to NASA's Integrated Vehicle Health Management (IVHM) Program. Specifically, we believe that it would have application on the objective that states: "Diagnose coupled degradation/malfunction/failure/hazard conditions and predict their effects on vehicle safety" and the approach that states: "Couple state awareness data with physics-based and data-driven models to diagnose degradation and damage caused by environmental hazards and electro/thermo/mechanical failures."

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Upon successful completion of the Phase II SBIR, we will have a stand alone UEDDAM-LSDYNA interface code that we will offer to International (if approved), Commercial, FAA, DHS, and DoD (and their contractors) for use in damage effects modeling of aircraft structures. Strategies for penetrating these markets will be tailored to their specific needs. We envision generating a CD-ROM with specific examples of how the product can benefit potential customers in both commercial and government applications. Military, commercial, and dual use implementation will be highlighted and used as a strong selling point.

TECHNOLOGY TAXONOMY MAPPING
Structural Modeling and Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
JENTEK Sensors, Inc.
110-1 Clematis Avenue
Waltham, MA 02453-7013

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Washabaugh
jentek@shore.net
110-1 Clematis Avenue
Waltham,  MA 02453-7013

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposed program will focus on life management needs for new and emerging composite material systems and built-up structures in "young" aircraft. Both wide area inspection of fuselage and wing structures and characterization of adhesive bonds in built-up structures are addressed. JENTEK will develop both (1) hybrid methods in which spatially registered, digital images, produced by two or more sensing modalities are combined, and (2) a new method called Magneto-Thermography, invented by JENTEK, which offers both wide area inspection advantages and potential for characterization of adhesive bonds in built-up composite and metal structures. In one implementation of a hybrid method for graphite fiber/epoxy composites, the MWM-Array could sense and locate fiber damage and fiber movement under loads, while thermography could sense both fiber and matrix damage, allowing discrimination between fiber breakage, fiber/matrix disbonding, matrix cracking, and disbonding in built-up structures. Magneto-Thermography will use the demonstrated capability of the MWM-Array to monitor temperatures of buried fibers and to monitor temperatures at buried interfaces to replace IR cameras with MWM-Arrays in thermographic methods. This will enable both wide area inspection of thick composites and enhanced characterization of adhesive bonds in built-up structures, for foam layers, and other aerospace and space applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Magneto-thermography and hybrid methods have the potential to provide revolutionary capabilities for condition assessment and life management of composite components and adhesive bonds. Composite components and adhesive bonds will play an increasingly important role in aircraft and spacecraft. Effective life management will require advances in nondestructive test methods to provide information on composite component health and usage states. Magneto-thermography and the hybrid methods proposed here have the potential to enable significant advances in life management for composites for both aircraft and spacecraft, reducing life cycle costs and increasing safety margins.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Advanced life management tools for composite aircraft components will play a major role in fleet life cycle management practices. These will include advances in (1) sensing material condition, (2) modeling material behavior and predicting future behavior, and (3) decision support tools. Magneto-Thermography and Hybrid Methods can provide a more complete picture of composite condition. Both commercial and military fleets will require advanced inspection and life management tools for controlling life cycle costs and maintaining safety margins. We consider the commercial potential to be significant and expect it to increase substantially as composite aircraft components and structures continue to displace metallic components and structures.

TECHNOLOGY TAXONOMY MAPPING
Portable Data Acquisition or Analysis Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Integran Technologies USA, Inc.
2541 Appletree Drive
Pittsburgh, PA 15241-2587

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Virgil Provenzano
virgil.provenzano@integranusa.com
6610 Tranford Drive
Cethesda,  MD 20810-4853

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Integran Technologies USA Inc.(Pittsburgh, PA) is pleased to provide this proposal in response to the Small Business Innovation Research (SBIR) Request for Proposal (RFP) (#A1.03), "Aircraft Aging and Durability". A material characterization technology is proposed that is based on grain boundary structure-property relationship to improve prediction of component life for nickel based superalloys. Since it has been well documented that the resistance to intergranular degradation is a function of the special (i.e., structurally ordered low- grain boundaries) grain boundary content in the material, the improvement in bulk material performance can be achieved through careful manipulation of the processing parameters to increase the presence of these special interfaces. The proposed program builds upon results of previous proprietary developments by the applicant in the areas of the microstructural optimization via metallurgical thermo-mechanical processing and the developed modeling concept based on grain boundary structure assessment. The program will involve material synthesis, testing and characterization activities with a specific emphasis on correlating the materials performance with respect to the grain boundary microstructure. The objective for this phase I program is to establish the inter-relationship amongst material processing, grain boundary character distribution, corrosion and deformation behaviour of the material. As a result of significant advances already made in the development of grain boundary engineering, the program proposed herein is expected to have a high probability of success and can potentially lead to a cost-effective technology for mitigating the susceptibility to microstructural instability and corrosion associated with Ni-based superalloys. This program is expected to require six (6) months for completion at a total cost of $100,000.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Enhancement of super alloys currently employed in aerostructures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Application of the proposed GBE technology beyond that specified in this proposal include circumstances where superior corrosion resistance in required when the materials fail through a intergranular corrosion mechanism. Industries that may benefit from this technology which will alleviate and mitigate these intergranular degradation concerns include: •Nuclear plant components (Intergranular corrosion, intergranular stress corrosion cracking) •Pulp and paper recovery boiler components (thermal fatigue and environmental-assisted stress corrosion cracking) •Lead acid battery industry (intergranular corrosion, intergranular stress corrosion cracking) •Industrial power and energy plant components (sulfidation resistance)

TECHNOLOGY TAXONOMY MAPPING
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Airframe
Composites
Metallics
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NextGen Aeronautics, Inc.
2780 Skypark Drive, Suite 400
Torrance, CA 90505-7519

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shiv Joshi
sjoshi@nextgenaero.com
2780 Skypark, Suite 400
Torrance,  CA 90505-7519

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NextGen is proposing a simple yet powerful damage identification technique for advanced composite structures. We propose to develop a damage index based on vibration signature comparison with original signatures of the structure. Our approach is to autonomously perform damage detection as well as identification of non-service loading events by minimum number of sensors. We will start with the preliminary work done by Dr. Mal at UCLA and improve upon it to achieve the objective of cradle-to-grave degradation monitoring. The overall goal of the program is to develop an accurate, rapid, inexpensive method for detection of composite internal damage including bonds strength in built-up structures. The objective of the Phase I program is to develop and demonstrate that the proposed technique is accurate and reliable. We will achieve TRL of 2 in Phase I and subsequent technology transition to TRL of 4 in Phase II. NextGen's strength lies in related prior work, an in-depth understanding of damage modes in advanced composite structures, and comprehensive knowledge of damage detection techniques. Dr. Ajit Mal of the Mechanical Engineering Department at UCLA has an exceptional background in structural health monitoring built on decades of cutting edge research in NDE

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In addition to the direct application of health monitoring system to new aircraft using substantial advanced composite materials, other NASA health monitoring applications of the proposed system include X-37 demonstrator, space shuttle, international space station, and the orbital space plane programs. When attached to fuel tanks or other critical structure, this system would provide a lightweight, inexpensive VHM system that would reduce launch turn-around time, increase probability of launch success, minimize life cycle costs, and increase the crew return mission success.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The life cycle cost of new aircraft and aerospace structures can be reduced significantly if continuous and autonomous condition based structural health monitoring systems can be integrated into their design. In addition to aircraft applications, commercial applications of NextGen's health monitoring system include long-term monitoring of nuclear waste storage, pressure vessels, storage tanks, and piping, automated inspection of nuclear power plants, Navy surface ships and submarines, critical engineering structures.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Structural Modeling and Tools
Autonomous Control and Monitoring
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Radiation Monitoring Devices, Inc.
44 Hunt Street
Watertown, MA 02472-4699

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Timothy Tiernan
TTiernan@RMDInc.com
Radiation Monitoring Devices, Inc., 44 Hunt Street
Watertown,  MA 02472-4699

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
New technology is needed for sensing and characterizing incipient defects, and assessing the effects of aging in aerospace components. Next generation materials, including nickel-based superalloys that are exceedingly difficult to inspect with existing technology are being adopted by designers and manufacturers. The ability to ascertain the remaining life of a spacecraft component, and develop mitigation procedures to improve safety and reliability, are critical. RMD proposes a revolutionary new imaging technology based on microscopic, solid-state sensors, magnetic imaging and "eddy current mapping". The new nondestructive evaluation (NDE) technology will be used to detect, map and characterize nano-scale cracks and corrosion in superalloys and metallic components. The data will be used to develop an accurate model for the prediction of defect propagation resulting from aging. The NDE technology will improve spacecraft integrity and safety, reduce the cost and complexity of inspection, and characterize incipient defects and defect propagation. It can be used during materials selection and testing and for evaluating components in the field as they age. The technology taxonomy areas addressed by this proposal include: avionics and astrionics, information, materials, sensors and sources, structures, and verification and validation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology will fill a gap in the NDE capabilities available to NASA, permitting the inspection of minute defects and aging effects in advanced metal alloys that cannot be inspected with existing NDE technology. The proposed NDE technology will be useful for inspecting flight surfaces, engine casings, titanium castings, hydraulic lines and other components that are made of standard or advanced metallic materials. The technology will permit inspection of thick components in 3-D. For materials testing and development, incipient defects can be detected and their propagation monitored and analyzed during aging. Since the technology can be used to improve manufacturing and the selection of materials, and to test finished components and aging systems, it will have a broad impact on the efficiency and effectiveness of NASA missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The advanced magnetic imaging technologies proposed here would enable inspectors to detect extremely small defects with a simple to operate and interpret NDE technology. Eddy current testing is the most widely used NDE technique in the $600M/year NDE market. The proposed NDE system could take two forms: 1. a stand alone turnkey imaging system for inspecting parts; 2. a module that can be retrofitted into existing ECT equipment to enhance the abilities of that equipment without the need for an entirely new instrument. Some of the market areas where the new technology has promise include: spacecraft, aircraft, ship and other transport vehicle inspection, jet engine inspection, pipeline inspection and manufacturing and QA of metallic components. In addition to NASA, branches of the DOD, specifically NAVAIR and the Air Force, are interested in new NDE technology for both modern and aging aeronautic and weapons systems. For example, NAVAIR has expressed interest to RMD for use of advanced NDE technology for the V-22 Osprey and the Joint Strike Fighter (JSF).

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Testing Facilities
Testing Requirements and Architectures
Structural Modeling and Tools
Tankage
Airport Infrastructure and Safety
Database Development and Interfacing
Sensor Webs/Distributed Sensors
Metallics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Emerald Sky Technologies
6106 Hour Hand Court
Columbia, MD 21044-4702

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Fritz
steven.fritz@comcast.net
6106 Hour Hand Court
Columbia,  MD 21044-4702

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed SBIR project will develop OZ, an innovative primary flight display for aircraft. The OZ display, designed from "first principles" of vision science, cognition, and Human-Centered Computing, brings all cockpit information required for flight together into a single, unified display that uses a common frame of reference employing both the focal and ambient channels of human visual processing. This proposal addresses Topic A1.05 Crew Systems Technologies for Improved Aviation Safety. It specifically addresses the goals of ensuring appropriate situation awareness and facilitating and extending human perception, information interpretation, and response planning and selection. Its primary focus is in the SBIR topical areas of interest in Data fusion technologies for real-time integration and integrity checking of single source information streams of varying spatial and temporal resolution; and Human-centered technologies to improve the access and performance of less-experienced operators and pilots from special population groups. Previous experimentation has shown that OZ provides significantly better performance for pilots than conventional flight instrumentation. The proposal will test the feasibility of using OZ to provide situational awareness superior to that provided by both conventional instrumentation and commercially available electronic primary flight displays. Phase I will show that OZ is also superior to existing electronic primary flight displays that display conventional flight instrumentation on an electronic display and will develop and demonstrate a prototype OZ system in a general aviation aircraft. In Phase II the prototype system will be flight tested against competing electronic flight information systems and a DO-178B compliant OZ system will be developed and flight tested to determine its suitability for FAA certification for general aviation aircraft.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed project will develop a primary flight display (PFD) system for general aviation aircraft. The proposed PFD has potential applications in any NASA aircraft or winged spacecraft. It also has potential application in air transport aircraft, rotorcraft and military aircraft, some of which are used by NASA in its operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed primary flight display (PFD) to be developed under this project is primarily intended for use in general aviation aircraft. It will provide significantly superior situational awareness with considerably less complexity than commercially available PFD systems. The PFD system will be suitable for general aviation aircraft ranging from Light Sport Aircraft to business jets, including a newly certified generation of Very Light Jets currently being introduced to the market. The superior performance of OZ will affect situational awareness and thus safety during flight in instrument meteorological (IMC) conditions, especially single-pilot IMC flight. OZ also has the potential to provide superior performance to current generation "glass cockpit" (i.e. PFD) systems used in air transport aircraft, and in rotorcraft.

TECHNOLOGY TAXONOMY MAPPING
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Human-Computer Interfaces

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
RL Associates, Inc.
1450 Edgmont Avenue, Suite 230
Chester, PA 19013-3934

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mary Ludwig
mludwig@rlassociatesinc.com
4 Tanglewood Dr.
Langhorne,  PA 19047-5729

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
RL Associates, Inc. proposes to conduct research leading to the development of a shortwave infrared (SWIR) range-gated LIDAR system for use in detecting external obscurants and hazards. Working in conjunction with a database of optical properties for known obscurants, the system will be capable of identifying the type and severity of the hazard. While several different LIDAR ranging techniques are currently employed for airborne detection applications, the RL Associates Inc. hazard detection and mitigation system is based upon our patented range-gated technique used in our FireLidar system. This technique allows not only detection of obscurants, but can also be used to image through obscurants and thus mitigate the hazard. RL Associates Inc. is currently leading the industry in shortwave infrared (1.5 um) active imaging systems and plans to use that technology in developing the SWIR LIDAR Hazard Detection System. This system will be compact and lightweight and will operate around 1.5 um, which is safe to the human eye.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has a stated need to improve current hazard detection systems, automate more of the pilots workload as it relates to hazard analysis, and combine and simplify the many available detection techniques for different types of hazards. The RL Associates, Inc. SWIR LIDAR system will identify airborne or ground hazards in the form of hard targets/obstacles or obscurant media, and provide feedback on the hazard type to the pilot. This technology will fill NASA needs in programs requiring atmospheric hazard detection, surveillance, hazard assessment and imaging through obscurants.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology will benefit government agencies including the Missile Defense Agency, for missile guidance systems, NavAir, for both airborne reconnaissance Lidar applications and targeting systems, and Homeland Security, for in-port or aerial surveillance systems. Private sector applications include detection systems for commercial airlines and weather stations.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Airport Infrastructure and Safety
Guidance, Navigation, and Control
Optical
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Global Technology Connection Inc
2839 Paces Ferry Road, Suite 1160
Atlanta, GA 30339-5770

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Nicholas Propes
athakker@globaltechinc.com
2839 Paces Ferry Road, Suite 1160
Atlanta,  GA 30339-5770

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Global Technology Connection, Inc., in collaboration with Georgia Tech (Center for Fuel Cell and Battery Technologies) and our industrial partner, Eagle Pichers, proposes to develop and test the feasibility of a Battery Diagnostics and Prognostics System for space exploration applications. The architecture couples neural network, support vector machine, and fusion algorithms to yield battery remaining useful life predictions taking into account battery usage patterns and detected failure modes to increase the reliability of NASA's electrical power systems. This improved high fidelity architecture will be applied to fault detection and life prediction of both Lead Acid and Lithium-Ion Batteries for several space applications like MER, CEV, CLV, ISS, etc. A multi-disciplinary team with a collaborative approach has been assembled for successful development and demonstration of Battery Life Prediction. Cycle testing of representative cells and batteries will be conducted at the Georgia Tech Research Institute to develop and validate remaining capacity and cycle life models for feasibility. Existing work by GTC on Li-Ion battery deep discharge models and data from our industrial and research partners will be leveraged for development of commercial software that can enhance and monitor battery health and accurately predict remaining useful life. Aggressive commercialization and technology transition plans will be pursued with our industrial team partners.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA requires lightweight rechargeable batteries for future missions to Mars and other outer planets that are capable of operating over a wide range of temperatures with high specific energy and energy densities. The proposed system can be used to monitor the batteries for a wide range of space structures like Mars Exploration Vehicles (MER), CEV, CLV, ISS, GEO, MEO, and LEO etc. The developed and validated Battery Health Monitoring System (BHMS) architecture will reduce repair and maintenance costs through automated diagnostics and prognostics that supports the current readiness, future readiness and quality of service requirements of NASA. The specific benefits are: (1) increased mission readiness (2) reduced total ownership costs (3) reduced battery maintenance parts and planning. The BHMS system will be a valuable technology to improve the safety of future space explorations including manned and unmanned missions to the Moon, the Mars, and other space missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A validated Battery Health Monitoring System (BHMS) would have broad applications to batteries used by DoD systems and vehicles, hybrid vehicles, commercial aviation, road transportation, telecommunications, medical equipment, computer laptop, UPS systems, etc. BHMS can be integrated into the vehicle or system level health management system using this open modular software framework.

TECHNOLOGY TAXONOMY MAPPING
Intelligence
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Reasoning/Artificial Intelligence
Expert Systems
Software Tools for Distributed Analysis and Simulation
Power Management and Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Techno-Sciences, Inc.
11750 Beltsville Drive, Suite 300
Beltsville, MD 20705-3194

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gaurav Bajpai
bajpai@technosci.com
11750 Beltsvill Drive
Beltsville,  MD 20705-3194

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of the project is the development of an open architecture, computational toolbox for design and implementation of diagnostic and prognostic algorithms for aircraft electrical power systems. The management of typical failure modes of the electrical system can have substantial returns in the overall availability, safety and operating cost of aircraft. We propose several innovative techniques for monitoring specific components of the power system such as generators, converters, and batteries. The integrated architecture using general purpose symbolic processing, numerical tools and data logging makes this project especially attractive and will bring advances in diagnostics and prognostics to engineering practice. The toolbox will include code generation tools resulting in the ability to seamlessly integrate the designed algorithms by automating several key steps for the implementation phase. In Phase I we will demonstrate the approach using experimental test beds. The successful completion of this phase of the project will provide not only a prototype health monitoring system but establish a framework to integrate new algorithms allowing the rapid packaging of advanced health management techniques for validation and verification, flight certification and final system integration and evaluation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application would be in prognostics and diagnostics for health management of next generation air and space vehicles. General purpose tools for evaluating newly developed prognostic and diagnostic model and data based algorithms. Lead to an integrated toolbox for the implementation of health management strategies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Power System Management for air, sea and land vehicles is increasingly becoming important as critical systems rely on electrical and electronic systems to operate without failures. Techno-Sciences, Inc (TSi) has ongoing funded research for shipboard power systems management and aviation safety. By leveraging these efforts we will develop diagnostic and prognostic capability for use in the health monitoring system for commercial aircraft. The proposed techniques and technology have a wide applicability for commercial users as well; these include commercial aircraft manufacturers and airlines, electric power generation systems, other sea and land vehicles, and applications where distributed power generation is being used as a primary source or to supplement the grid power.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Data Acquisition and End-to-End-Management
Database Development and Interfacing
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Software Development Environments
Power Management and Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Impact Technologies, LLC
200 Canal View Blvd.
Rochester, NY 14623-2893

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Roemer
mike.roemer@impact-tek.com
200 Canal View Boulevard
Rochester,  NY 14464-2893

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Impact Technologies, with support from the Georgia Institute of Technology and Honeywell, propose to develop and demonstrate a suite of real-time Fault Contingency Management (FCM) algorithms for application within an Integrated Vehicle Health Management (IVHM) system. The proposed FCM software will implement a novel vehicle subsystem fault accommodation approach based on a seamless integration between real-time system health identification and adaptive controller techniques. Specifically, the continuous health assessment algorithms include a real-time adaptive recursive system identification algorithm and an enhanced real-time moving horizon estimation (MHE) algorithm that will be developed and implemented on a prototype embedded system. The proposed FCM software hierarchy will act from the subsystems level up through the vehicle level and will implement fault-accommodating control, health management, and contingency management to accomplish its goal. The significant technology advancement proposed herein is based on the use of dynamic simulation models in a real-time computing environment to not only update health status predictions, but also to determine "on the fly" how accommodate for them. At the conclusion of Phase I, the project team will deliver a proof-of-concept demonstration of the proposed techniques running on an embedded platform using high fidelity propulsion and aircraft simulation models.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The real-time Fault Contingency Management technologies will be directly applicable to Propulsion IVHM, Crew Exploration Vehicle, Reusable Launch Vehicles, Unmanned Air Vehicles and future generation general aviation platforms. It will lead to benefits in the form of improved reliability, maintainability, and survivability of safety-critical aerospace systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential commercial use of the developed technologies is broad. Examples of key customers that could benefit through use of the developed technologies include: unmanned combat air vehicles, JSF, future combat systems, commercial airlines, land and marine propulsion systems, industrial actuation systems, and robotic applications. The aero propulsion domain alone has thousands of potential systems to address with this technology.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
On-Board Computing and Data Management
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Portable Data Acquisition or Analysis Tools
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-0807

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Burkholder
burkholder@bainet.com
1410 Sachem Place, Suite 202
Charlottesville,  VA 22901-2496

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Model-based machinery diagnostic and prognostic techniques depend upon high-quality mathematical models of the plant. Modeling uncertainties and errors decrease system sensitivity to faults and decrease the accuracy of failure prognoses. However, the behavior of many physical systems changes slowly over time as the system ages. These changes may be perfectly normal and not indicative of impending fail-ures; however, if a static a priori model is used, modeling errors may increase over time, which can ad-versely effect health monitoring system performance. Clearly, one method to address this problem is to employ a model that adapts to system changes over time. The risk in using data-driven models that learn online to support model-based diagnostics is that the models may ``adapt'' to a system failure, thus ren-dering it undetectable by the diagnostic algorithms. An inherent trade-off exists between accurately track-ing normal variations in system dynamics and potentially obscuring slow-onset failures by adapting to failure precursors that would be evident using static models. Barron Associates, Inc. and the University of Virginia propose an innovative solution that brings together Barron Associates' proven model-based diagnostic and prognostic algorithms with adaptive system identi-fication algorithms enhanced specifically for health monitoring applications that would benefit from online learning.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research effort clearly offers the potential for a significant leap in vehicle performance, op-eration, safety, cost, and capability. The technology will require a demonstration in an actual-flight envi-ronment to fully characterize and validate the performance that is predicted in simulation and demon-strated in wind tunnel experiments. The research is particularly relevant to NASA's Intelligent Flight Con-trol System (IFCS), which has the objective of enabling a pilot to land an aircraft that has suffered a major systems failure or combat damage, and also to the Single Aircraft Accident Prevention thrust of the Avia-tion Safety Program in which Barron Associates has participated for a number of years.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Prognostic and health management systems are becoming increasingly common in aviation, marine, and industrial applications due to the potential operational improvements and cost savings. The generic, open-architecture modeling, diagnostic, and prognostic software developed under this research program will be suitable for many military and commercial applications.

TECHNOLOGY TAXONOMY MAPPING
Autonomous Reasoning/Artificial Intelligence
Expert Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Ceramics Research, Inc.
3292 E Hemisphere Loop
Tucson, AZ 85706-5103

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ranji Vaidyanathan
rkv@acrtucson.com
3292 E Hemisphere Loop
Tucson,  AZ 85706-5103

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this phase I SBIR program, a team led by Advanced Ceramics Research Inc. (ACR) propose a novel, low-cost manufacturing process for multi-functional polymer composite components with improved lightning strike mitigation and EMI shielding capabilities. The proposed program will develop and demonstrate a process for manufacturing complex-geometry composite parts with tailored lightning strike mitigation capability based on design requirements. This process is a natural extension of the ACR water-soluble tooling process for fabricating complex-geometry polymer composite parts as well as filament wound composite tanks. For the proposed phase I program, the ACR-led team will use a novel process to create a highly conductive surface capable of providing the necessary lightning strike protection and EMI shielding. The ACR team will evaluate the new approach with two different space qualified matrix polymers with graphite fibers and compare the surface conductivity with baseline composite systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The process could be used for making large-scale composites requiring enhanced lightning strike mitigation and EMI shielding capabilities for space and satellite structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology could be used by commercial aircraft manufacturers as well as military contractors.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Powdermet, Inc.
24112 Rockwell Drive
Euclid, OH 44117-1252

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Doud
bpdoud@powdermetinc.com
24112 Rockwell Drive
Euclid,  OH 44117-1252

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed Phase I SBIR proposes a low density (0.75-1.2g/cc)syntactic aluminum foam energy absorber co-manufactured inside a composite fan case for turbine engines. Metal syntactic foams provide more energy absorption than any type other metal or non metallic foam on a volumetric basis (80-150J/cm^3). This will provide a lower weight alternative to hard wall fan casings and a smaller wall alternative to soft walled fan casings. The phase I program will test Syntactic aluminum foam and integrated carbon fiber aluminum syntactic foam panels under high strain rate conditions and under a blade failure ballistic test.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA commercial applications include turbine blade containment, ballistic energy absorption, micro-meteor impact mitigation, lightweight aero frame components, and thermal management materials.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA Commercial applications include both military and commercial. Military uses include lightweight aero frame components, laser framing components, thermal insulation, and composite armor. Commercial applications include automotive crash absorption, sporting equipment, lightweight structures, and turbine engine safety applications.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Spaceport Infrastructure and Safety
Thermal Insulating Materials
Airport Infrastructure and Safety
Composites
Metallics
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Technova Corporation
1232 Mizzen Drive
Okemos, MI 48864-3480

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Anagi Balachandra
tchnv@aol.com
1232 Mizzen Drive
Okemos,  MI 48864-3480

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A versatile class of high-performance structural joints is proposed where massive interatomic bonds over the large surface areas of nanostructured surfaces constitutes the primary joining mechanism. The new nano-engineered joints embody nanomaterials which are self-assembled and anchored onto the joining surfaces. Compatible functionalization of nanomaterials on opposite surfaces creates favorable energetic conditions for their effective engagement and joining via massive primary (chemical) bond formation. Complementary self-assembly techniques will be used for rapid, low-cost, energy-efficient and environmentally friendly processing and anchorage of nanomaterials upon substrate surfaces. Various nanomaterials and anchorage conditions can be used for different substrates (ceramics, metals, polymers, composites) and service requirements. The length of nanomateials would be selected to compensate for the surface roughness. The proposed joints can be engineered to provide broad ranges of mechanical performance, accommodate various material incompatibilities (e.g., thermal expansion mismatch), and different functionalities (e.g., thermal/thermal conductivity, or reversibility). The proposed Phase I research will establish the theoretical potential of the proposed nano-engineered joints, and will develop and characterize a precursor joint system embodying the proposed joining principles in order to verify the technical merits of the technology and its commercial potential.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Major developments in advanced materials over the past few decades have not been matched by corresponding developments in joining technologies. Hence, the distinct features of advanced materials tend to be compromised once they are assembled into hybrid, complex structural systems via conventional joining techniques (adhesive bonding, mechanical fastening, welding, and their derivatives/combinations). The proposed nano-engineered joints promise the high performance attributes, multi-functionality and versatility needed to meet the growing demands on joint performance in today's hybrid, complex structures. An example application, which is subject of our planning efforts with Boeing, focuses on joints within and between (ceramic) thermal protection systems and (composite) structures in reentry vehicles. As a versatile class of high-performance and multi-functional joints, the proposed technology promises to replace traditional joining (adhesive bonding, mechanical fastening and welding) techniques in a variety of applications in NASA's aerospace vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Joints are inherent elements of practically all aerospace systems, since such systems are rarely made of a single piece. Joints formed via adhesive bonding, mechanical fastening and welding (or their derivatives/combinations) are thus key constituents of aircraft structures. The rapid progress in development of advanced materials, and the growing trend towards design of hybrid structures for optimum use of various advanced materials have placed growing demands on joint performance. The developments in joining technology, however, have not offered options to effectively meet such growing demands. As a result, joints increasingly constitute weak links within structural systems, which define the limits on their performance and service life. The proposed joining technology promises to offer solutions to the growing joining problems in aircraft structures, and also in automotive and industrial structures employing advanced materials. The multi-functional features of the proposed nano-engineered joints could eventually expand their applications into electrical systems (as replacement for soldering) and also into thermal management systems.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Hyper-Therm High-Temperature Composites
18411 Gothard Street, Units B&C
Huntington Beach, CA 92648-1208

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Wayne Steffier
wayne.steffier@htcomposites.com
18411 Gothard St Units B&C
Huntington Beach,  CA 92648-1208

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Hot structures fabricated from ceramic composite materials are an attractive design option for components of future high-speed aircraft, re-entry vehicles and propulsion systems to reduce weight and increase performance. One important detail in the design of such structures is that of joining and attachment. Large-area hot structures will likely be fabricated by mechanically joining smaller component sub-assemblies. Conventional metallic fasteners and fastening techniques do not provide structurally tight joints over a wide temperature range. A metallic fastener, which is snug at room temperature, will loosen at elevated temperature due to its relatively high thermal expansion. Excessive preloading at room temperature to maintain a tight joint at elevated temperature may be detrimental to the structural integrity of the joint. Ceramic composite fasteners on the other hand can be designed with near-perfect thermo-elastic compatibility with the adherends, however their prohibitively high cost to produce severely restricts their utility. The objective of this proposed program is to demonstrate the feasibility of a unique, cost-effective thermal stress-free ceramic composite mechanical fastener system suitable for assembly of high-temperature ceramic composite structures. The innovative fastener design facilitates joining load-bearing hot structural assemblies and can be produced at a cost much lower then other competing designs and methods. Ceramic composite fasteners will be produced and experimentally evaluated to determine the shear and tensile properties of the fasteners both individually and of respective lap-joined ceramic composite assemblies.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Fiber-reinforced ceramic-matrix composites are recognized an enabling class of materials for a variety of high-temperature applications in chemical rocket engine throat inserts, combustion chambers and nozzles; aero-engine combustors, turbines and exhaust nozzles; hypersonic airframe hot structure and thermal protection systems; spacecraft re-entry heatshields; and a variety of industrial power generation radiant burner and heat exchanger tubes. One of the most important details in the design of high-temperature ceramic composite structures is that of joining and attachment. This proposal offers a high-temperature fastener that guarantees the lowest possible manufacturing cost and highest production rate over all other competing fastener designs and production methods.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Viable near-term applications for ceramic composites include expendable chemical rocket thrusters for orbital insertion, attitude control system and/or divert thrust chamber components for commercial and military communication spacecraft and/or various ballistic missile defense KE intercept weapons. Opportunities for retrofit application in turbine engine augmentors (e.g., converging/diverging exhaust nozzle flaps and seals) for military aero-propulsion systems also exist. Applications for ceramic composites in advanced airbreathing combined-cycle propulsion systems and control surfaces for reusable hypervelocity and exo/transatmospheric aerospace vehicles are currently being addressed. However, the issues of durability, survivability and maintainability are major concerns. For nuclear (e.g., fission and fusion) energy systems, SiC-matrix composites have been identified as enabling materials for heat exchangers, moderators, first wall plasma containment, liner, and diverter component applications. Similar requirements for high-temperature materials exist for commercial/industrial applications as well. Although less aggressive than the aerospace/defense and nuclear energy-related initiatives, programs are in place for evaluating reinforced ceramics for land-based turbine components, catathermal combustion devices, heat exchangers and radiant burners, which represent opportunities in energy and pollution abatement technologies that may mature over the next 10 or so years.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Reuseable
Ceramics
Composites
Aircraft Engines
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Digital Fusion
5030 Bradford Drive, Suite 210
Huntsville, AL 35805-1923

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Stalnaker
jstalnaker@digitalfusion.com
5030 Bradford Drive
Huntsville,  AL 35805-1923

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation proposed here is to provide a multi-physics modeling tool for materials damage assessment for application to future aircraft design. The software compute engine is based on an existing state-of-art multi-physics solver using first principles of mechanical engineering. Phase I will solve two significant NASA cases using this solver: 1) Coupled fluid-structure simulation of an aircraft wing with aeroelastic behavior and possible fragmentation of the wing, and 2) Simulation of a fuel tank rupture at a ground test facility including trajectory computation of the large fragments. Upon successful demonstration on these two problems, Phase II will proceed to enhance the Multi-Physics, fluid-structure-thermal, compute engine with: 1) a Graphical User Interface (GUI) wrapper to control the simulation, 2) The addition of continuum damage models, 3) a library of models for current NASA materials damage assessment cases, and 4) documentation of the GUI, delivery of the software and on-site training classes. The GUI will allow non-expert users to import existing models from commercial CAD packages and Finite Element codes. Using a desktop Personal Computer, engineers can quickly make accurate and reliable damage assessment decisions for future aircraft structures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications include subsonic fixed wing, rotary wing, supersonic / hypersonic aircraft, test facility explosions and safety, space debris impact on orbiting vehicles, future outer space missions for probability of crashes in space, crew survival analysis for deep space missions to Mars with the possibility of micrometeoroid impact, and even flight deck mishaps involving collision and damage.. Plans for future space vehicles, at all NASA centers, including the Crew Exploration Vehicle, are now underway and it's important to learn from the Shuttle experiences in the early design phase. In this regard, NASA has established the "Design for Minimum Risk" criteria. An important element of these criteria is the analysis of component hazards and failure modes to determine the effect on the full system hazards and risks. With these current and future vehicle designs, the existing empirical methodologies used for evaluating hazards and assigning risk will not be adequate to determine the potential outcomes from a particular initiating event. There is a risk that a critical sequence of events may be overlooked and that a potentially fatal outcome missed. Therefore, risk management for blast, impact and fragmentation assessment is a top priority. Digital Fusion, Inc submits this SBIR proposal to provide NASA with state-of-the-art computer software for direct and immediate application to these concerns.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The multi-physics modeling tool will directly apply to DoD Missile Defense Agency (MDA) programs, specifically tactical missiles for defensive interceptor systems which involve blast dynamics, impact and fragmentation. The U.S. Missile and Space Intelligence Center (MSIC) can directly use the software tool to analyze foreign missile concepts and threats. The fluid-structure-thermal interaction software will find commercial application in simulating car crashes, train accidents, ground shock propagation, aircraft-engine interactions with foreign debris, metal forming, component design for cars, aircraft, and watercraft. Additional materials damage applications include safety analysis of bridges, highways, and explosions in buildings including terrorists' investigations.

TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis and Simulation
Computational Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Hyper-Therm High-Temperature Composites
18411 Gothard Street, Units B&C
Huntington Beach, CA 92648-1208

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Wayne Steffier
wayne.steffier@htcomposites.com
18411 Gothard St Units B&C
Huntington Beach,  CA 92648-1208

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of this proposed effort is to demonstrate the promise of advanced C/SiC and SiC/SiC composites having improved environmental durability and longer life at higher allowable stress levels without using problematic external barrier coatings. Both oxidation inhibited C/SiC and SiC/SiC composite material systems are proposed for this effort on the basis that: (1) C/SiC offers the highest use temperature and lowest cost of all currently available refractory composite systems, and (2) SiC/SiC offers the highest durability and longest life. Each material system offers unique performance/cost benefits and limitations, and each has been identified as a viable candidate for advanced propulsion and thermal protection system component applications. Oxidation resistant C/SiC and SiC/SiC composite plates will be fabricated incorporating a recently developed, 2nd generation oxidation inhibited matrix produced by chemical vapor infiltration (CVI). Test samples from each material system will be prepared and experimentally evaluated in high-temperature tensile stress oxidation environments. The tensile stress rupture results will be compared to "baseline" uninhibited C/SiC and SiC/SiC composites to establish the performance benefits of the proposed approach.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are a number of NASA, DoD and DoE programs in progress or being planned that are targeting advanced ceramic composites as viable high-temperature material candidates. While possessing high specific strength and toughness at elevated temperatures, the utility of current state-of-the-art ceramic composites for satisfying these demanding requirements are severely limited by their susceptibility to oxidation embrittlement and strength degradation. The development of ceramic composite materials with superior performance and long-term durability over currently available materials could directly support and possibly impact future programs, such as: Integrated High Payoff Rocket Propulsion Technology (IHPRPT), Integrated High Performance Turbine Engine Technology (IHPTET), Versatile Affordable Advanced Turbine Engines (VAATE) Program, and a number of other enabling aerospace programs in need of materials capable of reliable load-bearing operation up to and beyond 3000<SUP>o</SUP>F (1650<SUP>o</SUP>C). The utility of current state-of-the-art ceramic composites for satisfying life, cost and performance requirements are limited by their susceptibility to oxidation embrittlement and severe strength degradation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Viable near-term applications for ceramic composites include expendable chemical rocket thrusters for orbital insertion, on-orbit attitude control system and/or divert thrust chamber components for commercial and military communication spacecraft and/or various ballistic missile defense KE intercept weapons. Opportunities for retrofit application in turbine engine augmentors (converging/diverging exhaust nozzle flaps and seals) for military aero-propulsion systems also exist, however the issues of long-term durability and damage tolerance are key barriers against insertion. Applications for ceramic composites in advanced airbreathing and rocket propulsion systems and control surfaces for reusable hypervelocity and exo/transatmospheric aerospace vehicles are currently being addressed, however the issues of durability, survivability and maintainability are major concerns. Although less aggressive than the aerospace/defense and nuclear energy-related initiatives, programs are in place for evaluating reinforced ceramics for land-based turbine components, catathermal combustion devices, heat exchangers and radiant burners, which represent opportunities in energy and pollution abatement technologies that may mature over the next 10 or so years.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Airframe
Launch and Flight Vehicle
Reuseable
Thermal Insulating Materials
Ceramics
Composites
Nuclear Conversion
Thermoelectric Conversion
Aircraft Engines
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
2750 Indian Ripple Road
Dayton, OH 45440-3638

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Hreha
hrehard@crgrp.net
2750 Indian Ripple Road
Dayton,  OH 45440-3638

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cornerstone Research Group, Inc. (CRG) proposes to design and develop a space-qualifiable cyanate ester elastomer for application in self-deployable space structures and future aircraft systems. Having already demonstrated the feasibility of the current cyanate ester shape memory polymer (SMP) as a space-qualifiable material, CRG proposes to refine its existing cyanate ester SMP to provide the flexibility necessary for self-deployable space structures. Working extensively on deployable structure systems for NASA and DoD projects (see section 5.2), CRG has demonstrated the feasibility of self-deploying structures by using surrogate styrene-based systems. CRG now proposes to develop new cyanate ester resins, incorporating the siloxane moiety in the monomer or polymer network, to provide NASA with a material combining the flexibility of siloxanes with CRG's space-qualifiable cyanate ester SMP. CRG's work with DoD and commercial aerospace customers has also helped to identify the proposed material as a durable, lightweight alternative to current state-of-the-art aircraft systems. CRG's innovative approach to the development of space-qualifiable cyanate ester elastomer will provide NASA with a low-cost, space-durable, and flexible material for application in self-deployable space structures and future aircraft systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Supporting NASA's Aeronautics Research Mission Directorate, this project's technologies directly address requirements for lightweight, multifunctional, durable, highly flexible, and shape memory materials for self-deployable space structures, future aircraft systems, and exoatmospheric space seals. This project's technologies offer a wide range of operational temperatures for application in both low temperature and high temperature systems, and will provide the limited outgassing and durability of a space-qualifiable material.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This project's technologies developed for NASA systems would directly apply to systems operated by other government and commercial enterprises. Government systems that would derive the same benefits would include but not be limited to future fixed wing and rotary wing aircraft systems, high temperature flight vehicles, and inflatable systems such as parachutes and inflatable habitats operated by the Department of Defense. This technology's attributes for deployable structures should yield a high potential for private sector commercialization for communications satellites.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Inflatable
Kinematic-Deployable
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Avant Analysis Technology
39 Hickory Circle
Ithaca, NY 14850-9610

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yu Mukherjee
xieyu9@hotmail.com
39 Hickory Circle
Ithaca,  NY 14850-9610

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Hypersonic aircraft are subjected to extreme conditions with respect to mechanical thermal and acoustic loads. Materials with complex microstructure, such as Functionally Graded (FGM) and honeycomb, are expected to play a key role in such vehicles. Detailed numerical stress and thermal analysis of such materials, with conventional Finite Element Methods (FEM), is extremely difficult. The Fast Multipole Boundary Element Method (FMBEM) is a very promising candidate for carrying out such calculations efficiently and accurately. This is an O(N) method (where N is the size of a problem) with respect to both matrix formulation and solution of linear systems. It is proposed that two user-friendly software packages based on the FMBEM, to be called AvantFGM and AvantHoneycomb, will be developed in this proposed Phase I project. These packages will be used to carry out mechanical and thermal characterization of these complex materials. The output of these packages will deliver material properties as functions of spatial coordinates, which can then be used to carry out conventional FEM analyses of aircraft components of complex geometrical shape. Plans for Phase II call for development of fully functioning commercial software capable of analyzing many realistic situations pertaining to hypersonic aircraft. Phase III will be concerned with further development of the software to include damage accumulation (due to, for example, mechanical, creep and thermo-acoustic fatigue) and risk analysis.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary objective of the AvantFGM and AvantHoneycomb software, to be developed during the Phase I project, is to demonstrate the feasibility of the FMBEM approach to carry out thermal and mechanical characterization of materials with complex microstructure, of interest to NASA. Functionally Graded and honeycomb are examples of such materials that are expected to play key roles in hypersonic vehicles. Such materials are required in order to survive the extreme mechanical, thermal and acoustic conditions that prevail in and around hypersonic vehicles. This software will help NASA in developing new materials systems, structural concepts, and manufacturing/fabrication technologies for such vehicles. The Phase II project will continue further development of the Phase I software and address details of issues such as combinations of extreme loads, normal and reentry flights and dynamic effects; and help NASA understand the effects of microstructure on structural response. Plans for Phase III include a study of damage accumulation and risk analysis of hypersonic vehicles from a structural viewpoint.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Fast Multipole Boundary Element Method is a very exciting and powerful method for solving detailed problems with complex microstructure. Meshing is much easier than the FEM due to the reduction of dimension by one, thanks to the BEM. Both matrix computation and solution of linear systems scales as O(N), where N is the size of a problem. The results are accurate and efficient. This method has already been applied to problems of composites, fabricated scaffolds, fuel cells, micro-electro-mechanical (MEMS) and (ongoing work) blood flow. It has huge potential applications in a variety of problems in diverse areas such as mechanical and aerospace (composites, diesel filters), semiconductor (MEMS), power generation (fuel cells), bioengineering (study of bone, soft tissue and blood flow) – for characterization of heterogeneous materials with complex microstructure – either man-made or natural. Once the behavior (typically thermal or mechanical) of such materials is characterized by the FMBEM, the results can be used in conventional FEM analyses of structural elements of complex geometrical shape composed of these materials.

TECHNOLOGY TAXONOMY MAPPING
Structural Modeling and Tools
Ceramics
Composites
Computational Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Materials Resources International
811 West 5th Street, Unit 2
Lansdale, PA 19446-2283

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ronald Smith
rsmith@materialsresources.com
811 West 5th Street, Unit 2
Lansdale,  PA 19446-2283

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Smart materials control of aero-surfaces based on shape memory alloys (SMA) is seeing increased use for improving of future subsonic fixed wing aircraft aero-surface controls. Such SMA actuators have the potential of lowering weight and increasing reliability through direct control. The binary NiTi system has been a preferred system but these alloys have austenite finish Af transition temperature in a reported range of 90 - 100ºC, which is too low for many applications. Therefore, there is strong interest in developing a class of ternary and/or quaternary alloys that incorporate Pd and/or other elemental additions. MRi is proposing to develop NiTiPd and NiTiPd+ X alloys that are capable of being directly formed via vacuum plasma spray (VPS) processing. These alloys have been shown to increase Af transformation temperature to over 350ºC, however, these alloys are also significantly less ductile and more prone to casting segregation. The proposed innovation has the potential to eliminate the typical cast/rolling/extrusion procedures typically used with NiTi alloys with a near-net vacuum plasma spray (VPS) forming process. If successful, the alloy and process development work to be conducted on the Phase I investigation would enable the VPS process to directly form shapes from NiTiPd-X alloys. The proposed Phase I research would be aimed at developing specific NiTiPd+X where X could be Hf, Zr and even B. The development work would focus on developing as –deposited structures that would yield Af transition temperature from 130 - 300ºC. If successful, the development would enable the cost effective manufacture of higher temperature shape memory alloy actuators for use as remote actuation of aero-control surface and engine controls.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA application for VPS formed SMA devices includes a range of remotely controlled actuation devcies to open and close doors and release systems for manned or unmanned vehicles that could be used in NASA spacecraft and probes where remote releases are now being explosively activated. SMA release actuation would be much safer and recallable.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other applications for VPS formed high temperature shape memory alloys include military and civilian uses such as torque and beam actuators for controling aero-surfaces, releases and door and hatch openings where higher power is needed and larger devices must be remotely controlled. Higher temperature acutuation temperature devices will also enble more reliable SMA aircraft engine controls.

TECHNOLOGY TAXONOMY MAPPING
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Prime Research LC
1750 Kraft Drive, Suite 1000
Blacksburg, VA 24060-6376

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell May
rmay@primephotonics.com
1750 Kraft Drive
Blacksburg,  VA 24060-6376

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Routine installation and use of high-temperature optical sensors for characterization of advanced materials critical to NASA hypersonic programs are difficult due to the fundamental difficulties of integrating very diverse materials into a reliable, manufacturable sensor. Sensors based on high-temperature optical fibers (including sapphire fibers) have been developed through extensive research; however, little advancement has been made with regard to achieving cost-effective sensors that can be employed in large numbers. Currently, the materials of the mounting site, the materials of the sensor coupon, the fiber itself, sensor assembly methods and the optical interrogation methods have limited compatibility, resulting in each application becoming a custom installation. Recent demonstrations at Virginia Tech, under NASA hypersonic program funding, of advanced Fracture-Release coupon structures, novel connectorization techniques, and improved assembly methods have enabled more rapid fabrication of high-temperature sapphire fiber sensors well-suited to instrumentation of advance materials in hypersonic research. Prime Research, teaming with Virginia Tech, proposes to leverage these previous demonstrations to improve the manufacturability and ease-of-use of sapphire fiber strain gages, and to modify the assembly methods to permit their use with Prime Research's patented spinel-clad sapphire fibers, which have improved optical properties over unclad sapphire fibers.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A key research goal for NASA is the advancement of hypersonic flight. It is a stated NASA objective to advance knowledge in the application advanced materials (e.g. carbon-carbon, carbon SiC, etc.) and test & diagnostic capabilities to further hypersonic research. Particularly important to this objective is the requirement for high-temperature sensors (including strain, temperature, pressure, mechanical properties, etc.) applicable to supporting advances in the state of the art in hypersonic research, in addition to other flight regimes. The proposed program has specific relevance to NASA strategic sub-goals 3E.3 and 3E.1 as stated in the 2006 NASA Strategic Plan, in that a capability to measure flight mechanical, structural, and material parameters is required for research extensions of fundamental flight performance and mechanics, and operational performance monitoring functions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The product that will emerge following successful conclusion of the proposed SBIR program will satisfy a need in a small but important market. High-temperature strain gages that are currently available suffer from a number of drawbacks that prohibit their use for gas turbine instrumentation. Electrical strain gages are prone to electromagnetic interference and are limited to uses below 1000&#61616;C. Commercially-available optical fiber strain gages are limited to temperatures below about 800&#61616;C by dopant diffusion and glass devitrification. The sapphire fiber strain gage being developed through this SBIR program will be the first practical strain gage for direct measurement of strain in the hot sections of gas turbine engines. Immediate customers are likely to be the gas turbine engine manufacturers, as well as government test and evaluation labs. While this represents a small overall market, it is a viable market that will support sensor system manufacturing and sales.

TECHNOLOGY TAXONOMY MAPPING
Control Instrumentation
Testing Facilities
Optical
Ceramics
Optical & Photonic Materials
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Los Gatos Research
67 East Evelyn Avenue, Suite 3
Mountain View, CA 94041-1518

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Manish Gupta
m.gupta@lgrinc.com
67 East Evelyn Avenue, Suite 3
Mountain View,  CA 94041-1518

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this SBIR effort, Los Gatos Research (LGR) proposes to develop a suite of laser-based diagnostics for the study of reactive and non-reactive hypersonic flows. These sensors will include both in situ and line-of-sight measurements of several critical parameters including gas temperature, velocity, and composition. Both established near-infrared and emerging mid-infrared laser sources will be utilized to make highly-accurate measurements via tunable diode laser absorption spectrometry. The SBIR instrument will be the first system capable of providing real-time, rapid quantification of these important combustion parameters in NASA's hypersonic wind tunnels. Such quantification is essential to the development of improved reactive CFD models and subsequent hypersonic propulsion systems for future aerospace vehicles.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In order to develop next-generation hypersonic vehicles, NASA researchers rely heavily on ground test facilities and complex numerical simulations. These models require a series of assumptions regarding important chemical species and the nature of turbulent flow to become tractable. Due to the complexity of these models and their parameters sensitivities, current CFD calculations lack sufficient predictive capabilities. In order to validate and refine these models, it is necessary to equip ground test engines with diagnostics that are capable of accurately measuring the gas temperature, gas velocity, and concentrations of key chemical species at several points within the turbulent flow field. By comparing the diagnostic results directly to numerical simulations, the modeling of compressible, turbulent flow can be greatly improved, enabling the production of next-generation propulsion systems

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Besides its application to NASA, a laser-based gas analyzer also has significant commercial application. Through a series of strategic partnerships, LGR is developing a suite of analytical instrumentation to measure trace gases for industrial process control monitoring and petrochemical applications. The proposed work is essential in making these instruments more compact, rugged, and cost competitive, and will thus enlarge the potential market size significantly.

TECHNOLOGY TAXONOMY MAPPING
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sun Valley Technology
26700 Renaissance Parkway, Unit 4
Warrensville Heights, OH 44128-5764

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Frank Sun
svtfrank@sbcglobal.net
26700 Renaissance Parkway, Unit 4
WARRENSVILLE HEIGHTS,  OH 44128-5764

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a Multi-Element Lean Direct Injection, ME-LDI, Combustion concept with the following innovative features: 1. Independent, mini burning zones created by containing the flame in a cylinder downstream of each fuel injector/swirler element in a multiple fuel injector array, see figure 1. The independent burning zones will enable fuel staging the fuel injectors (turning off fuel to selected fuel injectors) to cover the operating cycle, such that at each point of the operating cycle the combustor will have high combustion efficiency (>99%) and low NOx emissions. At high power conditions the combustion efficiency should be greater than 99.9%. 2. A low flow number, "Butterfly" fuel injector will be incorporated into ME-LDI that is low cost and simple to manufacture but a highly effective atomizer. The term "Butterfly" derives from the butterfly shape of the spray. The shape of the spray is formed by two diametrically opposed slots cut through a closed end fuel tube, see figure 2. The fuel flow through each slot forms a fan spray. The slot width can be varied to control drop-sizes within the spray.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In the course of the development of the concept it is planned to use laser diagnostics to measure droplet sizes from the fuel injector, fuel distribution, air and fuel droplet velocities and turbulence levels. This data would be made available to NASA for computer model development.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We propose that the initial application would be for small business and personal jets and regional jet aircraft gas turbine engines. The proposed concept would provide a low emissions combustor that would be economical to build and low cost to maintain. Small engines are particularly sensitive to cost and this concept should appeal to small engine manufacturers. It is a developing market and should be receptive to new ideas.

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
Micro Thrusters
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pentalim Corporation
1800 Dakota Drive
Findlay , OH 45840-1763

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dave Hiscock
dhiscock@pentalim.com
1800 Dakota Drive
Findlay ,  OH 45840-1763

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Pentalim Inc. is developing a new sensor for the measurement of chemiluninescence of air breathing engine combustion. The sensor will be wireless and incorporate optical power scavenging technology that will increase its effective transmission range. The sensor will also incorporate Silicon Carbide electronic materials to enable in situ monitoring of combustion. This sensor will be applicable to both future propulsion systems as well as legacy and helicopter engines and will enable improved combustion instability, pattern factor and emissions control.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The sensor will help enable active combustion control for air breathing engines. As a result, this sensor will be directly applicable to NASA milestones in combustion, controls and Intelligent Health Management research and development as part of its ongoing aeronautics research program. Additional development of the sensor would also enable it to be applice to rocket engine combustion research and development.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The sensor will be applicable to help enable the requirement This sensor will be applicable to both to both commercial and military air breathing engines in future propulsion systems as well as legacy and helicopter engines and will enable improved combustion instability, pattern factor and emissions control. Additionally, this sensor will be applicable to ground based turbine systems which also have stringent emissions and perforance requirements.

TECHNOLOGY TAXONOMY MAPPING
Optical
Photonics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Flow Parametrics, LLC
208 West Water Street
Dover, DE 19904-6741

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andreja Brankovic
brankov@flowparametrics.com
208 West Water Street
Dover,  DE 19904-6741

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective is to develop and demonstrate the use of Large Eddy Simulation (LES) for computations of gas turbine combustor flow and transport processes, using the unsteady Navier-Stokes equations on Cartesian grids with local mesh refinement and multigrid acceleration. The basic software for the coupled multigrid algorithm will be developed and demonstrated on simple flows. A Cartesian grid generator, capable of converting complex geometry into an unstructured Cartesian mesh, will be developed. These LES and numerical methods will then be applied to representative gas turbine combustor flows.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The major outcome of the SBIR research program will be an advanced, high performance LES code that will enable detailed studies of combustor performance, with particular emphasis on combustor emissions prediction and reduction. Strong demand by the aircraft engine and power generation turbine industries is anticipated, due to the inevitable reductions in pollutant emissions for these products. This will support NASA's aeronautics programs in many aspects of simulation for aerodynamic and reacting flows.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Outside the aircraft engine and power turbine industries, a wide variety of flow aerodynamics, hydrodynamics, and combustion modeling problems will be simulated using the new code. In particular, unsteady flows in bio-medical devices, automotive flows, alternate propulsion systems such as rocket, ramjets and scramjets, combustion system components such as augmentors, and pollutant dispersal are a few of the types of problems that can be solved through use of the new LES solver.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Cooling
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Innovative Scientific Solutions, Inc.
2766 Indian Ripple Rd
Dayton, OH 45440-3638

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sivaram Gogineni
sivaram.gogineni@wpafb.af.mil
2766 Indian Ripple Rd
Dayton,  OH 45440-3638

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The research team at The Ohio State University has been developing technologies to suppress jet noise using localized arc filament plasma actuators and are in the process of demonstrating this type of technology at NATR facility at NASA Glenn Research Center. The localized arc filament plasma actuators developed at OSU are the only actuators that can be used currently for active control of flow and noise in high Reynolds number and high-speed flows, such as jets, mixing layers, combustors, cavity, etc. However, the lack of availability of appropriate plasma generator has been a hindrance to this technology development. One of the challenges is designing and developing a power supply which can derive up to 64 actuators. The current Phase I SBIR program will explore some new technologies for the design of such a power supply. The research team will focus on building the power supply for NASA during the Phase II program and also will make significant efforts in commercializing this product by making it much more energy sufficient, user friendly, and compact.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Feasibility tests of the proposed concept of multi-channel, energy efficient, lightweight, high voltage pulsed plasma generator with independent channel control (Phase I), as well as testing and optimization of a working prototype powering up to 64 plasma actuators (Phase II) would make possible its use for large-scale, high-speed flow control and noise control applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The most likely commercial application of the proposed technology would be its use for jet engine noise reduction, with a possibility of retrofitting jet engines already in operation. Associated instrumentation, hardware, and software from this technology has the potential for government, industrial, and academic organizations.

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
MHD
Testing Facilities
MHD and Related Conversion
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Michigan Engineering Services, LLC
2890 Carpenter Road, Suite 1900
Ann Arbor, MI 48108-1100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Geng Zhang
gengzhang@miengsrv.com
2890 Carpenter Road, Suite 1900
Ann Arbor,  MI 48108-1100

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The structural design during the early development of an aircraft focuses on strength, fatigue, corrosion, maintenance, inspection, and manufacturing. Usually the acoustic requirements are met after the design of the fuselage structure has been completed. Ideally the structural-acoustic concerns should enter the design cycle early and they should be considered along with other main design disciplines within a Multi-disciplinary Design Optimization (MDO) environment. The proposing firm is uniquely positioned for developing technology which will bring structural-acoustic simulations early in the airframe design process because of their Energy Finite Element Analysis (EFEA) product for structural-acoustic simulations of large systems, and their development of a general purpose code for Multi-disciplinary Design Optimization under Uncertainty (MDO-U). The proposed Phase I project will demonstrate the feasibility of including structural-acoustic simulations in early airframe design. An adjoint sensitivity formulation will be implemented in the EFEA for enabling the utilization of the EFEA within a design optimization environment. In a case study a representative airframe structure will be optimized simultaneously for two different disciplines, using common design variables. An impact type of concern (representative of impact applications for rotorcraft and aircraft, and of shock applications for launch vehicle dynamics) and a structural-acoustic performance due to structure-borne and air-borne excitations (representative to aircraft, rotorcraft, and launch vehicle applications) will be considered. The MDO-U and the EFEA codes will be utilized in the case study, which will demonstrate the feasibility and the value of bringing structural-acoustics early in the design cycle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Structural-acoustic concerns are present in aircraft structures, launch vehicles, and spacecraft, since they are directly related with occupant comfort, and noise induced vibration on payloads and electronic equipment. In all of these areas simulations are utilized during design. Currently, structural-acoustic concerns are typically addressed late in the design cycle when the structural configuration has been finalized. Therefore bringing structural acoustic simulations early in the design cycle will offer cost and weight savings. Therefore, the proposed developments will be useful to all NASA groups interested in reducing weight and cost when designing aircraft, launch vehicles, and spacecraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Structural-acoustic concerns are present in the shipbuilding, the automotive, the military ground vehicle, and heavy construction equipment industries since structural-acoustic performance is directly related with the perceived product quality, acoustic signatures, occupant comfort, and noise regulations. In all of these areas simulations are utilized during design. Currently, structural-acoustic concerns are typically addressed late in the design cycle when the structural configuration has been finalized. Therefore bringing structural acoustic simulations early in the design cycle will offer cost and weight savings. Thus, there is a great market potential for the outcome of this SBIR.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Simulation Modeling Environment
Structural Modeling and Tools
Software Tools for Distributed Analysis and Simulation
Composites
Metallics
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NextGen Aeronautics, Inc.
2780 Skypark Drive, Suite 400
Torrance, CA 90505-7519

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gerald Andersen
gandersen@nextgenaero.com
2780 Skypark, Ste 490
Torrance,  CA 90505-7519

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NextGen proposes an approach to significantly enhance aeroelastic analysis capabilities over what is commonly available in linear analysis environments such as NASTANTM The approach to accomplish this builds upon an existing software framework that allows the integration of varying-fidelity aerodynamic modeling capability with varying videlit structural models. The approach utilizes inherently nonlinear aerodynamic predictions schemes that are incorporated into the aeroelastic solution strategy. Potentially large (geometrically nonlinear) structural deflections under the influence of nonlinear aerodynamic can be analyzed using the approach. Hierarchical levels of analysis capabilities are included, ranging from simple yet powerful empirical approaches to the complete coupling of high-order CFD codes and nonlinear structural models. An aeroservoelastic solution framework will be developed in Phase I resulting in a prototype nonlinear aeroelasticity method suitable for a proof-of-concept demonstration. The developed methods will be demonstrated on test cases of recent research interest, such as the Active Aeroelastic Wing (AAW) F/A-18 aircraft.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This software product will benefit NASA commercialization potential by providing a more accurate and capable aeroelastic analysis methodology. The development and subsequent use of these new capabilities will result in more efficient design cycles yielding more effective designs that perform as they were intended. Common use of high-fidelity nonlinear aerodynamics will decrease the cost of producing aerospace vehicles as the risk of encountering a major design flaw late in the development process will be reduced. The expenses of a flight test program may even eventually be lessened as confidence is gained in simulation techniques to validate vehicle designs. For these reasons, transition from NASA research projects to the commercial sector will be facilitated.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The capabilities developed in this effort will significantly benefit general commercial applications because tools will be introduced that greatly simplify the aeroelastic analysis procedure. User-friendly interface modules will be introduced that will allow much faster problem definition and analysis set-up. The intent of this effort is to eventually offer the practicing engineer aeroelastic data relevant to the design process. To accommodate this, automated procedures will be implemented to perform pressure load integration over desired areas, thereby yielding quantities of practical interest, such as forces on aircraft components, hinge moments, and stability and control derivatives.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Simulation Modeling Environment

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Dynamics, Inc.
4488 Snowmass Court
Salt Lake City, UT 84124-2681

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Patrick Hu
patrick.g.hu@gmail.com
4488 Snowmass Court
Salt Lake City,  UT 84124-2681

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed research program aims at developing a variable-fidelity software tool set for aeroservothermoelastic-propulsive (ASTE-P) modeling that can be routinely applied to the design of aerospace vehicles. The tool set can be applied to conventional vehicle types as well as hypersonic vehicles. The major issues involved in ASTE-P modeling and simulation will be significantly and extensively investigated in this project, which include full coupling between fluid/structure/control dynamics, the aeroservothermoelastic-propulsive instability, the viscous/turbulent effects, shock and shock-boundary layer interaction, as well as the large unsteady and highly nonlinear aerothermal dynamic loading on structure of vehicles. The interface of the structure/control surface dynamic vibration modes with flows will be modeled using particle-based material point method (MPM) in an integrated dynamic fluid-structure interaction environment. The MPM is essentially a particle-based method which avoids dealing with the time-varying mesh distortions and boundary variations due to structure/control surface deformations and/or motions (i.e. wing flutters, FCS/structural mode interaction, PSD turbulence response), thus being significantly more robust and computationally efficient than the traditional finite element methods that must utilize moving-boundary and mesh-regeneration. Phase I will build and demonstrate the initial capability; the end software in Phase II will be fully capable of ASTE-P analysis and evaluation for aerospace vehicles.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The development of variable-fidelity aeroservothermoelastic-propulsive analysis and modeling capability will benefit the testing and clearance of aerospace vehicles in NASA Centers by providing an essential design tool that is not currently available. The end software will be applicable to various aerospace vehicles from conventional types to spacecrafts, and would greatly increase the safety and efficiency of flight testing and clearance. The benefit in terms of improved specification, design and operation