SBIR Phase 2 Solicitation STTR Phase 1 and 2 Solicitation Abstract Archives
| 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
| PROPOSAL NUMBER: | 06-I A1.02-9089 |
| SUBTOPIC TITLE: | Integrated Resilient Aircraft Control |
| PROPOSAL TITLE: | Model Based Aircraft Upset Detection and Recovery System |
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
| PROPOSAL NUMBER: | 06-I A1.02-9217 |
| SUBTOPIC TITLE: | Integrated Resilient Aircraft Control |
| PROPOSAL TITLE: | In-Service Aircraft Engine System Life Monitor Using Advanced Life-Estimating Technique |
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
| PROPOSAL NUMBER: | 06-I A1.02-9516 |
| SUBTOPIC TITLE: | Integrated Resilient Aircraft Control |
| PROPOSAL TITLE: | Damage Adaptation Using Integrated Structural, Propulsion, and Aerodynamic Control |
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
| PROPOSAL NUMBER: | 06-I A1.02-9768 |
| SUBTOPIC TITLE: | Integrated Resilient Aircraft Control |
| PROPOSAL TITLE: | Dynamic Damage Modeling for IRAC Simulations |
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
| PROPOSAL NUMBER: | 06-I A1.03-8344 |
| SUBTOPIC TITLE: | Aircraft Aging and Durability |
| PROPOSAL TITLE: | Magneto-Thermography and Hybrid Methods for Composite Life Management |
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
| PROPOSAL NUMBER: | 06-I A1.03-8436 |
| SUBTOPIC TITLE: | Aircraft Aging and Durability |
| PROPOSAL TITLE: | Grain Boundary Engineering for Assessing Durability and Aging Issues with Nickel-Based Superalloys |
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
| PROPOSAL NUMBER: | 06-I A1.03-8886 |
| SUBTOPIC TITLE: | Aircraft Aging and Durability |
| PROPOSAL TITLE: | Cradle-to-Grave Monitoring of Composite Aircraft Structures |
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
| PROPOSAL NUMBER: | 06-I A1.03-9319 |
| SUBTOPIC TITLE: | Aircraft Aging and Durability |
| PROPOSAL TITLE: | System for Analyzing Microscopic Defects and Defect Propagation Due to Aging |
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
| PROPOSAL NUMBER: | 06-I A1.05-8854 |
| SUBTOPIC TITLE: | Crew Systems Technologies for Improved Aviation Safety |
| PROPOSAL TITLE: | OZ: An Innovative Primary Flight Display |
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
| PROPOSAL NUMBER: | 06-I A1.06-9659 |
| SUBTOPIC TITLE: | Aviation External Hazard Sensor Technologies |
| PROPOSAL TITLE: | Near Infrared LIDAR for Hazard Sensing and Characterization |
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
| PROPOSAL NUMBER: | 06-I A1.07-8707 |
| SUBTOPIC TITLE: | Integrated Vehicle Health Management |
| PROPOSAL TITLE: | Battery Diagnostics and Prognostics for Space Applications |
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
| PROPOSAL NUMBER: | 06-I A1.07-8798 |
| SUBTOPIC TITLE: | Integrated Vehicle Health Management |
| PROPOSAL TITLE: | Aircraft Electrical Power System Diagnostics and Health Management |
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
| PROPOSAL NUMBER: | 06-I A1.07-9303 |
| SUBTOPIC TITLE: | Integrated Vehicle Health Management |
| PROPOSAL TITLE: | Real-Time Fault Contingency Management for Integrated Vehicle Health Management |
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
| PROPOSAL NUMBER: | 06-I A1.07-9512 |
| SUBTOPIC TITLE: | Integrated Vehicle Health Management |
| PROPOSAL TITLE: | Real-Time Adaptive Algorithms for Flight Control Diagnostics and Prognostics |
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
| PROPOSAL NUMBER: | 06-I A2.01-8096 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Polymer Matrix Composite Materials for Lightning Strike Mitigation |
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
| PROPOSAL NUMBER: | 06-I A2.01-8325 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Low Cost P/M Aluminum Syntactic Foam for Blade Containment in Turbine Engines |
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
| PROPOSAL NUMBER: | 06-I A2.01-9149 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Nano-Engineered Structural Joints |
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
| PROPOSAL NUMBER: | 06-I A2.01-9428 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Ceramic Composite Mechanical Fastener System for High-Temperature Structural Assemblies |
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
| PROPOSAL NUMBER: | 06-I A2.01-9551 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Multi-Physics Computational Modeling Tool for Materials Damage Assessment |
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
| PROPOSAL NUMBER: | 06-I A2.01-9578 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Advanced SiC-Matrix Composites with Improved Oxidation Resistance and Life |
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
| PROPOSAL NUMBER: | 06-I A2.01-9593 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Space-Qualifiable Cyanate Ester Elastomer |
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
| PROPOSAL NUMBER: | 06-I A2.01-9674 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Material Characterization for Hypersonic Vehicles by the Fast Mutipole Boundary Element Method |
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
| PROPOSAL NUMBER: | 06-I A2.01-9885 |
| SUBTOPIC TITLE: | Materials and Structures for Future Aircraft |
| PROPOSAL TITLE: | Vacuum Plasma Spray Formed High Transition Temperature Shape Memory Alloys |
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
| PROPOSAL NUMBER: | 06-I A2.02-8281 |
| SUBTOPIC TITLE: | Combustion for Aerospace Vehicles |
| PROPOSAL TITLE: | Development of Manufacturing Methods for Low-Cost, High-Temperature Sensors Applicable to Hypersonic Research |
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C. Commercially-available optical fiber strain gages are limited
to temperatures below about 800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
| PROPOSAL NUMBER: | 06-I A2.02-8522 |
| SUBTOPIC TITLE: | Combustion for Aerospace Vehicles |
| PROPOSAL TITLE: | A Laser-Based Diagnostic Suite for Hypersonic Test Facilities |
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
| PROPOSAL NUMBER: | 06-I A2.02-8571 |
| SUBTOPIC TITLE: | Combustion for Aerospace Vehicles |
| PROPOSAL TITLE: | Multi-Element Lean Direct Injection Combustor Module |
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
| PROPOSAL NUMBER: | 06-I A2.02-9136 |
| SUBTOPIC TITLE: | Combustion for Aerospace Vehicles |
| PROPOSAL TITLE: | A Wireless Chemiluminesce Detector for In-Situ Monitoring for AFEC |
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
| PROPOSAL NUMBER: | 06-I A2.02-9540 |
| SUBTOPIC TITLE: | Combustion for Aerospace Vehicles |
| PROPOSAL TITLE: | Robust High Fidelity Large Eddy Simulation Tool for Gas Turbine Combustors |
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
| PROPOSAL NUMBER: | 06-I A2.03-9145 |
| SUBTOPIC TITLE: | Aero-Acoustics |
| PROPOSAL TITLE: | Development of Energy Efficient, Multi-Channel, Pulsed Plasma Generator for High-Speed Flow Control by Localized Arc Filament Plasma Actuators |
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
| PROPOSAL NUMBER: | 06-I A2.03-9596 |
| SUBTOPIC TITLE: | Aero-Acoustics |
| PROPOSAL TITLE: | Structural-Acoustic Simulations in Early Airframe Design |
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
| PROPOSAL NUMBER: | 06-I A2.04-8147 |
| SUBTOPIC TITLE: | Aeroelasticity |
| PROPOSAL TITLE: | Adjustable Fidelity Computational Aeroelasticity Procedure (AFCAP) |
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
| PROPOSAL NUMBER: | 06-I A2.04-8242 |
| SUBTOPIC TITLE: | Aeroelasticity |
| PROPOSAL TITLE: | Integrated Variable-Fidelity Tool Set For Modeling and Simulation of Aeroservothermoelasticity -Propulsion (ASTE-P) Effects For Aerospace Vehicles Ranging From Subsonic to Hypersonic Flight |
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 operational performance for diverse aerospace vehicles
will potentially lead to savings in project time and cost, and increase the US
space mission effectiveness.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting
methods and software ability will, of course, benefit other DoD components, such
as Army, Navy and Air Force. The US aerospace industries, including Boeing,
Pratt & Whitney, General Electric, General Dynamics, Lockheed Martin,
Textron, and others, will be the major non-military potential customers.
Moreover, improvement of computational accuracy and efficiency is common
interest in CFD/CSD community, thus is highly demanded. The aerospace industries
in Europe, China and Japan represent another large potential marketing of the
resulting methods and software. Advanced Dynamics will promote the international
sales through resale partners of local companies abroad. Therefore, the methods
and software abilities gained from this SBIR project will be additional to
Advanced Dynamics' existing commercial offerings.
TECHNOLOGY TAXONOMY MAPPING
Chemical
Fundamental Propulsion
Physics
Ablatives
Simulation Modeling Environment
Structural Modeling
and Tools
Guidance, Navigation, and Control
Software Development
Environments
Thermodynamic Conversion
| PROPOSAL NUMBER: | 06-I A2.04-8944 |
| SUBTOPIC TITLE: | Aeroelasticity |
| PROPOSAL TITLE: | Sensitivity Analysis and Error Control for Computational Aeroelasticity |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Scientific Simulations, LLC
1582
Inca
Laramie, WY 82072-5007
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Dimitri Mavriplis
mavripl@infionline.net
1582 Inca
Laramie, WY 82072-5007
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of this proposal
is the development of a next-generation computational aeroelasticity code,
suitable for real-world complex geometries, and incorporating error-control for
superior reliability and efficiency, and sensitivity analysis for aeroelastic
design problems. The principal enabling innovation for achieving these goals
involves the development of adjoint methods for time-dependent coupled
aeroelastic simulations. The use of adjoint techniques has become widespread for
steady-state aerodynamic design, and the potential of adjoint methods for
controlling spatial error has been well documented. However, the extension of
these methods to unsteady problems and coupled aero-structural problems has
generally been lacking. Using a consistent and modular adjoint formulation, the
proposed project will result in the incorporation of an adjoint methodology into
an existing three-dimensional unstructured mesh aeroelastic simulation
capability. The adjoint methodology will enable revolutionary advances in
efficiency and reliability for computational aeroelasticity, by providing the
means of controlling temporal error through time-step control for relevant
engineering outputs, such as the determination of flutter boundaries.
Sensitivity analysis will also be enabled, providing the means for performing
aerodynamic shape optimization, structural modifications, as well as valuable
information for guiding the placement, location and properties of flow control
devices, actuators, and smart material technologies.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
On the
one hand, an aeroelasticity simulation package with robust error control will
dramatically reduce the computational requirements and enhance the reliability
of aeroelastic simulations. This will enable NASA projects to combine
wind-tunnel testing and simulation in a more effective manner. On the other
hand, a capability for performing sensitivity analysis within an aeroelastic
simulation will enable NASA to determine novel solutions to aeroelastic problems
through shape optimization, or through structural modifications and/or the
design and placement of active or passive flow control devices. The developed
software may be used in the design of novel subsonic and supersonic aircraft
configurations, as well as in the design and validation of future access to
space transportation architectures.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The developed
software package will be based on an existing steady-state analysis and design
aerodynamics code currently marketed and supported by Scientific Simulations
LLC. The proposed work will extend the capabilities of the current commercial
software product to include aeroelastic effects including analysis and design,
representing an innovative capability which will be unique in the marketplace.
This capability will be marketed to existing Scientific Simulations customers in
the fixed wing aircraft industry, as well as to new customers in other
industries where aeroelasticity is of importance such as the rotorcraft
industry, and the wind turbine industry.
TECHNOLOGY TAXONOMY MAPPING
Airframe
Simulation Modeling
Environment
Software Tools for Distributed Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A2.05-8507 |
| SUBTOPIC TITLE: | Aerodynamics |
| PROPOSAL TITLE: | High-Fidelity Aerodynamic Design with Transition Prediction |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Desktop Aeronautics, Inc.
1900 Embarcadero
Road, Suite 101
Palo Alto, CA 94303-3310
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
David Rodriguez
dlr@desktopaero.com
1900 Embarcadero Rd, Suite 101
Palo Alto,
CA 94303-3310
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To enhance aerodynamic design
capabilities, Desktop Aeronautics proposes to combine a new sweep/taper
integrated-boundary-layer (IBL) code that includes transition prediction with a
Cartesian Euler solver developed at NASA. This combined solver will play an
important role in the preliminary design of both conventional and unconventional
aerospace vehicles traveling at subsonic, transonic, and supersonic speeds.
Complex aircraft configurations may be easily analyzed with the practically
automated surface intersection and Cartesian mesh generation of the Euler
solver. The proposed design-oriented approach to transition prediction will
permit rapid assessment of aircraft that exploit natural laminar flow to reduce
drag. To facilitate design and numerical optimization using the new aerodynamic
analysis, a parameterized geometry engine that can quickly model complex
aircraft configurations will be interfaced with the Euler/IBL solver. Desktop
Aeronautics will also develop a set of optimization tools well-suited to use
with the geometry engine and aerodynamic analysis. This set of tools will permit
aerodynamic shape optimization and multidisciplinary design at earlier stages in
the vehicle development process.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Aerodynamic shape optimization with an Euler solver and integrated
boundary layer method is used by all major aircraft manufacturers and certainly
at NASA centers. The advantage of the proposed application is the time required
to complete a design problem. Because the Cartesian Euler solver is virtually
automatic, extremely robust, and time-efficient, and because the integrated
boundary layer method allows the Euler solver to be useful in many flight
regimes, this application could be used on virtually all aerospace vehicles. The
addition of a transition model provides a new and unique capability to design
aircraft that exploit natural laminar flow.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed
project would generate an innovative commercial application that would address
the needs of virtually every major and even some minor companies that design
aircraft. The specific applications are identical to those listed in the "NASA
Applications" and therefore are not repeated here. Note that the proposed
application would also be marketable abroad since the Cartesian Euler solver can
be licensed internationally.
TECHNOLOGY TAXONOMY MAPPING
Airframe
Software Development
Environments
Aircraft Engines
| PROPOSAL NUMBER: | 06-I A2.05-8653 |
| SUBTOPIC TITLE: | Aerodynamics |
| PROPOSAL TITLE: | Ultra-Low-Power High-Frequency Micro-Vortex Generators for Transonic Flow Control |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
FlexSys, Inc.
2006 Hogback Road, Suite
7
Ann Arbor, MI 48105-9750
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Anne Marsan
amarsan@flxsys.com
2006 Hogback Rd. Suite 7
Ann Arbor, MI
48105-9750
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Active flow control to prevent
or delay boundary layer separation dramatically improves the performance of air
vehicles in critical regions of the flight envelope. FlexSys Inc. has designed a
compact, efficient, electromechanical High-Frequency Micro-Vortex Generator
system (HiMVG) and tested it a subsonic speeds, proving that, when tuned to the
boundary layer, it is as effective at promoting flow attachment as that of the
best oscillatory pneumatic systems but is light-weight and energy-efficient,
consuming a maximum 6 watts of power per actuator. We propose to enhance the
HiMVG system by further reducing its power consumption, increasing its maximum
oscillating frequency, and demonstrating its effectiveness at transonic speeds.
The proposed system will have a tunable natural frequency, so that as the flow
velocity changes, we can adjust the HiMVG system's natural frequency to match
the optimal vortex generator frequency, allowing us to maintain nearly constant,
ultra-low-power consumption. This will allow effective flow control for diverse
flight conditions. The system will consume very little power - less than one
watt per actuator - allowing large arrays to operate using light-weight, compact
power supplies. These improvements will make the HiMVG system feasible for a
wide variety of situations where active flow control is necessary, from subsonic
through transonic conditions.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Robust,
light-weight, energy-efficient active flow control devices can be applied to a
wide variety of aircraft on wings, fuselages, at inlet ports of turbine engines,
etc. Potential NASA customers for our HiMVG system include the Fundamental
Aeronautics Program within the Aeronautics Research Mission Directorate.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Robust,
light-weight, energy-efficient active flow control devices can be applied to a
wide variety of aircraft on wings, fuselages, at inlet ports of turbine engines,
etc. Potential Non-NASA customers for our HiMVG system include all branches of
the military, and all of the major aircraft and jet engine manufacturers.
TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Ultra-High
Density/Low Power
| PROPOSAL NUMBER: | 06-I A2.06-9714 |
| SUBTOPIC TITLE: | Aerothermodynamics |
| PROPOSAL TITLE: | Computational Tool for Aerothermal Environment Around Transatmospheric Vehicles |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
CFD Research Corporation
215 Wynn Drive,
5th Floor
Huntsville, AL 35805-1944
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Vladimir Kolobov
sxh@cfdrc.com
215 Wynn Dr., 5th Floor
Huntsville, AL
35805-1944
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this Project is to
develop a high-fidelity computational tool for accurate prediction of
aerothermal environment on transatmospheric vehicles. This computational tool
will be based on the Unified Flow Solver (UFS) developed at CFDRC for hybrid
simulations of rarefied, transitional and continuum flows. In this Project, the
UFS will be enhanced with advanced non-equilibrium chemistry coupled to
radiation transport and plasma capabilities. The enhanced UFS will include
Boltzmann/continuum solvers for gas species and plasma electrons, state-to-state
vibrational kinetics of molecules, advanced non-equilibrium chemistry coupled to
radiation transport with real gas effects, and charged particle transport and
chemistry. Our two strong points are (i) master equations coupled with
nonequilibrium chemistry in a multidimensional code, and (ii) Boltzmann solvers
for charges and neutral particles providing the capability of using the code
both for reentry flows and for the low-temperature plasma flows. Phase I will be
devoted to evaluation of physical models, initial implementation and
demonstration of new capabilities. In Phase II, these capabilities will be fully
developed, validated and demonstrated for selected benchmark problems. The
availability of the proposed tool will bring the fidelity of modeling high speed
flows of molecular gases to a next level and enable computational investigation
of innovative concepts of plasma technologies for different applications.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This
project will result in a high-fidelity non-equilibrium reentry code with
predictive capabilities. The code will find direct and immediate application in
a multitude of NASA technology development programs under Project Constellation
and the New Millennium Program. Ascent and descent aerothermodynamic effects on
Crew Exploration Vehicle components such as crew capsules and landers, RCS plume
impact during orbital maneuvering, and plume environments during landing
operations near planetary outpost habitat structures will present operational
risks. The accurate modeling of aerothermal environments is essential for
protecting space vehicles and insuring crew safety and overall mission success.
The code will be used as a design tool for development of new generation reentry
vehicles (such as Crew Exploration Vehicle) and components of future hypersonic
vehicles. The code will be also used for plasma flow control for subsonic and
supersonic aerospace applications.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Technology
applications beyond NASA include Theater and National Missile Defense vehicles
performing exo-atmospheric missile intercept, interceptor divert thruster plume
interaction, and the generation of target missile plume signatures. Advanced
space propulsion systems such as arcjets, ion thrusters, and plasma thrusters
must be evaluated for their installed performance and environmental impact. The
Air Force is actively pursuing development of high-speed, long-range,
scramjet-powered strike aircraft that will operate at high altitudes presenting
complex propulsion airframe interaction issues. The software will find numerous
commercial and research applications in material processing (Chemical Vapor
Deposition and dry etching), semiconductor manufacturing, microelectronics,
microsystems, MEMS, etc.
TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling
Environment
Testing Requirements and Architectures
Software Tools for
Distributed Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A2.06-9752 |
| SUBTOPIC TITLE: | Aerothermodynamics |
| PROPOSAL TITLE: | High-Fidelity Kinetics and Radiation Transport for NLTE Hypersonic Flows |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Spectral Sciences, Inc.
4 Fourth
Avenue
Burlington, MA 01803-3304
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Fritz Bien
fritz@spectral.com
4 Fourth Avenue
Burlington, MA 01803-3304
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The modeling of NLTE
hypersonic flows combines several disciplines: chemistry, kinetics, radiation
transport, fluid mechanics, and surface science. No single code or model has
been able to capture, with high fidelity, all the complex effects that come into
play, especially at higher velocities. Spectral Sciences, Inc. proposes to
create an innovative software tool to develop and demonstrate high-fidelity
chemistry, radiation, and flow models for NLTE hypersonic flows that will
address all the important effects in a unified way. SSI will demonstrate an
end-to-end capability to simulate the kinetics and radiation transport for NLTE
hypersonic flows through the development of prototype software and demonstration
for a candidate hypersonic flow scenario. The software will be designed to be
modular, in order that they can be used by other codes and other applications.
Testing and validation will include studies of the interaction of gases in the
shock layer with the ablating material making up the thermal protection system
of the vehicle as well as an assessment of other available codes. It is intended
that the software tool be used as a benchmark to test lower-fidelity models, or
as an inexpensive substitute for laboratory or field tests.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Potential NASA applications include the accurate prediction of
NLTE, hypersonic aerothermal environments near spacecraft. The software
developed from this effort will have applications to spacecraft design and
development for the Crew Exploration Vehicle and aerocapture missions to Titan,
Neptune, and Venus. The software will potentially avoid the need for expensive
measurements and/or complement existing measurements of hypersonic flow
properties. The software tool will provide benchmark results to help assess NASA
flow models that may be less computationally expensive, but perhaps more
flexible to the geometry of the actual problem or in the ability to explore a
large parameter space of trajectories and conditions. The NLTE kinetics and
radiation transport portion of the model will be modular and general in order to
be easily adapted for other potential uses involving other NASA hypersonic, NLTE
flows, or flow-solvers.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed
software tool will have wide application for Earth atmosphere hypersonic flow
problems, including the development of military hypersonic vehicles and military
applications involving the modeling of re-entry flows for missile defense. Other
important military applications include the modeling and analysis of missile
base heating, and modeling associated with the radiation signature of flows near
missile bodies in rarefied, hypersonic flow regimes. The radiation signature due
to NLTE flows near the missile body will be critical for development of missile
defense sensors and associated algorithms. In addition, the proposed software
could supplement existing commercial continuum fluid dynamics software,
providing high-fidelity, NLTE physics capability.
TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion
Physics
Ablatives
Simulation Modeling Environment
Cooling
Thermal
Insulating Materials
Aerobrake
| PROPOSAL NUMBER: | 06-I A2.06-9822 |
| SUBTOPIC TITLE: | Aerothermodynamics |
| PROPOSAL TITLE: | Gas-Kinetic Navier-Stokes Solver for Hypersonic Flows in Thermal and Chemical Non-Equilibrium |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
D&P LLC
3409 N. 42nd
Place
Phoenix, AZ 85018-5961
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Lei Tang
tangl69@hotmail.com
3409 N. 42nd Pl.
Phoenix, AZ 85018-5961
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR project proposes to
develop a gas-kinetic Navier-Stokes solver for simulation of hypersonic flows in
thermal and chemical non-equilibrium. The Navier-Stokes solvers adopted in
current hypersonic CFD codes like LAURA and GASP use Riemann solver for the
convection part and central scheme for the diffusion part. As a result, their
integration with DSMC in the transitional and rarefied flow regimes may cause an
artificial flow across the interface between CFD/DSMC zones because of the
inconsistency in the estimated fluxes. On the other hand, the proposed
gas-kinetic BGK solver for the Navier-Stokes equations (BGK-NS) computes the
inviscid and viscous fluxes as a single entity, consistent with the DSMC
approach. Furthermore, this BGK-NS solver has been demonstrated very accurate
for hypersonic heat transfer prediction. The approach has also been successfully
extended for solution of the Burnett equations whereas the macroscopic Burnett
approach has some numerical difficulties. This SBIR project will further extend
this BGK-NS solver to hypersonic flows in thermal and chemical non-equilibrium.
In Phase I, a prototype non-equilibrium BGK-NS solver will be developed for the
nitrogen shock dissociation cases and then in Phase II, a gas-kinetic CFD
counterpart of LAURA will be fully developed and well validated.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
current mission focuses on human lunar and martian exploration. The design of
crew exploration vehicles requires a computational tool, which is able to
accurately predict hypersonic flows in thermal and chemical non-equilibrium.
Compared with the macroscopic CFD approach, the proposed gas-kinetic CFD
approach is more suitable for simulation of high-temperature non-equilibrium
processes. It is not only accurate for prediction of shock stand-off distances,
peaks in thermal loads, skin friction drag, forces and moments on the vehicles,
but also ready for extension beyond the continuum flow regime. Such a
computational tool can be used for accurate prediction of wake heating,
single/multiple rocket plume effects on the vehicle aerodynamics and heating.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Except Exa's
Powerflow code, current commercial CFD software in the market is based on the
macroscopic CFD approach, which is not well suited for simulation of
non-equilibrium flows. On the other hand, Exa's Powerflow code only works for
incompressible flows. The developed gas-kinetic computational algorithm can
satisfy people's desire of accurate simulation of high-speed non-equilibrium
flows. It can significantly enhance the capability of aerospace industry for
accurate prediction of the aerothermal loads on a space vehicle, and can be used
to analyze aerobrake systems, to predict leakage flows past seal teeth in gas
turbine engines, etc. Such a computational tool is currently lacking in the
market.
TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis
and Simulation
| PROPOSAL NUMBER: | 06-I A2.07-9416 |
| SUBTOPIC TITLE: | Aircraft Control and Dynamics |
| PROPOSAL TITLE: | Miniature High Force, Long Stroke Linear Shape Memory Alloy Actuators |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
MIGA Motor Company
1250 Addison Street,
Studio 208
Berkeley, CA 94702-1713
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Mark Gummin
mark@migamotors.com
1250 Addison Street, Studio 208
Berkeley,
CA 94702-1713
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Shape Memory Alloys (SMAs) are
metal alloys (Nickel-Titanium, for example) that change shape when heated. When
drawn and processed in wire form, the shape change is an aggressive contraction
with useable lifetimes of millions of cycles. Despite this fact, SMAs have
largely been a scientific curiosity, finding very little commercial use as
actuators since their discovery over 30 years ago. The apparent lack of
practical application may be due to their low recoverable strain (~4% of total
wire length). MIGA Motor Company has numerous international patents covering
Displacement Multiplication (DM) techniques that allow us to package strokes of
over 1 inch in highly compact, lightweight packages. Our current commercially
available linear actuators provide 1/2" of stroke with 4.5 pounds of output
force. We propose to develop several high force variants of the DM designs,
allowing up to 45 pounds of force in a device weighing less than 2 ounces. The
manufacturing techniques that we have developed in manufacturing the DM
actuators have paved the way to expansion into the high force realm: high
reliability wire attachment methods, use of high temperature thermoplastics,
Teflon-coated or over-molded precision chemically-etched stainless-steel motive
elements, and various load-sharing techniques have enabled the design of these
actuators to finally become a reality.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There
are numerous applications for high-force linear electric actuators in the
aerospace industry including latch-release devices, telescope and instrument
door and aperture mechanisms, thermal management louver and thruster control
actuators, aircraft control surface actuators, and remotely operated vehicles.
Robotic manipulators, rovers, and other exploration technologies can benefit
significantly from these lightweight, high-force actuators with an extremely
high force/weight ratio (over 360:1). MIGA actuators are compatible with
ultra-high vacuum: made entirely out of high-temperature thermoplastics,
Nickel-Titanium, and stainless steel (or titanium). There are no lubricants. The
total part count is very low, enhancing reliability on orbit or in any other
application. Also owing to their low weight, they are nearly immune to high-g
loads.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The medical
industry represents the most urgent need for modern, high force, linear electric
actuators. The miniaturization of electronic components has fueled the desire
for more portable equipment, and much of the diagnostic equipment in the medical
industry today relies on motors, solenoids, and pneumatic actuators to move,
latch, squeeze, etc, samples and subjects -in ever diminishing package sizes.
There is a huge pent-up demand for assisted medical devices: those which require
a human input, but also demand higher forces than can be applied by a single
technician, or for long periods of time. The defense industry is another
important market, requesting efficient electric actuators that can open and
close weather-station doors in harsh environments across the world, for
instance. Security is becoming an increasingly important business sector, and
there are numerous demands for integrated security solutions, including
electronic latching, dead-bolting, assisted entry systems, and use as redundant
mechanisms in biometric security systems. Each of these applications requires
higher forces than the current MIGA actuators can provide.
TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Micro
Thrusters
Human-Robotic Interfaces
Integrated Robotic Concepts and
Systems
Mobility
Manipulation
Perception/Sensing
Teleoperation
Controls-Structures
Interaction (CSI)
Erectable
Electrostatic Thrusters
Attitude
Determination and Control
Guidance, Navigation, and
Control
Tools
Multifunctional/Smart Materials
| PROPOSAL NUMBER: | 06-I A2.08-8427 |
| SUBTOPIC TITLE: | Experimental Capabilities and Flight Research |
| PROPOSAL TITLE: | Piezo-Hydraulic Hybrid Pump for Flight Control |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Axis Engineering Technologies
One Broadway,
14th Floor
Cambridge, MA 02412-4244
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Eric Prechtl
eric@axisetech.com
One Broadway, 14th Floor
Cambridge, MA
02412-4244
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Axis Engineering Technologies
proposes a revolutionary new technology that can provide performance levels, in
terms of output power, bandwidth and mass, previously unmet in current
commercially available actuation platforms. The approach features a new hybrid
pump, which is powered by active material stacks, and produces fluidic power to
directly power hydraulic actuators. The compact, sealed unit eliminates external
hydraulic components, such as accumulators, reservoirs, and, especially, long
hydraulic tubing runs. By increasing system efficiency, reducing system mass and
exploiting the unique characteristics of active materials, we expect to get a
significant performance improvement in representative applications. This is in
contrast with many commercially available actuation systems, composed of either
traditional hydraulic or electromechanical mechanisms. Each of these systems is
limited due to either excessive mass or limited bandwidth, or both. And yet
these technologies have been adopted across a wide spectrum of applications,
including Unmanned Aerial Vehicles (UAVs), high performance fighter aircraft,
active automotive suspension systems and mobile robotic systems. Each of these
applications would benefit greatly from the introduction of an actuation system
that can provide mass-savings and bandwidth improvements, simultaneously.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
actuator proposed is suitable for a wide range of actuation scenarios across a
number of NASA missions. Fundamentally, we propose to deliver a higher mass
efficient actuation system than currently available commercially. In
Aeronautics, the use of high performance actuators could enable advanced flight
control of experimental aircraft. In Aerospace, they could be used to actuate
thrusters on satellites, position payloads on orbital platforms or provide
efficient control for planetary exploration on-board NASA rovers.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The non-NASA
applications are numerous. In addition to uses similar to those described for
NASA, the system can also be used to enable high performance UAV flight control
in battlefield applications, and actuation on war-fighting robotic platforms. It
would also be enabling for advanced systems, such as wearable robotic
exo-skeletons, and morphing aircraft. The most notable civilian application is
for automotive active suspensions. In this program, our goal is to demonstrate
the technology on a representative application, while pursuing ways to
transition the technology to other platforms.
TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and
Systems
Mobility
Manipulation
Airframe
Controls-Structures
Interaction (CSI)
Pilot Support Systems
Manned-Manuvering Units
| PROPOSAL NUMBER: | 06-I A2.08-8973 |
| SUBTOPIC TITLE: | Experimental Capabilities and Flight Research |
| PROPOSAL TITLE: | Unified Nonlinear Flight Dynamics and Aeroelastic Simulator Tool |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Zona Technology, Inc.
9489 E. Ironwood
Square Drive
Scottsdale, AZ 85258-4578
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Dario Baldelli
dario@zonatech.com
9489 E. Ironwood Square Drive
Scottsdale,
AZ 85258-4578
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA Technology, Inc. (ZONA)
proposes a R&D effort to develop a Unified Nonlinear Flight Dynamics and
Aeroelastic Simulator (UNFDAS) Tool that will combine proven simulation and
visualization techniques to accurately match in-flight recorded dynamic behavior
of an air vehicle. ZONA proposes to develop the UNFDAS Tool through a blend of
state-of-the-art aerodynamic model updating and control-oriented techniques. It
blends mathematically sound flight dynamics and aeroelastic modeling approaches
with CFD, wind-tunnel or flight-test data. The end product is a nonlinear
dynamic tool capable of simulating the key aeroelastic coupling mechanism
between structural modes and unsteady aerodynamic effects with classical
rigid-body dynamics. Feasibility studies are proposed to validate the UNFDAS
Tool using a suite of actual data from flying qualities and flutter flight
tests. This enabling technology will be invaluable to the flight test community
by accurately simulating the air vehicle responses to different input commands,
and then identifying the critical flying conditions before actual flights are
performed. Marketing the resulting software package will be simplified by taking
advantage of ZONA's current extensive customer list. ZONA Technology's
reputation and track record in supporting the aerospace industry and government
with ZONA codes can assure the success of the commercialization plan.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A
nonlinear flight dynamics simulator tool with an added-on aeroelastic solver is
still not available. NASA Dryden Flight Research Center and NASA Langley
Research Center have been working for many years towards achieving a software
package that would accurately predict the interaction between flight dynamics
considering airframe structural flexibility in closed-loop with flight control
laws. The proposed UNFDAS Tool is aimed at providing an expedient
multidisciplinary nonlinear flight simulator tool to perform an efficient flaw
debugging for advanced control laws as well as to promote physical understanding
of the in-flight observed dynamic behaviors due to evolutionary designs. It also
will assist to predict the onset of instabilities prior to envelope expansion
programs. The toolbox will be especially valuable during NASA's current and next
generation UAV's flying qualities and envelope expansion programs, the ERAST
aircraft which is highly flexible and even future RevCon projects that will
introduce distributed control from active materials.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ZONA's business
plan for this toolbox will follow ZONA's flagship software called: ZAERO
product/service sales strategy. The added capabilities developed in the UNFDAS
Tool will strengthen ZONA's market position in the aerospace industry. The
toolbox will be marketed towards the flight test applications on a wide class of
aerospace vehicles such as: (a) USAF's F-22 and F-35 aircrafts at Edwards AFB,
(b) UASF's Hilda, sensorcraft as well as stealth and morphing UAV/UCAV, (c)
DARPA's Morphing Aerostructure (MAS) and Oblique Flying Wing (OFW) Programs, (d)
Boeing 7E7 and future executive jet designs of Cessna, Raytheon, etc. The
proposed toolbox can also be applied to validate health management strategies
specifically designed for aircraft designs with prominent aeroelastic
characteristics.
TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures
Interaction (CSI)
Simulation Modeling Environment
Structural Modeling and
Tools
Guidance, Navigation, and Control
Software Tools for Distributed
Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A2.09-8306 |
| SUBTOPIC TITLE: | Aircraft Systems Analysis, Design and Optimization |
| PROPOSAL TITLE: | Multidisciplinary Optimization Object Library |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
M4 Engineering, Inc.
2161 Gundry
Avenue
Signal Hill, CA 90755-3517
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Myles Baker
myles.baker@m4-engineering.com
2161 Gundry Avenue
Signal Hill,
CA 90755-3517
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of a library
of Common MDO Objects is proposed, in which the software objects will automate a
variety of recurring problems in the development of MDO systems. The focus of
the Phase I project is development of MDO objects to implement multi-fidelity
modeling and simulation within MDO systems, and to implement general
inter-disciplinary mapping/coupling algorithms that can apply to disciplines
such as aerodynamics, structures, and thermal. These modules will make it much
easier to develop MDO applications, as the common issues can be solved by simply
selecting the appropriate "MDO Object".
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
first NASA applications are the BWB-LSV and CEV programs. This effort is also
expected to be directly applicable to the research projects planned in the
Aeronautics Research Mission Directorate (ARMD). The multidisciplinary nature of
the technology makes it an ideal candidate for use any time a very high
performance vehicle is designed, where interactions between components and
disciplines is important. Examples include future high efficiency subsonic
aircraft, quiet supersonic aircraft, high-altitude, long-endurance aircraft,
hypersonic aircraft, and next-generation launch vehicles (either airbreathing or
rocket powered).
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed
software is expected to find wide application to many aerospace and
non-aerospace products, as any type of multidisciplinary analysis and
optimization can be performed. Examples include the medical engineering field,
automotive, aerospace/defense, and alternative energy applications.
TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis
and Simulation
| PROPOSAL NUMBER: | 06-I A2.09-8495 |
| SUBTOPIC TITLE: | Aircraft Systems Analysis, Design and Optimization |
| PROPOSAL TITLE: | Cumulative Metamodeling with Uncertainty Estimation: a New Approach to Optimization of Highly Integrated Flight Vehicles |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Nielsen Engineering & Research, Inc.
605 Ellis Street, Suite 200
Mountain View, CA 94043-2241
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Patrick Reisenthel
phr@nearinc.com
605 Ellis Street, Suite 200
Mountain View, CA
94043-2241
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future adaptive, smart air
vehicles will continually tune themselves using sophisticated on-board health
management and on-the-fly optimization of performance parameters. To support
these dynamic, complex/nonlinear, and multidisciplinary optimization tasks
requires novel methodologies. These new methodologies must be capable of
assimilating data from disparate (heterogeneous) sources in a potentially
high-dimensional parameter space, yet provide robust and updatable predictions.
Recent progress in cumulative metamodel technology suggests new optimization
methodologies capable of combining a priori mathematical models, numerical
predictions, and noisy experimental data. The resulting representations can be
constructed on-the-fly and are cumulatively enriched as more data become
available. Nielsen Engineering & Research (NEAR) proposes to investigate the
use of Cumulative Global Metamodels (CGM) in novel optimization techniques for
conceptual design of highly integrated flight vehicle and air space concepts.
The Phase I will investigate the feasibility of an orders-of-magnitude
acceleration in nonlinear multidimensional design by combining existing search
techniques with adaptive CGMs. A special emphasis of the work will be to
capitalize on NEAR's CGM uncertainty estimation capabilities to monitor the
quality of the metamodel and provide confidence estimates which can be used to
guide optimization in a rational and systematic way.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NEAR's
CGM module for formulating and communicating metamodel information, including
the visualization of uncertainty in multiple dimensions, will support decision
making in complex multidisciplinary environments. The proposed CGM technology is
innovative and has the potential to accelerate future design methods,
particularly when the number of design variable is large. This reduction in time
and cost will result in the designer's ability to handle larger problems or
increase the scope of parametric studies. This technology will help NASA's
mission by reducing risk and incorporating high-fidelity analyses early in
conceptual design of highly-integrated flight and space vehicles.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In the
aerospace field, the uncertainty-enhanced CGM technology will benefit reusable
launch vehicles, UAVs, commercial aircraft, military aircraft, missiles and
armaments. The commercial benefits of developing the CGM technology reach far
beyond the defense and aerospace sectors, however. Numerous technical activities
in the automotive, chemical, and pharmaceutical industries stand to benefit from
the proposed innovation. Banks, the insurance industry, and the Department of
Homeland Security are also potential customers for this technology.
TECHNOLOGY TAXONOMY MAPPING
Chemical
Control
Instrumentation
Airframe
Inflatable
Launch and Flight
Vehicle
Simulation Modeling Environment
Structural Modeling and
Tools
On-Board Computing and Data Management
Database Development and
Interfacing
Software Tools for Distributed Analysis and Simulation
Sensor
Webs/Distributed Sensors
Aircraft Engines
Aerobrake
| PROPOSAL NUMBER: | 06-I A2.09-9065 |
| SUBTOPIC TITLE: | Aircraft Systems Analysis, Design and Optimization |
| PROPOSAL TITLE: | Multi-Disciplinary Multi-Fidelity Design Environment |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Phoenix Integration
1715
Pratt
Blacksburg, VA 24060-6472
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Scott Ragon
sragon@phoenix-int.com
1715 Pratt
Blacksburg, VA 24060-6472
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Phoenix Integration will
develop a collaborative simulation and design environment that will seamlessly
integrate the people, data, and tools required for analyzing and designing
complete vehicle systems. This next generation environment will help NASA to
accurately assess and trade-off competing air vehicle concepts early in the
design process. Working within the environment, geographically distributed team
members will be able to easily construct large multi-disciplinary multi-fidelity
system simulations from a custom library of reusable analysis components. A key
feature of the environment will be "numerical zooming", i.e. the ability to
incorporate numerical analyses of varying levels of fidelity in the simulation.
Interfaces and tools will be provided that will allow users to configure the
system simulation and securely execute it using heterogeneous computing
resources. A simulation data library will allow users to share models, results,
and conclusions with one another, and will serve as a searchable information
repository. The expected results of the Phase I research will be a working
prototype that will demonstrate key aspects of the proposed design environment.
The Phase II program will result in a comprehensive framework environment that
will help NASA achieve Fundamental Aeronautics Program goals for a broad range
of air vehicles.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
To
achieve the Fundamental Aeronautics Program goals, NASA needs a design
environment that will allow early stage designers to accurately assess and
trade-off competing concepts for a wide range of air vehicles. Key needs include
(1) the ability to construct large multi-disciplinary multi-fidelity system
simulations from diverse analysis tools, (2) the ability to bring in more
accurate higher fidelity tools early in the design process, (3) the ability to
deploy and securely execute the system simulation, (4) the ability to archive,
share, and understand the resulting data. Phoenix Integration's proposed design
environment will meet all of these needs in a cost-effective and timely manner.
Because the environment will be built using an open architecture, a wide range
of NASA centers and projects will benefit from the framework. Other potential
applications include propulsion, operations, and mission designs.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Beyond NASA,
the target market for the innovation is any organization involved with complex
system design problems. Sectors that could benefit immediately from the proposed
design environment include aerospace and defense, automotive, electronics, heavy
machinery, shipbuilding, and oil and gas. More diverse, future applications may
emerge in areas such as financial modeling, medical research, and disaster
modeling. Industries in all of these sectors are looking to modeling and
simulation design software to reduce design time, achieve more successful
designs, and to reduce the costs of goods and services. The proposed design
environment will allow firms with a wide range of analysis interests, staff
capabilities, and computer resources to benefit from advanced modeling and
simulation capablities.
TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling
Environment
Database Development and Interfacing
Human-Computer
Interfaces
Software Tools for Distributed Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A2.09-9172 |
| SUBTOPIC TITLE: | Aircraft Systems Analysis, Design and Optimization |
| PROPOSAL TITLE: | Advanced Modeling Concepts for Conceptual Design |
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)
Adarsh Pun
apun@nextgenaero.com
2780 Skypark, Suite 400
Torrance, CA
90505-7519
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Preliminary design of aircraft
structures is multidisciplinary, involving knowledge of structural mechanics,
aerodynamics, aeroelasticity, structural dynamics and design concepts. Even
though analysis tools and computing resources have improved significantly, very
little attention is being paid to the required data exchange and seamless
interoperability for true multi-disciplinary analysis. Indeed there is a lot to
be gained in performing multi-disciplinary analysis up front in the design cycle
during the conceptual design phase as changes during mid or tail end of the
design process are often expensive and difficult to implement. The net result is
increased cost and performance limiting weight penalties on the air vehicle. It
is essential to consider the impact of several design disciplines simultaneously
to arrive at a satisfactory design where generated data for each discipline is
seamlessly generated or available to each design discipline.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Traditional build and test procedures for developing conceptual
prototype designs are costly and there is a need to perform computer simulations
to rapidly evaluate multiple design configurations. The proposed software
framework with advanced workbenches for multiple design disciplines and unique
data management capabilities for interoperability between the various design
disciplines has tremendous commercialization potential NASA airframe development
applications.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Traditional
build and test procedures for developing conceptual prototype designs are costly
and there is a need to perform computer simulations to rapidly evaluate multiple
design configurations. The proposed software framework with advanced workbenches
for multiple design disciplines and unique data management capabilities for
interoperability between the various design disciplines has tremendous
commercialization potential Non-NASA applications in the automotive, marine and
civil industry sectors that currently employ the costly traditional build and
test for conceptual design.
TECHNOLOGY TAXONOMY MAPPING
Controls-Structures Interaction
(CSI)
Simulation Modeling Environment
Modular Interconnects
Structural
Modeling and Tools
Software Development Environments
| PROPOSAL NUMBER: | 06-I A2.10-8152 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | Erosion Resistant Compressor Blade Repair Technologies |
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)
Jun Nable
jnable@powdermetinc.com
24112 Rockwell Dr
Euclid, OH
44060-1252
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase I SBIR program will
demonstrate the use of wear resistant high strength nanocomposites in the
turbine engine repair and refurbishment process. The metallic nanocomposite will
be applied using laser additive remanufacturing to worn turbine blades. This
would provide greatly increased erosion resistance for rotorcraft turbine
engines, extending their life and reducing fuel consumption by 15-20% over the
life of the engine. Powdermet will develop composite feedstocks optimized for
laser additive manufacturing, and is teamed with Flight Support International,
and FAA certified repair shop certified for T64 engine repairs.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Currently, some rotorcraft operating in severe ground environments
such as firefighting, deserts, and dusty urban enviroments need rebuilding in as
little as 100-200 hours of operation due to erosion of compressor blades. As the
blades wear, engine efficiency and power are reduced until the rotorcraft
becomes unsafe. The proposed technology would result in a ten-fold improvement
in rotorcraft engine life while providing new materials options for laser
additive manufacturing and remanufactring of NASA parts including propellant
valves, thrusters, bearing races, rotating seals, and other high wear
components.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This program
will develop a domestic manufacturing base providing 15-30 micron composite
powders to support the emerging manufacturing processes of laser additive
manufacturing and cold spray. Powder feedstock design and optimization for laser
additive manufacturing would be carried out, enabing low cost powder production
of virtually any alloy or composite for this rapidly growing manufacturing
technique. Currently, only costly nickel and titanium based powders are
available in the desired 20 micron particle size, this program would develop a
range of wear resistant, higher strength, and tailorable metallic nanocomposites
to expand laser additive applications into additional markets.
TECHNOLOGY TAXONOMY
MAPPING
Composites
Metallics
Multifunctional/Smart
Materials
Aircraft Engines
| PROPOSAL NUMBER: | 06-I A2.10-8181 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | Optimized Cellular Core for Rotorcraft |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Patz Materials & Technologies
4968
Industrial Way
Benicia, CA 94510-1006
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Nick Patz
nickpatz@patzmandt.com
4968 Industrial Way
Benicia, CA
94510-1006
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Patz Materials and
Technologies proposes to develop a unique structural cellular core material to
improve mechanical performance, reduce platform weight and lower the production
costs for rotorcraft platforms. The performance of any rotorcraft will be
inherently dependent on the flight weight of that structure. The goal of Patz
Materials and Technologies is to combine their experience of resin/fiber
reinforced composite materials with their core fabrication technology to create
a new and novel cellular core material for the advancement of the rotorcraft
industry. To achieve this goal Patz Materials and Technologies proposes to work
directly with a rotorcraft producer, Bell Helicopter, to quantify the specific
physical requirements of cellular core structures applied to rotorcraft
platforms. The outcome of this partnership will allow Patz Materials and
Technologies to develop a unique structural prepreg based cellular core to
optimize performance versus weight. A small amount of the core will be fabricate
and physically tested to validate its significance.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Rotorcraft industry: One of the primary goals of NASA is to
improve the state of the art technologies available to the aerospace industry.
This is the main focus of this proposal. Space Platforms: The cost per weight of
material placed into space is astronomical. The creation of stronger lighter
core materials could significantly reduce the weight of a structure, sub
structure and even the launch vehicle enabling higher payload capacities less
fuel consumed and less overall cost to produce the structure. Mars Unmanned
Rotorcraft Vehicle: The reduction of weight on an unmanned rotorcraft vehicle
for the purpose of exploring Mars is an immediate application in which saving
even a few pounds of weight will yield immense savings in associate launch
costs.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Structures such
as military and commercial aircraft, ground vehicles and marine vessels have the
potential to utilize a new cellular core material to increase strength while
reducing weight. The new cellular core material could also be utilized in
numerous sporting goods, optical benches and even cargo containers.
TECHNOLOGY TAXONOMY MAPPING
Airframe
Composites
| PROPOSAL NUMBER: | 06-I A2.10-8750 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | Surface-Mount Rotor Motion Sensing System |
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)
Robert McKillip
bob@continuum-dynamics.com
34 Lexington Avenue
Ewing, NJ
08618-2302
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A surface-mounted
instrumentation system for measuring rotor blade motions on rotorcraft, for use
both in flight and in wind tunnel testing, is proposed for development. The
technology builds upon previous Navy-sponsored SBIR work in the design of a
system for measuring rotor blade motion and loads, by combining several separate
measurement technologies into a single instrumentation unit. The device may be
applied onto the underside of any rotor system, and has a sufficiently small
weight and form factor to minimize any impact on either blade aerodynamic or
inertial properties. Data transfer to and from the unit is performed using
optical telemetry, and power for the system is provided from self-contained
conformal batteries. These features eliminate the need for specialized rotor hub
hardware for blade angle measurement or sliprings for power or data exchange,
thus enabling its use on a wide range of rotor systems of interest to NASA and
commercial customers.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
instrumentation system to be developed here would significantly enhance the
capabilities of NASA researchers to improve rotorcraft aeromechanical modeling
and prediction tools by providing much-needed high-quality data on rotor blade
motion during rotorcraft testing. These data would be used to validate analyses
of distributed aerodynamic and aeroelastic loads on rotor systems both in-flight
and in wind tunnel test environments. The additional detail available from these
datasets would improve physical understanding of the complicated aeromechanical
interactions present in rotor system response, thereby leading to the
development of better design tools for characterizing the rotor's behavior.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA
commercial applications for this measurement system include supporting
rotorcraft flight test operations, functioning as a condition monitoring system
for rotor motion limit checking, and aiding routine maintenance for rotor blade
vibration reduction through enhanced blade tracking. Future applications could
include rotor state measurement for enhanced rotorcraft flight control feedback
functions.
TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Attitude
Determination and Control
On-Board Computing and Data
Management
Autonomous Control and Monitoring
Portable Data Acquisition or
Analysis Tools
Sensor Webs/Distributed Sensors
| PROPOSAL NUMBER: | 06-I A2.10-8983 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | Next Generation Modeling Technology for High Speed Rotorcraft |
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)
Todd Quackenbush
todd@continuum-dynamics.com
34 Lexington Avenue
Ewing, NJ
08618-2302
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent R&D associated with
designing high speed rotorcraft has been greatly hampered by a lack of test data
and confidence in predictions for rotors operating above advance ratio 1.0. This
proposal outlines a plan for addressing this situation through a series of rotor
tests and analytical enhancements. The three-pillared approach begins with a
model rotor test in Phase I that will obtain essential data on autorotation
characteristics of rotors operating at high advance ratio. The second pillar
will involve analytical enhancements for comprehensive rotorcraft analyses
featuring an improved yawed flow correction and an improved lifting surface
blade model that will properly shed wake off the "leading edge" of blades
operating as reverse velocity rotors. The third pillar will focus on improving
grid generation methods for CFD solutions to appropriately model reverse and
spanwise flow regions. Phase II will see additional rotor tests and model
improvements followed by incorporation of new technology into a software module
suitable for immediate implementation in rotorcraft analysis and flight
simulation software. The new software module will provide a hierarchy of methods
capable of modeling high speed rotorcraft blade aerodynamics for a broad
spectrum of fidelity/speed requirements ranging from real-time flight simulation
to high resolution CFD.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed effort directly responds to NASA's SBIR solicitation goal of developing
validated physics-based multidisciplinary computational tools applicable for the
design, analysis and optimization of rotorcraft in the area of aerodynamics. The
proposed effort will provide invaluable test data and analysis enhancements for
the aerodynamic design of high speed rotorcraft, particularly any V/STOL
aircraft utilizing a slowed-rotor system. The Phase I and Phase II test programs
will provide important experimental data on aerodynamic characteristics of high
speed rotors including Reverse Velocity Rotors. This test data will be
invaluable in the evaluation of future concepts.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There is
currently high interest at the DOD in High Speed rotorcraft. Several ambitious
and high risk projects are being funded, such as the Sikorsky X2 co-axial rotor
and the Groen Brothers slowed-rotor heliplane. The test data and analytical
enhancements proposed here would provide invaluable support in the design and
evaluation of these concepts. The analysis and test data would also facilitate
design and assessment of other compound aircraft and unmanned vehicle concepts
utilizing slowed rotors to reduce noise and improve cruise performance while
maintaining a hovering capability.
TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis
and Simulation
| PROPOSAL NUMBER: | 06-I A2.10-9283 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | Rotorcraft On-Blade Pressure and Strain Measurements Using Wireless Optical Sensor System |
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)
Gang Wang
wangg@technosci.com
11750 Beltsville Drive
Beltsville, MD 20705-3941
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Experimental measurements of
rotor blades are important for understanding the aerodynamics and dynamics of a
rotorcraft. This understanding can help in solving on-blade problems as well as
in designing and optimizing the blade profiles for improved aerodynamics and
noise attenuation in the next generation rotorcraft. Therefore, a Wireless
Optical Pressure/Strain Sensor (WOPSS) system for helicopter on-blade pressure
and strain measurement is proposed to utilize the benefits of low coherence
interferometry system to create an innovative real-time pressure and strain
measurement technique. Leveraging past and current experiences with fiber optic
sensor development, a proof-of-concept of optical pressure/strain sensor system
with wireless data acquisition and transfer capability will be demonstrated at
the end of Phase I. The distributed optical pressure/strain sensor measurements
will be used to obtain real-time dynamic pressure fields and mode shapes and
displacements by integrating strain data for the helicopter rotor blade. Phase I
efforts will conduct optical pressure and strain sensor design analysis to meet
on-blade pressure and strain measurement requirements and demonstrate a
proof-of-concept prototyped wireless optical pressure and strain sensor package.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Throughout the Phase I effort, we will work in concert with NASA
sponsors and our industry to ensure that the WOPSS technology can be seamless
integrated with rotor blade systems. To facilitate technology transfer, we will
work in Phase I to address top-level hardware and software integration issues
from a systems engineering perspective. Issues such as hardware and control
electronics, software architectures, hardware interfaces, manufacturability,
ruggedness, and reliability will be considered in Phase I and implemented in
Phase II.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The WOPSS
technology will be applicable to a wide range of end-users in the defense,
commercial, and industry sectors. TSi's WOPSS will be an integrated
software/hardware product that can be licensed for manufacture to our strategic
manufacturing partner, or a similar rotorcraft producer, depending on the market
being addressed. Because TSi already enjoys market share of adaptive materials
for precision control of structures, noise, weapons effectiveness, etc., through
our existing customers, we plan to leverage these marketing outlets and offer
WOPSS systems for enhanced performance where conventional sensors have not been
successful from performance and cost perspective. TSi will finalize a formal
partnership with a strategic manufacturing partner, who will produce the WOPSS
systems specific to commercial rotorcraft. TSi will partner with an OEM
manufacturer in an appropriate field of use (e.g., electro-optics manufacturer,
weapons systems integrator, aircraft OEM, etc.) to modify the WOPSS as a generic
sensor. We will perform final systems integration of the WOPSS systems and
conduct direct marketing and sales of the product to the end-use through our
internal resources.
TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and
Control
| PROPOSAL NUMBER: | 06-I A2.10-9284 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | Vibration Reduction Methods and Techniques for Rotorcraft Utilizing On-Blade Active Control |
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)
Curt Kothera
kotherac@technosci.com
11750 Beltsville Drive
Beltsville, MD
20705-3941
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Rotor blades adapted for
vibration control have the added benefit of extended blade and rotor life, as
well as improved passenger comfort. Approaches that have been explored for
on-blade active control or individual blade control include control surface
actuation, such as trailing edge flaps, and integrated blade manipulation, such
as controllable twist. For retro-fit and upgrade purposes, the advanced rotor
system needs an actuation scheme with appropriate force, deflection, and
bandwidth, without detrimentally increasing on-blade mass. Research in this area
has been conducted with potential solutions employing various conventional
active material actuator configurations, but these systems have typically
suffered from inherent disadvantages. Due to these limitations, Techno-Sciences,
Inc. proposes the use of pneumatic artificial muscles to actuate a trailing edge
flap device for management of rotorcraft vibration. The proposed actuators are
constructed of passive materials that are very mass efficient and low cost,
while maintaining adequate force, stroke, and bandwidth. Oriented along the
blade span and located within the airfoil contour near the blade root, the
antagonistic configuration of actuators offers bi-directional flap deflection
and operation under a low centrifugal field. A lightweight mechanism accompanies
the actuators, running along the span, to transfer and tailor the mechanical
work from the actuators to the span station of the flap. The proposed research
plan will work to properly size and scale the actuators and mechanism for the
desired response, and construct a prototype device that demonstrates the
feasibility of the concept on the bench-top and in a rotating environment at
full-scale loading.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Throughout the Phase I effort, Techno-Sciences, Inc. will work in
concert with NASA sponsors to ensure that the proposed trailing edge flap device
operated with pneumatic artificial muscles can be seamlessly integrated with
existing rotor blade systems and future vertical flight technologies currently
in development. These include single or multiple passenger vehicles for
transportation, search and rescue operations, and package delivery, in addition
to unmanned vehicles for meteorological and atmospheric measurements, operations
in hazardous environments, and traffic control. To facilitate technology
transfer, we will work in Phase I to address top-level hardware and software
integration issues from a systems engineering perspective. Issues such as
control electronics, software architectures, hardware interfaces,
manufacturability, ruggedness, and reliability will be considered in Phase I and
implemented in Phase II of the program.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The
pneumatically actuated, trailing edge flap device for rotorcraft vibration
control will be applicable to a wide range of end-users in the defense,
commercial, and industry sectors. Its broad applicability is enabled by the
scalability of the pneumatic artificial muscles for the entire range of small
unmanned vehicles to larger transport vehicles. In addition to the noted NASA
applications, vibration control in vertical take-off and landing systems is
attractive to the military for tasks such as mine detection, troop insertion and
extraction, and biochemical weapons cleanup; and commercial and industry tasks
such as construction in hazardous terrain, maintenance of bridges and buildings,
and storm tracking. The proposed flap technology will be an integrated
hardware/software product that can be licensed for manufacture. Techno-Sciences,
Inc. already enjoys market share of related technologies through our existing
customers, and we plan to leverage these marketing outlets and offer pneumatic
artificial muscle flap systems for advanced rotor upgrade packages.
TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and
Control
| PROPOSAL NUMBER: | 06-I A2.10-9691 |
| SUBTOPIC TITLE: | Rotorcraft |
| PROPOSAL TITLE: | A Post-Processing System for Physics Based Derived Rotorcraft Computational Aero-Acoustics Simulations |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
JMSI, Inc. dba Intelligent Light
301 Rt.
17N - 7th Floor
Rutherford, NJ 07070-2580
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Earl Duque
epd@ilight.com
301 Rt. 17N - 7th Floor
Rutherford, NJ 07070-2580
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Intelligent Light, the makers
of the FIELDVIEW CFD post-processing software, in response to NASA SBIR Phase 1
solicitation, proposes an effort that addresses A2.10 Rotorcraft-Acoustics. The
proposed work shall result in a specialized prototype post-processing system
designed for large rotorcraft acoustics problems. This system is designated as
RCAAPS – Rotorcraft Computational Aero-Acoustics Post-processing System. It is
designed to expedite the exploration of large transient datasets that result
from multi-physics based (i.e. Large-Eddy Simulation with aeroelasticity and
acoustics) simulations as it pertains to rotorcraft performance predictions
especially maneuver. It consists of specially configured hardware, flow solver,
acoustics and post-processing software enhanced to take advantage of
contemporary SMP computer clusters during both compute and I/O. The prototype
system developed under this SBIR will revolutionize the way investigators
explore large datasets and allows for more complete and thorough use of the
complete CFD and acoustics data.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
RCAAPS
has two potential benefits to NASA: as a highly effective tool to advance the
usefulness of rotorcraft simulation and as a post-processing tool to support all
types of unsteady design and analysis tools. RCAAPS primary focus is
aeroacoustics, which has application in environmental noise reduction for
rotorcraft and fixed wing aircraft in high-lift configurations. The fundamental
technologies (integrated high-performance parallel I/O, high performance
CFD-specific numerical methods, 'point and click' interrogation of large
unsteady runs) will be applied to the software products that the offeror
currently markets, such as FIELDVIEW and FIELDVIEW eXtreme (for Virtual Reality
environments), along with next-generation tools currently under development.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aero-acoustic
analysis is of high importance to manufacturers of both fixed wing aircraft and
rotorcraft. A system such as RCAAPS will significantly advance the tools
available to US industry for the design and analysis of environmental noise from
such machines - this is becoming more and more of a priority today, both in
combat and commercial operations. Companies such as Sikorsky, Boeing and Bell
are among those who have expressed interest in this capability. Aircraft engine
manufacturers such as GE, Pratt & Whitney and Rolls Royce are beginning to
utilize 3D unsteady simulations in an effort to reduce the acoustic signature of
their products. RCAAPS would become a critical capability to them and to
automotive manufacturers as well. Any application of large unsteady CFD is a
potential user of these technologies.
TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis
and Simulation
| PROPOSAL NUMBER: | 06-I A3.01-8158 |
| SUBTOPIC TITLE: | Next Generation Air Transportation System - Airspace |
| PROPOSAL TITLE: | Computational Appliance for Rapid Prediction of Aircraft Trajectories |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Optimal Synthesis, Inc.
868 San Antonio
Road
Palo Alto, CA 94303-4622
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Padmanabhan Menon
menon@optisyn.com
868 San Antonio Road
Palo Alto, CA
94303-4622
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Next generation air traffic
management systems will be based to a greater degree on predicted trajectories
of aircraft. Due to the iterative nature of future air traffic management
computations, the success of these systems will depend strongly on the ability
to rapidly generate trajectory predictions. This proposal advances the
development of a computational appliance for rapid prediction of aircraft
trajectories (CARPAT) that combines the capabilities of the NASA-FACET software
with the fast computing capabilities of the emerging field programmable gate
array technology. By integrating the FACET software components on commercial,
off-the-shelf high-speed computing technology, the proposed research will
demonstrate high trajectory prediction speeds at modest cost. Phase I research
will demonstrate the feasibility of developing the trajectory prediction
appliance using off-the-shelf hardware. High-speed trajectory predictions will
be demonstrated under realistic traffic scenarios. A complete version of the
system will be developed and provided to NASA during the Phase II work. The
trajectory prediction appliance will commercialized during the Phase III work.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
By
enabling very fast trajectory predictions, the proposed system will contribute
towards the NASA-NGATS research program.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The
CARPATsystem developed under the proposed research will contribute towards the
development of next-generation air traffic management technologies. The
computational appliance and its architecture have several applications in flight
simulation, space vehicle and UAV guidance, and in real-time signal processing.
TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and
Control
On-Board Computing and Data Management
Pilot Support
Systems
Computer System Architectures
Software Tools for Distributed
Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A3.01-8376 |
| SUBTOPIC TITLE: | Next Generation Air Transportation System - Airspace |
| PROPOSAL TITLE: | Airspace Flow Program Modeling in the Future ATC Concept Evaluation Tool |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Mosaic ATM, Inc.
1190 Hawling
Place
Leesburg, VA 20175-5084
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Lara Cook
cook@mosaicatm.com
1190 Hawling Pl SW
Leesburg, VA 20175-5084
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Airspace Flow Program
(AFP) is a new Traffic Flow Management (TFM) control technique that has entered
operation in 2006. AFPs use two existing technologies, Ground Delay Programs
(GDPs) and Flow Constrained Areas (FCAs), to reduce demand on constrained areas
of the airspace by issuing delays to be applied pre-departure. The operational
use of AFPs during the 2006 severe weather season was received positively by the
TFM community. However, there are significant aspects of AFP operational
characteristics that differ from the previous airport-based GDPs. NASA's FACET
model has already contributed significantly to the research and evaluation of
TFM concepts. As the JPDO continues to refine its vision for the Next Generation
Air Transportation System, additional capabilities in FACET will support its use
as a critical tool for further NASA research. The development of an AFP model
for FACET is an essential addition to support research and analysis of both
current and future TFM operations. Mosaic ATM proposes to conduct detailed
analysis of AFP operations and to develop an AFP model for FACET.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
analysis of AFP operations and development of a FACET AFP model as proposed
herein will support NASA's advanced research into TFM operations and decision
support tools. The proposed FACET AFP model will provide the infrastructure and
capability necessary for NASA researchers and other industry analysts to achieve
deep insight into TFM operations. NASA will also benefit from the work to be
conducted in this effort, through the transfer of the AFP model into the ACES
modeling system.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Universities
and other government agencies, including the FAA and JPDO, that conduct research
on air traffic management could benefit from the use of the FACET AFP model.
There are currently many research and operational users of FACET. The addition
of an AFP model will provide added capability and benefit for all users of the
system.
TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling
Environment
Airport Infrastructure and Safety
Expert Systems
Software
Tools for Distributed Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A3.01-8855 |
| SUBTOPIC TITLE: | Next Generation Air Transportation System - Airspace |
| PROPOSAL TITLE: | ACES Model Composition and Development Toolkit to Support NGATS Concepts |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Intelligent Automation, Inc.
15400 Calhoun
Drive, Suite 400
Rockville, MD 20855-2785
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Vikram Manikonda
vikram@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville, MD
20855-2737
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation proposed in
this effort is the development of a model composition toolkit that will enable
NASA Airspace Concept Evaluation System (ACES) users to design and compose
agents, activities, and models to meet specific design requirements. Our
technical approach builds on recent advances in formal agent specification, role
composition and model composers. The toolkit will allow end-users to use a
graphical editor and templates/property sheets to load, create, configure and
interconnect agents, activities and domain models.. In addition to composing
agent and models, a key feature provided by this toolkit is a family of
"physical language specific adaptors" that will allow users to import domain
models written Matlab<SUP>REG</SUP>. The toolkit will also provide
capabilities to export ACED LDC data to tools such as Matlab for post analysis
and graphing. The primary focus of the Phase I effort will focus on
demonstrating the feasibility and capability of this toolkit for the ACES
Terminal Area Plant. We propose to demonstrate this capability by developing
showing how an end-user, not experienced with Java, can easily add a C2 agent to
perform runway balancing and replace the current timer-based Terminal Area Link
transit models with 4-D trajectory models.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our
initial target for the product developed in this effort is the ATM modeling and
simulation community within NASA. Over the last few year NASA ACES software has
gained increased acceptance and usage by Air Traffic Management (ATM)
researchers, concept developers and analysts. It is currently being used by the
FAA, JPDO and other organization to develop and evaluate current and future
airspace concepts in support of NASAs VAMS and NGATS efforts. The proposed ACES
agent model composition toolkit will significantly increase the flexibility and
usability of ACES, and reduce the lead time and cost associated with developing
new concepts and/or inserting new models into ACES.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Our target
market here is the DOD and commercial modeling and simulation community sector.
To address this broader modeling and simulation market IAI will extend and
generalize the model composition toolbox for applicability to simulations using
CyebelPro<SUP>REG</SUP> and make it available as a component of
CybelePro suite of tools. Other examples of IAI's commercialization efforts in
developing toolboxes for Cybele include the development of a game-theoretic
toolbox, a distributed robot control toolbox, and DIVA, a case tool for design
and development of Multi-agent Systems.
TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling
Environment
Computer System Architectures
Human-Computer
Interfaces
Software Development Environments
Software Tools for
Distributed Analysis and Simulation
| PROPOSAL NUMBER: | 06-I A3.01-9619 |
| SUBTOPIC TITLE: | Next Generation Air Transportation System - Airspace |
| PROPOSAL TITLE: | Market-Based Mechanisms for Efficient Allocation of NAS Resources |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Metron Aviation, Inc.
131 Elden Street,
Suite 200
Herndon, VA 20170-4758
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Robert Hoffman
hoffman@metronaviation.com
131 Elden Street, Suite 200
Herndon, VA 20170-4758
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Both FAA and NASA research has
highlighted the need for efficient and equitable allocation of NAS resources and
increased operational flexibility. In particular, market-based mechanisms are
needed for transferring system-imposed delay from more critical to less critical
flights. In this SBIR, we will develop a National Airspace Resource Exchange
System (NRES) that will provide the FAA and the aviation community with a means
for trading scarce resources and priorities for ATM services. Today's airspace
system has rudimentary market mechanisms in place. However, these are valid only
for highly specialized circumstances: airport arrival slot trading in ground
delay programs applied by FAA traffic managers. We propose to develop an
infrastructure necessary to support secondary markets for the full spectrum of
NAS resources and services.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed SBIR directly benefits the NASA's Next Generation Air Transportation
System (NGATS) Air Traffic Management Airspace Project, whose primary goal is to
develop integrated solutions for a safe, efficient and high-capacity airspace
system. Efficient airspace allocation requires early research in market-based
mechanisms for design of the next-generation air transportation system. This
research also extends NASA objectives from the recently completed Advanced Air
Transportation Technologies (AATT) project, whose primary goal was to improve
the capacity of transportation aircraft operations at and between major airports
within the National Airspace System. As part of AATT, NASA helped develop
decision-support tools for air traffic controllers, airline pilots and air
operations managers to handle the growing demand for safe and efficient air
travel. Our research extends effectiveness of those NASA tools and concepts
(CTAS, TMA, McTMA, Regional Metering), by increasing utilization of capacity by
increasing the efficiency of NAS resource usage.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The NAS
Resource Exchange System (NRES) has application in commercial air traffic
management (ATM) within the United States and abroad. In the United States ATM
market, the FAA will require the tools and procedures output by Phases II and
III of this SBIR to act as a central processor and tracker of ATM-induced
delays. At the same time, US air carriers will require tools with which to
monitor and manipulate their delay management accounts. Estimates of ATM costs
due to delays range from hundreds of millions of dollars to billions of dollars
per year. The opportunity to save even a fraction of these costs creates a
significant amount of motivation for airline participation in a delay management
system. It is reasonable to assume that the number of carriers willing to
participate in this system will be comparable to the number of carriers now
signed up as active members of the collaborative decision making (CDM) program,
which is 27. Air-traffic delays in foreign countries are generally not as
pronounced as in the U.S., but this has been achieved by sacrificing flexibility
in the system – a major limitation on the ability to handle growth in demand for
air transportation. For this reason, foreign ATM systems represent another
market for the delay management system.
TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and
Safety
| PROPOSAL NUMBER: | 06-I A3.01-9867 |
| SUBTOPIC TITLE: | Next Generation Air Transportation System - Airspace |
| PROPOSAL TITLE: | Dynamic Airspace Configuration Tool (DACT) |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Metron Aviation, Inc.
131 Elden Street,
Suite 200
Herndon, VA 20170-4758
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Arash Yousefi
yousefi@metronaviation.com
131 Elden Street, Suite 200
Herndon, VA 20170-4758
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron Aviation will develop
optimization algorithms and an automated tool for performing dynamic airspace
configuration under different operational scenarios. The Dynamic Airspace
Configuration Tool (DACT) takes as an input the regularly updated projections of
aggregated demand and weather forecasts and produces optimum airspace boundaries
that balance the airspace complexity under various global and regional
constraints for time horizons as short as four hours. The optimality criteria
are defined separately for different levels of automation in Air Traffic Control
(ATC) procedures. DACT enables the ATC managers to initiate high volume
operational corridors and other classes of airspace to best serve the user
demand for airspace resources. Additionally, when fully developed, DACT provides
a capability for airspace managers to dynamically manage the allocation of
Special Use Airspace (SUA) and Military Operation Airspace (MOA) to ensure
security of the airspace system. DACT enables a more efficient utilization of
airspace capacity and reduces the operational cost for air traffic control
services by dynamically re-aligning the airspace boundaries to comply with the
monthly, daily, and hourly alterations in user aggregated demand, route
structures, and changes in weather patterns. DACT address one of the main
components of NASA's NGATS Airspace effort in developing an operational
framework for DAC concept that provides the air traffic service providers with a
new degree of freedom to accommodate the user demand for airspace capacity,
balanced against needs of national interest (e.g. security). The proposed effort
will combine state of the art mathematical optimization techniques with ATC
functional requirements necessary for development of the DAC concept.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Airspace
capacity is limited by the ability of controllers to deal with complex traffic
situations. In congested areas of the National Airspace System (NAS), the
controller workload limitation is a critical capacity constraint that generates
significant en route delay. In today's rigidly structured airspace system, the
airspace managers do not have the flexibility to reconfigure the airspace based
on aggregated demand. The only local tactical solution is combining two or more
sectors and opening all or part of SUAs. These tactical modifications are not
well communicated with the users, and the resulted capacity is often lost. To
address these issues, NGATS envisions a more automated control system in which
tactical separation assurance is fully automated and controllers will perform
more strategic functions for managing the traffic. Accordingly, NASA's NGATS
Airspace effort [1] is envisioned to develop an operational framework for
Dynamic Airspace Configuration (DAC) (Milestone AS 3.3.01) that provides the air
traffic service providers with a new degree of freedom to accommodate the user
demand for airspace capacity, balanced against needs of national interest (e.g.
security). The DACT system proposed in this SBIR combines state of the art
mathematical optimization techniques (Milestone AS 1.3.03) with ATC functional
requirements necessary for deployment of the DAC concept.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
As demand
grows, more efficient procedures for airspace capacity management will be
required to address the users' demand. Both Europe and the United States have
reached a conclusion that airspace configuration should be dynamically adapted
to user aggregated demand. If fully developed, the DAC concept can potentially
change the ATM paradigm by introducing a revolutionary way for managing the
airspace capacity and entire aviation community can benefit from this new
concept. Estimates of ATM costs due to delays range from hundreds of millions to
billions of dollars per year. The opportunity to save even a nominal percentage
of these costs creates a significant amount of motivation for implementation of
the DAC concept. This concept can also result in long-term savings for the FAA
by reducing the controller workload and potentially decreasing the total number
of controllers in the NAS. In the US government ATM market, the primary sources
for funding are the organizations and agencies that maintain and improve the ATM
systems of the US. Because of our role at the ATCSCC, Metron Aviation is well
connected to these agencies. Similar to the US, the European airspace is
suffering from excessive delays due to airspace design inefficiencies and, as
such, European countries are other potential customers for decision support
tools and design methodologies related to DAC.
TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and
Control
| PROPOSAL NUMBER: | 06-I A3.02-8286 |
| SUBTOPIC TITLE: | Next Generation Air Transportation - Airportal |
| PROPOSAL TITLE: | Decision Support Tool and Simulation Testbed for Airborne Spacing and Merging in Super Dense Operations |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Intelligent Automation, Inc.
15400 Calhoun
Drive, Suite 400
Rockville, MD 20855-2785
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Vikram Manikonda
vikram@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville, MD
20855-2785
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation in this
effort is the development of a decision support tool and simulation testbed for
Airborne Spacing and Merging (ASM). We focus on concepts related to airports
with Super Dense Operations (SDO) where new airport runway configurations,
simultaneous operations on runways, simultaneous sequencing, merging
de-confliction and spacing are some of the proposed concepts currently being
considered. We focus on modeling and simulating a complementary airborne and
ground system for ASM. From a ground systems perspective a scheduler will
generate arrival sequences and spacing requirements that will be fed to the ASM
system operating on the flight deck. We propose to use and enhance NASAs ACES
software to model and simulate our concept. Our Phase I simulation will include
a prototype model of an airport emulating SDO and an implementation of airborne
spacing and merging algorithms implemented in the ACES flight agents. Integral
to our proposed effort will be the understanding future demand in terminal areas
as NAS transitions to NGATS type concepts and operations in 2025 including the
impacts of possible VLJ induced traffic. Using the simulations we will evaluate
the performance of our approach as air traffic densities increase, evaluate
controller workload and investigate extensions needed for totally airborne
autonomous operations.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our
initial target for the product developed in this effort is the NGATS modeling
and simulation community within NASA and FAA. The proposed approach and testbed
will provide a unique capability to model and simulate NGATS Airportal
operations.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential
target market for this technology are aerospace companies developing ADS-B based
automation tools for air traffic management. For this effort IAI has already
identified ACSS as out initial customer and has teamed with them in this effort.
TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling
Environment
Airport Infrastructure and Safety
On-Board Computing and Data
Management
Pilot Support Systems
Human-Computer Interfaces
| PROPOSAL NUMBER: | 06-I A3.02-8982 |
| SUBTOPIC TITLE: | Next Generation Air Transportation - Airportal |
| PROPOSAL TITLE: | Analysis and Mitigation of Increased Traffic Impacts on the Environment (AMITIE) |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Metron Aviation, Inc.
131 Elden Street,
Suite 200
Herndon, VA 20170-4758
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Terence Thompson
thompson@metronaviation.com
131 Elden Street, Suite 200
Herndon, VA 20170-4758
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron Aviation designs and
develops an integrated methodology and supporting algorithms for estimating
environmental impacts of increased traffic on the surface and in the terminal
airspace, and extends beyond estimation to identify key causes and develop
mitigation options. From previous work, we provide multi-dimensional impact
calculation in terms of noise, emissions, and fuel usage, as well as measurement
of these impacts with respect to both baseline and alternative future scenarios.
In AMITIE we add the following capabilities critically important to design of
the next-generation system within environmental constraints: • Automated
identification of scenario elements causing the principal environmental impacts;
• Automated generation of mitigation options; and • Quantification of the
benefits of the mitigation options. The specific technical objectives are: •
Integrated estimation/mitigation methodology that provides the basis for closing
the feedback loop from environmental impacts to system design and development. •
Develop supporting algorithms that calculate the appropriate metrics, analyze
them to identify major causes of impacts, and generate mitigation options that
reduce the impacts. • Develop a software prototype that implements the
estimation, analysis, and mitigation algorithms. • Exercise the prototype
against test cases to demonstrate the feasibility and value of the approach
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
needs for Next-Generation Air Transport System design, development, and
evaluation are being addressed by this project in order to estimate and mitigate
environmental constraints in such a way that the constraints can be met while
still enabling increased NGATS traffic density. NASA needs to estimate,
identify, and mitigate environmental impacts of many aspects of NGATS, including
such elements as Super Density Operations (SDO). Due to the surface and
terminal-area focus of SDO and the ambitious traffic increases being sought, and
the nature of the noise and emissions metrics, NASA will need to explore as many
different alternative design factors as possible. NASA will need to
quantitatively evaluate and defend the alternatives selected.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other
Government Agencies – Other Government agencies involved with the development of
NGATS include FAA and the Departments of Defense, Commerce, and Transportation.
Each of these agencies will face the need to estimate and mitigate environmental
impacts of different aspects of NGATS. The will also require quantitative
analysis of selected alternative design elements. Commercial - Aviation-related
commercial firms of all types (airlines, airports, aerospace companies,
consultants, etc.) need access to a methodology and algorithms that will help
them identify and mitigate the aspects of increased traffic that contribute most
to environmental impacts associated with aviation noise, emissions, and fuel
consumption.
TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and
Safety
| PROPOSAL NUMBER: | 06-I A3.02-9623 |
| SUBTOPIC TITLE: | Next Generation Air Transportation - Airportal |
| PROPOSAL TITLE: | Airport Configuration Planner with Optimized Weather Forecasts |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Metron Aviation, Inc.
131 Elden Street,
Suite 200
Herndon, VA 20170-4758
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Laurel Stell
stell@metronaviation.com
131 Elden Street, Suite 200
Herndon,
VA 20170-4758
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The core planning algorithms
to support the NGATS concepts will need accurate predictions of airport
configuration over planning horizons of six hours or more. Such predictions are
not currently feasible because the configuration often is not completely
determined by factors such as weather forecasts, future demand, and noise
restrictions that might be input to an automated predictor. When this is the
case, the air traffic control tower personnel choose between the feasible
configurations based on factors such as staffing issues and individual
controller preferences. Furthermore, the primary meteorological forecasts
currently available to the tower are not adequate to enable accurate runway
usage prediction. In fact, they often fail to predict required changes in flow
direction, causing reactive rather than proactive airport configuration
management. In this SBIR, Metron Aviation and WSI Corporation will jointly
develop an airport configuration planner incorporating optimized weather
forecasts to assist tower controllers in planning runway usage more accurately
at longer time horizons than currently possible and to communicate the plan to
appropriate National Airspace System (NAS) stakeholders and planning systems.
The optimization algorithms in this decision support tool will improve resource
allocation not only at individual airports but also over all airports in a
metropolitan area.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
airport configuration planner developed in this SBIR will enable dynamic airport
configuration management by using improved meteorological forecasts, optimizing
resource allocation for individual airports and also over all airports in a
region, and automating communication between the tower and other FAA facilities,
planning systems, and NAS stakeholders. This tool will also result in reliable
configuration plans necessary for other NGATS concepts, including block-to-block
4D trajectories and super-density operations. In short, maximizing throughput of
a runway complex and optimizing efficient use of airport resources depends upon
these reliable configuration plans, which can only be obtained with better
weather forecasts. Furthermore, including tower controller feedback in the
planning process will allow them the flexibility they need and avoid incorrect
predictions when unforeseen circumstances arise.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The FAA will
require the planner developed in this SBIR to implement the NGATS vision. The
optimization algorithms in this tool will improve airport throughput and
efficiency; whilst the tower controller feedback in the planning process will
maintain flexibility. By basing the plan on improved meteorological forecasts,
airport configuration management will be more proactive and less reactive. By
automating the communication of the plan between FAA facilities, air traffic
management coordination will be improved. It will assist communication between a
TRACON and towers within that TRACON to plan and implement configuration
changes. It will automate the communication of planned configurations and
arrival and departure rates to the FAA Command Center, which will improve the
planning of traffic management initiatives such as GDPs. The configuration
planner will also communicate the configuration plan to FAA customers, allowing
them to improve their planning to better achieve their goals and objectives.
TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and
Safety
| PROPOSAL NUMBER: | 06-I A4.01-8240 |
| SUBTOPIC TITLE: | Test Measurement Technology |
| PROPOSAL TITLE: | Fiber-Optic Etalon Pressure Sensor System with High Thermal and Mechanical Stabilities |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Structured Materials Industries, Inc.
201
Circle Drive North, Suite 102/103
Piscataway, NJ 08854-3723
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Jie Yao
jyao@structuredmaterials.com
201 Circle Drive North, Suite 102/103
Piscataway, NJ 08854-3723
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Atmospheric pressure sensing
in particular is of critical importance to any attemp of Mars landing. Pressure
sensing has traditionally always drawn high interest from the military due to
its applications to high-performance military airplanes and helicopters,
missiles and ballons. Aerodynamics also find its applications in civilian
aviation. After over 100 years of research and development, most powered
aerodynamic experiments can be accurately simulated numerically on a computer
today. However, aerodynamic experiments and measurements are still needed for
the input parameters to the simulation, for the final verification of results
and routine monitoring of performance. As a matter of fact, precision
aerodynamic measurements gain ever higher importance today than before. There
are 3 special challenges of measuring pressure on Mars: (1) the thin atmosphere
requires high ensitrivity sensors; (2) the extreme temerature range; and (3) the
survival of the landing impact. This proposal address them all. At home on the
Earch, air pressure measurements reveal a lot of useful information about
aircraft engine performance, about the air flow on aircraft wings, about the
on-blade dynamic pressure of a helicopter, and about the optimal design and
motion of a parachute among other things. The unique advantage of our solution
lies in its high stability against temperature variations and mechanical
disturbances, rendering the proposed system rugged and robust enough for Mars
landing and exploration while keeping the cost at the level of commercial off
the shelf fiber-optic communications systems. In Phase I of this program, we
propose to demonstrate a bench-top system with several high-sensitivity etalon
pressure sensors with high temperature and mechanical stability. In Phase II, we
will develop the complete pressure sensor system using existing fiber optic
components with monitoring and feedback control software.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Mars
atmospheric pressure sensing for landing and exploration
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
(1) earth
atmospheric pressure sensing for weather and environmental studies (2) on-blade
pressure measurement for helicopters (3) aircraft engine health monitoring (4)
aerodynamic pressure sensing for prototyping parachutes.
TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Optical
Sensor
Webs/Distributed Sensors
Semi-Conductors/Solid State Device
Materials
Aircraft Engines
| PROPOSAL NUMBER: | 06-I A4.01-8326 |
| SUBTOPIC TITLE: | Test Measurement Technology |
| PROPOSAL TITLE: | Retroreflector Array for Test Environments (RATE) |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Research Support Instruments, Inc.
4325-B
Forbes Blvd.
Lanham, MD 20706-4854
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
John Kline
kline@researchsupport.com
4325-B Forbes Blvd.
Lanham, MD
20706-4854
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Research Support Instruments,
Inc. (RSI) proposes to develop the Retroreflector Array for Test Environments
(RATE), an innovative technology that will non-intrusively measure pressure on
aerodynamic surfaces in NASA ground test facilities with high sensitivity and
bandwidth. The signal from RATE units will change locally due to pressure
changes. Pressure sensitive paints, in comparison, have serious drawbacks: they
must applied to a rigid surface, are specific to the flow species, and do not
retroreflect. Because RATE will be independent of the flow species, and applied
as a very thin, flexible, adhesive material, it will be able to measure the
aerodynamic pressure while minimizing changes in the flow field. The Phase I
RATE program will involve design, fabrication, and test of various candidate
designs in order to select the most promising approach for Phase II. RSI will
use its experience in microfabricated structures and pressure sensors to employ
a highly innovative technology in order to non-intrusively measure aerodynamic
pressure in NASA ground test facilities. The result will be a product that will
address a critical NASA instrumentation need.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
will use the technology for non-intrusive wind tunnel diagnostics; there is a
need for a pressure diagnostic with high sensitivity, ruggedness for
survivability during wind tunnel startup, and that will not alter the flow
field. In addition, NASA can employ the RATE sensors in flight tests because the
retroreflector divergeance will provide high signal at long ranges; the sensors
will be useful for NASA flight vehicle monitoring for the same reason.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition,
several non-Government applications are possible. Pressure sensors have a
lucrative commercial market in manufacturing (for process monitoring) and
medical diagnostics, as well a healthy market in scientific applications.
Sensors that can be applied as an adhesive patch to existing devices will be
very attractive, particularly if they are thin, sensitive, and robust.
TECHNOLOGY TAXONOMY MAPPING
Propellant
Storage
Perception/Sensing
Control
Instrumentation
Inflatable
Testing Facilities
Guidance, Navigation, and
Control
Biomedical and Life Support
Instrumentation
Optical
Sensor
Webs/Distributed Sensors
Portable Life Support
Photonics
| PROPOSAL NUMBER: | 06-I A4.01-9662 |
| SUBTOPIC TITLE: | Test Measurement Technology |
| PROPOSAL TITLE: | Measurement and Assessment of Flow Quality in Wind Tunnels |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Complere, Inc.
P.O. Box 541
Pacific
Grove, CA 93950-0541
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Kevin Owen
kevin@complereinc.com
P.O. Box 541
Pacific Grove, CA
93950-0541
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With increased commercial
competition, great pressure is being applied to effect aerodynamic design
changes that will improve fuel economy and performance. But, for example, as we
are now concerned with small changes in drag count, potential sources of
improvement are much more likely to be masked by poor flow quality. We may have
reached the stage where the lack of suitable facility flow quality will hinder
and dictate the rate of progress of ground based testing. Few measurements have
been made in the Nation's wind tunnels, and in those cases, large discrepancies
have been found between full-scale and predicted performance. Consequently,
there is an urgent need for in-situ measurements to measure flow quality and the
performance of turbulence and noise suppression devices. To meet these
challenges, a unique research program is proposed to clarify and alleviate the
aerodynamic problems associated with adverse wind tunnel flow quality. It
combines innovative advances in data base assessment and management, and new
approaches to turbulence instrumentation and analysis. Standardized turbulence
measurement techniques and data analysis procedures will be established and used
to document the flow quality in our major test facilities.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There is
a national need to develop improved test capabilities for proposed civil and
military aerospace systems. Detailed flow quality measurements and assessments
of the performance of turbulence and noise suppression devices will lead to cost
effective improvements in wind tunnel flow quality which will be needed to help
design and ground test the proposed new generation of fuel efficient commercial
transports and advanced military aircraft proposed for the new millennium.
Standardized test procedures will enable meaningful assessments to be made of
individual tunnel operational ranges with adequate flow quality related to
specific test programs. These advances will help provide NASA with superior test
capabilities at competitive cost and so attract a viable customer base that will
be required for cost-effective facility operations.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Measurements
are urgently needed in the Nation's major facilities if we are to successfully
combat the ever increasing European test facility challenge. Wind tunnel
disturbances must be measured to the highest accuracy to allow the
aerodynamicist to distinguish between aerodynamic, aeroelastic, and Reynolds
number effects. Measurements will help provide U.S. companies with superior test
capabilities at competitive cost and so help attract a viable customer testing
base that will be required for cost effective facility operations. This
state-of-the-art turbulence testing capability available to support commercial
aerospace needs meets two of the three main goals of NASA's Aeronautics Test
Program (ATP) for corporate management of Aeronautical facilities namely: to
"increase the probability of having the right facilities in place at the right
time" and to "operate those facilities in the most effective and efficient
manner."
TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Testing
Requirements and Architectures
| PROPOSAL NUMBER: | 06-I A4.01-9960 |
| SUBTOPIC TITLE: | Test Measurement Technology |
| PROPOSAL TITLE: | Autonomous Facility Health-Enabled Test Instrumentation |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Mobitrum Corporation
8070 Georgia Avenue,
Suite 209
Silver Spring, MD 20910-4973
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Ray Wang
rwang@mobitrum.com
8070 Georgia Avenue, Suite 209
Silver Spring, MD 20910-4973
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The combination of smart
devices and embedded metadata and networked (wire and wireless) technologies
present real opportunities for significant improvements in reliability,
cost-benefits, and safety for remote testing, performance measurement, and
facility management. Adding robust and autonomous network protocol for routing
will further simplify testing installation process and increase test facility
reliability. However, the realization of a practical autonomous facility test
system requires the synthesis of several technologies. One must bring together
knowledge in the fields of sensors, data processing, distributed systems, and
networks. Mobitrum proposes to develop "an autonomous facility health-enabled
test instrumentation" for characterization and measurement of ground test
facilities. The proposed device includes: (1) facility health-enabled sensor,
(2) signal conditioning and analog-to-digital (digital-to-analog) conversion,
(3) microprocessor, (4) on-board memory (e.g., Flash or EEPROM) for metadata
storage and executable software, and (5) embedded network interfaces to create a
powerful, scalable, re-configurable, and reliable distributed test instrument.
Autonomous facility health-enabled test instrumentation is built upon an
open-system architecture with standardized protocol modules easily to interface
with industry standards.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Ground
testing of propulsion systems is a critical requirement to enable NASA's New
Vision for space exploration. The proposed visual sensor test instrumentation
will enable a cost effective remote testing and health monitoring through
wireless sensor network. Mobitrum anticipates the following applications that
NASA will benefit from the proposed technology: 1) Data analysis, processing,
and visualization for Space exploration and Earth science observations, 2)
Rocket engine test, 3) Remote test facility management, 4) Field communications
device for spatial data input, manipulation and distribution, 5) Sensor,
measurement, and field verification applications, 6) RFID for identification and
tracking, 7) Condition-aware applications, 8) Location-aware applications, 9)
Biometric identification applications. 10) Data collaboration and distribution
applications, and 11) Wireless instrumentation for robotic manipulation and
positioning for audio and visual capture, and real-time multimedia
representation.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We believe the
application of smart embedded test data acquisition device will have tremendous
potential for commercial market. That is because global revenues for smart
pressure, flow, force/load, and temperature sensors with signal
conditioning/amplification capability collectively totaled about $3.4 billion,
according to SBD's latest data. We anticipate the embedded data acquisition and
health-monitoring device will enable more home applications for energy control
and security monitoring provided by Internet service providers through value-add
services. Commercial applications are: 1) Home control, 2) Energy management for
cost saving, 3) Security (intruder detection), 4) Safety (sensing), 5) Utility –
remote meter reading, 6) Building automation systems – real-time monitoring and
control of security and surveillance systems, alarms, HVAC, etc., 7)
Manufacturing and distribution – industrial automation using RFID, 8) Health
care – wireless monitoring equipments.
TECHNOLOGY TAXONOMY MAPPING
Human-Robotic
Interfaces
Intelligence
Mobility
Perception/Sensing
Operations
Concepts and Requirements
Simulation Modeling Environment
Training
Concepts and Architectures
Testing Facilities
Testing Requirements and
Architectures
Spaceport Infrastructure and Safety
Telemetry, Tracking and
Control
Ultra-High Density/Low Power
Airport Infrastructure and
Safety
On-Board Computing and Data Management
Waste Processing and
Reclamation
Architectures and Networks
Autonomous Control and
Monitoring
RF
Instrumentation
Computer System Architectures
Data
Acquisition and End-to-End-Management
Data Input/Output Devices
Database
Development and Interfacing
Expert Systems
Human-Computer
Interfaces
Portable Data Acquisition or Analysis Tools
Software Tools for
Distributed Analysis and Simulation
Sensor Webs/Distributed
Sensors
Portable Life Support
Tools
General Public Outreach
K-12
Outreach
Mission Training
Computational Materials
Multifunctional/Smart
Materials
Wireless Distribution
| PROPOSAL NUMBER: | 06-I X1.01-8518 |
| SUBTOPIC TITLE: | Full Data Coherency Systems for Engineering Systems Modeling and Simulation |
| PROPOSAL TITLE: | Application Coherency Manager |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Cybernet Systems Corporation
727 Airport
Boulevard
Ann Arbor, MI 48108-1639
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Glenn Beach
gbeach@cybernet.com
727 Airport Blvd
Ann Arbor, MI 48108-1639
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes an
Application Coherency Manager that implements and manages the interdependencies
of simulation, data, and platform information. It will also enforce a simulation
configuration profile submission that includes the specification of the
interdependency requirements. To describe these interdependences, a
general-purpose language will serve as the basis for higher-level rules that are
assembled using a higher-level graphical user interface. We propose to implement
a graphical user interface that allows the user to manage and assemble
rule-profiles. A rule profile would be created by assembling and parameterizing
one or more low-level code modules. This user interface would then be able to
save these profiles into a revision archive, perhaps alongside the applications
and the data sources. These profiles could then be checked out, and used.
Locking the version of such a profile would freeze it in a known state. Leaving
it unlocked would allow it to evolve. The profiles themselves would likely be
stored as XML-based documents that refer to the low-level data-source checker
modules
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
development of this ACM technology is consistent with the simulate-first
methodology used at NASA. The ACM technology described in this proposal would
improve the effectiveness of NASA simulation technologies.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ACM
technology has definite application in the enhancement of an existing Cybernet
commercial effort. This is a virtual prototyping architecture for designing and
virtually testing Vetronics (vehicle electronics) systems. This system is known
as the Virtual Simulation Integration Lab (VSIL). With the VSIL, Cybernet is
developing simulation models for various Vetronic components. The VSIL supports
rapid model development, model change, and test of virtual Vetronics systems.
This system is able to import Vetronic components of varying age, which leads to
the exact problem this proposal addresses. The integration of an ACM front-end
to the VSIL system will increase its value and usability and will make it a more
attractive option within the DoD and commercial Vetronic-related applications.
TECHNOLOGY TAXONOMY MAPPING
Expert Systems
| PROPOSAL NUMBER: | 06-I X1.02-8978 |
| SUBTOPIC TITLE: | System Lifecycle Integration of Cost and Risk Models |
| PROPOSAL TITLE: | I-RaCM: A Fully Integrated Risk and Lifecycle Cost Model |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
SPACEWORKS ENGINEERING, INC. (SEI)
1200
Ashwood Parkway, Suite 506
Atlanta, GA 30338-4747
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Dominic DePasquale
dominic.depasquale@sei.aero
1200 Ashwood Parkway, Suite 506
Atlanta, GA 30338-4747
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SpaceWorks Engineering, Inc.
(SEI) proposes development of the Integrated Risk and Cost Model I-RaCM, as the
innovation to meet the need for integrated cost and risk assessment early in the
design of a new system. I-RaCM will integrate a diverse set of new and
industry-standard tools used for life cycle cost, operations, reliability
modeling, and estimation of technology development costs. The I-RaCM platform
will provide seamless integration between tools, perform all data exchange, and
interface with the performance disciplines.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A
software product for use by NASA to determine financing, long-term support
costs, evaluate the impact of risk and reliability on mission success, and
assess the economic case for a venture. A spin-off software product, service, or
consultancy where early consideration of cost and risk is important. Use in
consultation work by SEI to support government or industry space concept design,
development, and analysis.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A software
product for use by commercial space companies or financial analysts to determine
financing, long-term support costs, evaluate the impact of risk and reliability
on mission success, and assess the economic case for a venture. A stand-alone
software product for use by NASA, Air Force, NRO, and other government aerospace
and defense agencies. A spin-off software product, service, or consultancy for
sale to other government agencies and commercial organizations where early
consideration of cost and risk is important. Use in consultation work by SEI to
support government or industry space concept design, development, and analysis.
TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and
Requirements
Spaceport Infrastructure and Safety
Software Development
Environments
Software Tools for Distributed Analysis and Simulation
| PROPOSAL NUMBER: | 06-I X1.02-9567 |
| SUBTOPIC TITLE: | System Lifecycle Integration of Cost and Risk Models |
| PROPOSAL TITLE: | System Engineering Software Assessment Model for Exploration (SESAME) |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Payload Systems, Inc.
247 Third
Street
Cambridge, MA 02142-1129
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
James Francis
francis@payload.com
247 Third Street
Cambridge, MA 02142-1129
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Concept phase space-systems
architecture evaluations typically use mass estimates as the primary means of
ranking potential mission architectures. Software does not directly have
physical mass and, as a result, is often left-out of such evaluations, despite
the potential of being one of the main contributors to a mission's overall cost
and risk. During NASA's Concept Exploration and Refinement (CE&R) program,
personnel from MIT, Draper Laboratories, and Payload Systems Inc. developed a
systems architecture software assessment approach that addresses both the early
concept phases of a program and the complexities of critical embedded software
systems. This approach uses a series of weighted software and human-computer
interaction parameters that evaluate how a system's architecture affects
software. Payload Systems Inc. proposes to validate this Systems Engineering
Software Assessment Model for Exploration as the next step on the path to a tool
that provides early, reliable ranking of systems architectures based on
software. The Phase I effort will focus on validation of this assessment tool.
This validation will be based on embedded spaceflight systems projects. Once
validated, this assessment approach will provide a basis, during Phase II, for
the development of a Systems Engineering tool for assessing the impact candidate
system architectures on software.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This
systems engineering software assessment was specifically aimed at elements of
NASA's Exploration Initiative, where early decisions in systems development have
a significant impact on the overall software development, maintenance, and
human-computer interaction cost and risk. Additionally, this model is applicable
for any number of NASA programs that require embedded software development, such
as Constellation-X, the James Webb Space Telescope, and the Laser Interferometer
Space Antenna.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This systems
engineering software assessment model is applicable to DoD and commercial
projects that require modeling and assessments of embedded software development
cost and risk and human-computer interaction costs and risks. These include
aircraft avionics systems, medical instrumentation systems, optical
communications monitoring systems, etc.
TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and
Safety
Computer System Architectures
Human-Computer Interfaces
Portable
Data Acquisition or Analysis Tools
| PROPOSAL NUMBER: | 06-I X2.01-8204 |
| SUBTOPIC TITLE: | Integrated Systems Health Management |
| PROPOSAL TITLE: | Automated Fault Diagnostics, Prognostics, and Recovery in Spacecraft Power Systems |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Qualtech Systems, Inc.
100 Great Meadow
Rd., Suite 603
Wethersfield, CT 06109-2355
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Sudipto Ghoshal
sudipto@teamqsi.com
100 Great Meadow Rd., Suite 603
Wethersfield, CT 06109-2355
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Constellation Program, the
next frontier of NASA's space exploration plan, targets for manned mission to
Moon and Mars. The missions under this program will be of long-duration and far
more critical than any previous manned mission. Integrated Systems Health
Management (ISHM), which includes fault detection, diagnosis, and prognosis, has
been recognized as one of the critical processes that will enhance system
functionality, mission success probability and crew safety for these missions.
In addition, ISHM should support in deciding reactionary actions in response to
a system failure or a failure precursor, i.e., the system recovery functions.
Spacecrafts for the constellation program requires a significant degree of
autonomy – that includes the ability to monitor their own health and perform
mission objectives in the wake of unexpected events (faults, failures, etc). In
response to the needs stated in the solicitation topic x2.01, Qualtech Systems,
Inc. (QSI) proposes to develop novel diagnostic, prognostic, degradation
analysis and automated recovery techniques for spacecraft power systems. The
proposed effort will use reactive mission planner technologies for formulating
recovery options and mission re-planning to accommodate for degradation in power
systems. Inclusion of the resulting technologies will streamline cost of
long-duration space missions and enhance the mission success probabilities.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Resulting technologies from proposed effort will aid in
streamlining the mission planning and support cost for NASA's Constellation
Program. The efforts will also lead to techniques and software packages that
will be readily deployable for integrated system health management (ISHM) in
Orion, the crew exploration vehicle (CEV) of the constellation program. The
technologies and processes can be utilized in the crew launch vehicle (CLV) and
long-duration unmanned space missions.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aviation
industry (and operators), commercial communication satellite manufacturers and
operators, automotive industries and cruise ship operators are the potential
non-NASA civil sectors who will be interested in this technology. Fault
diagnosis, prognosis, degradation analysis and automated recovery are of special
importance to these sectors. In addition, all these industries are interested to
employ reactive mission planning into their manufacturing and/or service
operations. DoD, Navy, Airforce, and MDA are the potential military customers of
the resulting technology. These agencies will be specifically interested into
the automated reactive mission planning process.
TECHNOLOGY TAXONOMY MAPPING
Pilot Support Systems
Autonomous
Reasoning/Artificial Intelligence
Power Management and Distribution
| PROPOSAL NUMBER: | 06-I X2.01-9421 |
| SUBTOPIC TITLE: | Integrated Systems Health Management |
| PROPOSAL TITLE: | Integrated Health Management for Space Flight Digital Systems |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
RIDGETOP GROUP, INC.
6595 N Oracle Rd,
Suite 153B
Tucson, AZ 85704-5645
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Justin Judkins, PhD
justin@ridgetop-group.com
6595 N Oracle Rd, Suite 153B
Tucson,
AZ 85704-5645
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal addresses the
need for a real-time Prognostics and Health Management (PHM) system to identify
anomalous states in digital electronic systems used in spaceflight applications
and recommend corrective actions. We identify promising host platforms for
implementation of PHM and consider strategies for identifying faults at the
board level. Models for each approach are developed for further study of the
effectiveness in identifying faults, estimating system states, and identifying
anomalous states. Each method is then ranked with respect to prognostic fault
coverage (state-awareness), missed alarms, and false alarms. Finally, a strategy
is developed to optimally and dynamically reconfigure or recover the digital
system based on current or predicted system status given by the
prognostic/reasoner approach and board topology. By responding to a need for
greater health awareness in complex on-board digital systems, the technology
developed in this project will improve safety and effectiveness of future
spaceflight missions, and improve serviceability and availability throughout the
system lifecycle.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Ridgetop's plans are to work closely with NASA on the application
of electronic prognostics to a representative electronic network system within
NASA. Also, prognostics can support remote diagnostics/prognostics. The value
proposition is that early detection of impending failures can be made remotely,
via the web, and corrective actions quickly employed to preserve overall system
integrity. With remote systems deployed on other planets, autonomous operation
enabled with electronic prognostics is very important. Advance warnings and
mitigation of failures are facilitated using electronic prognostics that detect
an impending failure before it occurs. Another potential application of
Ridgetop's technology would be the Advanced Diagnostic Systems (ADS) project,
which is interested in reasoners and PHM in the Space Station. Among the level 1
requirements for the Crew Exploration Vehicle (CEV) is rapid launch capability,
enabling its use as a Crew Rescue Vehicle for the Orbital Space Station in the
event of an emergency. Ridgetop has developed ground-based prognostic tools that
can be leveraged to develop applications that provide ground-based logistic
support for spaceflight hardware on NASA vehicles. A final example is the NASA
Space Shuttle. By using electronic prognostics with mission critical systems, we
can reduce false alarms, thereby reducing instances of potentially expensive and
unsafe abort-after-liftoff due to false alarm of sensors in critical systems.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Through the
work on this SBIR, Ridgetop will improve its market position in Electronic
Prognostics and be able to capitalize on a large market. Ridgetop has initiated
commercialization activities stemming from its prior work in prognostics with
the introduction of the Sentinel Silicon<SUP>TM</SUP> Library and
Sentinel PHMPro<SUP>TM</SUP> products. There is a large potential
for prognostics in the commercial sector, which is expected to exceed $200M by
2010. Ridgetop has segmented the market to focus on high reliability
applications, such as automotive, banking system, industrial process control,
and commercial aerospace. Prognostics, to the extent that it can leverage
existing diagnostic backbones such as JTAG, I2C, and CAN buses, supports
Condition Based Maintenance (CBM) and Prognostics and Health Management (PHM)
strategies for critical industrial applications. For CBM and PHM applications,
the value of preserving operational readiness is paramount and these
applications are not expected to be cost-sensitive. One useful application of
this prognostic approach is to monitor the health of electronic power systems.
Monitoring of trends may provide an estimation of system level RUL. Self-healing
and dynamic resource allocation provide the best approach with respect to
visibility, availability, and serviceability of electronic power. Tools will be
developed for application across multiple industries, such as commercial
aviation and automotive.
TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and
Safety
Architectures and Networks
Autonomous Control and
Monitoring
Autonomous Reasoning/Artificial Intelligence
Database
Development and Interfacing
Expert Systems
Human-Computer
Interfaces
Portable Data Acquisition or Analysis
Tools
Tools
Highly-Reconfigurable
| PROPOSAL NUMBER: | 06-I X2.02-8873 |
| SUBTOPIC TITLE: | Spacecraft Autonomy |
| PROPOSAL TITLE: | System-Level Autonomy Trust Enabler (SLATE) |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Adventium Enterprises, LLC
111 Third Ave.
S., Suite 100
Minneapolis, MN 55401-2551
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Mark Boddy
mark.boddy@adventiumenterprises.com
111 Third Ave. S., Suite 100
Minneapolis, MN 55401-2551
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR project will achieve
trusted, reconfigurable, intelligent autonomy through system-level validation.
The goal is to design and develop a representation and reasoning system for
system-level verification and validation (V&V) of high-level autonomous
control for complex systems operating in dynamic environments. Starting from
component-level behavioral guarantees, the System-Level Autonomy Trust Enabler
(SLATE) will reason about composition, abstraction, and embedding of system
components, resulting in high-confidence guarantees of behavior for high-level
autonomous control systems relevant to a wide range of NASA applications,
including manned and unmanned spacecraft, rovers, and habitats. SLATE will
support incremental computation of guarantees and the assumptions required,
vastly simplifying the reconfiguration, upgrading, or retargeting of autonomous
control systems. Phase I will provide a feasibility demonstration and evaluation
of SLATE's representation and inference through application to a multi-level
robotic control system, and identify the key features needed in an
application-ready version of SLATE. Phase II will develop an
application-specific version and provide a user interface, address performance
and reasoning issues, and demonstrate operation on a representative NASA
application.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
SLATE
has the potential to be useful on any NASA mission requiring some form of
complex automation, whether or not the mission is manned. The initial
application areas targeted will include 1) Autonomous Rendezvous and Docking
(ARD) applications relevant to Mission to Mars, Mars Sample Return, Mini-AERCAM,
Orbital Express (DARPA), and earlier programs such as DART, XSS-11 (AFRL), and
Automated Transfer Vehicle and 2) Rover-based exploration, mapping, and resource
extraction systems on the moon and Mars, or 3) other relevant application as
directed by NASA.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential
design and V&V benefits of this SBIR extend beyond space-based systems to
include other complex, high-value, life-critical control systems. Customers for
such products or systems include military users of high autonomy systems,
particularly unmanned aerial vehicles (UAV) and unmanned combat air vehicles
(UCAV), and especially UAV sensor platforms, which are moving into domestic
arenas and so need to fly in national air space with correspondingly stringent
V&V requirements. Other potential customers include airframe integrators and
supporting vendors, US critical infrastructure owners with significant
unattended operating requirements such as remote pumping and transfer stations,
and requirements design and analysis vendors.
TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and
Requirements
Testing Requirements and Architectures
Telemetry, Tracking
and Control
Attitude Determination and Control
Guidance, Navigation, and
Control
On-Board Computing and Data Management
Architectures and
Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial
Intelligence
Expert Systems
Software Development Environments
| PROPOSAL NUMBER: | 06-I X2.02-9743 |
| SUBTOPIC TITLE: | Spacecraft Autonomy |
| PROPOSAL TITLE: | A Data Abstraction Architecture for Spacecraft Autonomy |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Traclabs, Inc.
8610 N. New Braunfels, Suite
110
San Antonio, TX 78217-2356
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
David Kortenkamp
korten@traclabs.com
1012 Hercules
Houston, TX 77058-2356
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Spacecraft generate huge
amounts of data. A significant challenge for both human operators and autonomous
control systems is ensuring that the right data (and combinations of data) are
available at the right time for control and decision-making and ensuring that
the data is at the right abstraction level. A key part of this process is data
abstraction -- that is converting low-level analog or digital signals into
higher-level data. We are proposing a data abstraction architecture that
provides a provides a tool-box of components, connections and development
environment that allow engineers to build and maintain data abstraction systems.
In addition, having a well-defined data abstraction architecture allows data
displays to be automatically generated and updated as the architecture develops.
Thus, a data abstraction architecture can support both human decision-making as
well as providing data services to autonomous control systems. We are also
proposing to build an integrated development environment in which designers or
operators can graphically build data abstraction architectures from standard
components to accomplish their data tasks. Together these provide a data
abstraction architecture that is a key component of NASA's operational
infrastructure and provides a building block for deploying more advanced
autonomy architectures in the future.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The new
collection of exploration vehicles (called Constellation) will require the
integration of a variety of software components from a variety of different
contractors. Managing the flow of data from these components and assembling it
into a coherent picture, whether for human decision-makers or autonomy, will be
difficult. A standard data abstraction architecture will be important. We will
target markets such as the eventual Crew Exploration Vehicle (CEV) prime
contractor (either Boeing/Northrop or Lockheed Martin). We will also target NASA
Mission Operations Directorate (MOD) as a customer for data abstraction in
ground operations. In addition, robotic missions and uncrewed space vehicles
offer opportunities for deploying data abstraction architectures.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Unmanned
vehicles, both air and ground, are becoming more and more common in battlefield
situations. Future Combat Systems (FCS) envision manned and unmanned vehicles of
all sizes working side-by-side. In addition, Congress has mandated that
one-third of all military vehicles must be unmanned by 2015. Whether these
vehicles are operated remotely or are autonomous they will need data abstraction
architectures. As information streams from these systems to centralized command
and control centers data abstraction and data presentation will be key. An
architecture that allows different vendors to combine data will be beneficial to
the military. Intelligence agencies offer other applications for a data
abstraction architecture. As data is collected from a variety of assets it needs
to be merged, abstracted and displayed in a variety of forms. Being able to
easily configure a data abstraction architecture for a variety of different
domains will be extremely beneficial.
TECHNOLOGY TAXONOMY
MAPPING
Intelligence
Perception/Sensing
Autonomous
Reasoning/Artificial Intelligence
Human-Computer Interfaces
Software
Development Environments
| PROPOSAL NUMBER: | 06-I X2.03-8550 |
| SUBTOPIC TITLE: | Software Engineering Technologies for Human-Rated Spacecraft |
| PROPOSAL TITLE: | Static Detection of Bugs in Embedded Software using Lightweight Verification |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Grammatech Inc
315-317 N. Aurora
Street
Ithaca, NY 14850-4201
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Ray Teitelbaum
tt@grammatech.com
315-317 N. Aurora Street
Ithaca, NY
14850-4201
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Validating software is a
critical step in developing high confidence systems. Typical software
development practices are not acceptable in systems where failure leads to loss
of life or other high costs. New software development tools are needed to
radically reduce defect rates and enable the high levels of confidence required
for safety- and security-critical systems. Lightweight verification techniques
have proven themselves effective in finding defects in large software systems by
balancing rigor with scalability and usability. Lightweight verification
techniques do not exhaustively check software, but they can find defects in
systems that are too large for more rigorous analysis techniques, and are fast
becoming an essential tool for software developers. The techniques generally
fail to address key sources of problems specific to embedded systems: paths due
to asynchronous transfer of control or context switches between tasks are not
considered; assembly language components are ignored; it is hard to detect
violations of domain-specific rules. We propose to extend and adapt our static
analysis technology to make it capable of addressing these problems. We will
exploit our existing connections with NASA facilities to gain help validating
our approach and to ensure that the solution we propose is responsive to NASA's
unique needs.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
results of this research are expected to be of immediate use to NASA. Our
existing CodeSonar and CodeSurfer tools are already in use in several
facilities, including JSC, KRC, GRC, and IV&V. They are being used for code
understanding and inspections, and for finding flaws in both flight and ground
software. Improvements to the technology developed under this proposal are
expected to improve the recall and precision of the flaw-detection capabilities,
thus allowing users to find more flaws, more accurately, and in less time. These
improvements will be funneled into the product line, thereby benefiting users at
these locations quickly. Our existing connections with these NASA facilities
will be exploited during the course of the project to help us make sure that our
solutions are relevant to NASA.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Lightweight
verification tools such as CodeSonar are becoming increasingly popular in many
industrial sectors, especially those concerned with developing high-confidence
real-time embedded software. This includes communications, military/aerospace,
medical devices, automotive, finance, security, and others. If successful, the
technology we propose to develop will provide the capability to find more
serious flaws in such software than current approaches, thereby cutting
development costs and increasing code quality.
TECHNOLOGY TAXONOMY MAPPING
Testing Requirements and
Architectures
Software Development Environments
| PROPOSAL NUMBER: | 06-I X2.03-9178 |
| SUBTOPIC TITLE: | Software Engineering Technologies for Human-Rated Spacecraft |
| PROPOSAL TITLE: | Analytical Methods for Verification and Validation of Adaptive Systems in Safety-Critical Aerospace Applications. |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Contek Research, Inc.
615 Nash Street,
Suite 220
El Segundo, CA 90245-2827
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Fola Soares
fola@contekresearch.com
P. O. Box 88758
Los Angeles, CA
90009-6758
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A major challenge of the use
of adaptive systems in safety-critical applications is the software life-cycle:
requirement engineering through verification and validation. Adaptive systems
incorporate learning to adapt the control system to the current operating
conditions of the system, certifying their performance is a complex and tedious
process. Ongoing effort in the development of tools for verification and
validation of adaptive control systems, there is little research directed at the
development of analytical methods. Learning rules for adaptive systems
derivation using Lyapunov's second method, is based on the derivation of an
energy-type function whose derivative must be negative to guarantee convergence
therefore the asymptotic stability of the system. The first problem is that
Lyapunov's second method provides a sufficient condition for stability thus the
synthesis of an appropriate Lyapunov function for a particular application is a
major challenge. The second problem in many applications, including the design
of adaptive neural flight control systems, it is only possible to prove that the
derivative of the Lyapunov function is non-positive, rather than being negative.
For practical purpose, it is only possible to conclude that the control system
errors are ultimately bounded, and it not possible to estimate the magnitude of
these errors or the time it takes for these errors to converge to their
steady-state limits. The objective of this research project is to develop
analytical methods for the analysis of adaptive neural networks (ANN) based
flight control systems including analytical estimates of the settling time and
the steady-state magnitudes of the error dynamics. The magnitudes of the error
bounds will be related to the performance handling qualities of the system and
provide very important information about the performance of the closed-loop
system.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed technology is designed to be compatible with current safety
requirements for conducting aircraft systems ground and flight tests in order to
take advantage of the state of the technology in expert system. A goal of NASA
is to establish new levels of autonomy and robustness within aerospace vehicles.
NASA believes these higher levels can be realized through the incorporation of
intelligent systems. If these envisioned levels of autonomy could be achieved,
significant aerospace business and research opportunities will be enabled. As
example, components of the Intelligent Vehicle can include: 
Intelligent Mission Manager  Intelligent Vehicle Manager
 Intelligent Health Manager  Intelligent Flight Control
System  Intelligent Propulsion System At NASA Dryden and other
centers, there is need for quantitative performance measure of adaptive neural
networks based control system for aeronautics and aerospace applications.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This research
has significant importance for the use of adaptive NN in safety critical
application in aerospace industry, medical fields, power industry and other
industries where full knowledge is unable to predict system failures, failure
scenarios and the magnitude or criticality of the failure. This research
provides the foundation, that when fully understood, the commercial application
of adaptive NN will be a more robust application technology for the future. We
envisage further application in the aviation control towers of major airports,
process industry (chemicals, food, etc.).
TECHNOLOGY TAXONOMY MAPPING
Intelligence
Operations Concepts and
Requirements
Simulation Modeling Environment
Testing Facilities
Testing
Requirements and Architectures
Airport Infrastructure and Safety
Guidance,
Navigation, and Control
Pilot Support Systems
| PROPOSAL NUMBER: | 06-I X2.04-9002 |
| SUBTOPIC TITLE: | Low Temperature, Radiation Hardened Avionics |
| PROPOSAL TITLE: | Magnetic Logic Circuits for Extreme Environments |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
NVE CORPORATION
11409 Valley View
Road
Eden Prairie, MN 55344-3617
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Catherine Nordman
cathyn@nve.com
11409 Valley View Road
Eden Prairie, MN
55344-3617
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The program aims to
demonstrate a new genre of all-magnetic logic circuits which are
radiation-tolerant and capable of reliable operation in extreme environmental
conditions including low temperatures and wide temperature swings. The circuits
are based on tunneling magnetoresistive technology, and are expected to have a
greater single-event latchup immunity than semiconductor-based CMOS logic.
Recent breakthroughs in magnetic tunnel junction technology have resulted in
magnetoresistive responses in excess of 200%. With these developments adequate
current gain may now be realized to implement practical multi-stage logic
circuits. This work will seek to prove novel gate designs and explore the
magnetic thin-film tunneling structures necessary to realize them.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
New
class of logic circuits useful for all onboard systems for space and planet
exploration. Robust electronics (rad-hard, low-temperature tolerant) for space
environments.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Medical
instrumentation—electronics which withstand sterilization by heat or radiation.
Nuclear power industry—electronics for non-destructive evaluation of containment
vessels. Oil industry—temperature-tolerant electronics for exploration
technology.
TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data
Management
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid
State Device Materials
| PROPOSAL NUMBER: | 06-I X2.04-9336 |
| SUBTOPIC TITLE: | Low Temperature, Radiation Hardened Avionics |
| PROPOSAL TITLE: | Electronic Modeling and Design for Extreme Temperatures |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
CoolCAD Electronics
7101 Poplar
Avenue
Takoma Park, MD 20912-4671
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
James McGarrity
jmcgarrityarl@yahoo.com
1334 Patuxent Dr.
Ashton, MD
20861-9759
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop
electronics for operation at temperatures that range from
-230<SUP>o</SUP>C to +130<SUP>o</SUP>C. This new
technology will minimize the requirements for external heat sources that are
currently necessary for operation of low-temperature electronics. Such
technology would significantly improve reliability, performance, lifetime of
electronics that are used for space applications, including satellites and space
travel. This will be achieved through the development of unique circuits that
are derived from novel physics based device and circuit modeling techniques and
verified by experiment. Statistical methods will be employed to connect the
resistive heating caused by individual devices to heating of the entire
integrated circuit. Special algorithms will be further developed which allow for
determination of operating conditions where the intrinsic operation of the
circuit will allow for sufficient heat generation to eliminate carrier
freeze-out and efficient operation of integrated circuits in environments
ranging from -230<SUP>o</SUP>C to +130<SUP>o</SUP>C. For
situations where intrinsic circuit resistive heating at cryogenic temperatures
is insufficient to overcome carrier freeze out, we will design on-chip
micro-heaters to provide direct heating to chips at the submicron device level.
Thermal modeling of packaging will also be performed. With the intrinsic
temperature control established, we will design specific single electron latchup
immune circuits for application extreme environments.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
We
propose to develop extreme temperature electronics which are especially
applicable for space missions. We propose to develop physics-based transistor
device models valid at temperatures ranging from -230<SUP>o</SUP>C
to +130<SUP>o</SUP>C. We propose to incorporate these device
modeling results into Computer Aided Design (CAD) tools for predicting the
electrical performance, reliability, and life cycle for low-temperature
electronic systems and components. We also propose to develop low-temperature
(-230<SUP>o</SUP>C) circuit design methodologies facilitating novel
layout designs for integrated mixed-signal and analog circuits. We plan to
design radiation-tolerant and SEL immune, low power, mixed-signal circuits
including analog-to-digital converters and band-gap references. We will
investigate high-density packaging able to survive large numbers of thermal
cycles (hundreds) and tolerant of the extreme temperatures of the Moon and Mars.
We plan to design radiation-tolerant, SEL immune, wide temperature
(-180<SUP>o</SUP>C to +130<SUP>o</SUP>C), and ultra-low
temperature (-230<SUP>o</SUP>C) RF electronics for short range and
long-range communication systems.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The
physics-based device models can be used to predict transistor heating at any
temperature. This can be used in conjunction with our chip heating model to
determine the thermal profiles of integrated circuits for any given ambient
conditions. These calculations can then be used to offer new device and chip
layout paradigms that are optimized for specialized operation. More
specifically, understanding of cryogenic device and chip operation can result in
reliable and efficient low temperature electronics. Furthermore, since a major
objective of our work is to develop methodologies for efficient thermal
management of electronics, the proposed work has broad application in
high-density electronics, which continues to operate at higher and higher
temperatures, i.e. Pentium processors. Furthermore, the need to operate
electronics in extreme environments such as vehicle engines, and power systems,
will continue to expand. The technology developed in the proposal will aid in
design of electronics in such environments.
TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Control
Instrumentation
Simulation Modeling Environment
Testing Requirements and
Architectures
Spaceport Infrastructure and Safety
Telemetry, Tracking and
Control
Cooling
Thermal Insulating Materials
Guidance, Navigation, and
Control
On-Board Computing and Data Management
Pilot Support
Systems
Instrumentation
Portable Data Acquisition or Analysis
Tools
Sensor Webs/Distributed Sensors
Portable Life
Support
Radiation-Hard/Resistant Electronics
Earth-Supplied Resource
Utilization
Semi-Conductors/Solid State Device Materials
| PROPOSAL NUMBER: | 06-I X2.04-9709 |
| SUBTOPIC TITLE: | Low Temperature, Radiation Hardened Avionics |
| PROPOSAL TITLE: | Improved Models and Tools for Prediction of Radiation Effects on Space Electronics in Wide Temperature Range |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
CFD Research Corporation
215 Wynn Dr., 5th
Floor
Huntsville, AL 35805-1944
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Marek Turowski
sxh@cfdrc.com
215 Wynn Dr., 5th Floor
Huntsville, AL 35805-1944
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
All NASA exploration systems
operate in the extreme environments of space (Moon, Mars, etc.) and require
reliable electronics capable of handling a wide temperature range (-180ºC to
+130ºC) and high radiation levels. To design low-temperature radiation-hardened
(rad-hard) electronics and predict circuit and system characteristics, such as
error rates, modeling tools are required at multiple levels. To determine the
electrical responses of transistors and circuits to radiation events,
physics-based Technology Computer Aided Design (TCAD) and mixed-level tools are
required. This project will provide models and tools that will improve
capabilities for prediction of technology-dependent responses to radiation in
wide temperature range, which will lead to better design of rad-hard
electronics, better anticipation of design margins, and reduction of testing
cost and time. Future NASA missions will use nanometer-scale electronic
technologies which call for a shift in how radiation effects in such devices and
circuits are viewed. Nano-scale electronic device responses are strongly related
to the microstructure of the radiation event. This requires a more detailed
physics-based modeling approach, which will provide information for engineering
models used in device and integrated circuit (IC) design. Hence, the proposed
innovation: detailed high-energy-physics-based simulations of radiation events
(using Geant4-based software, from Vanderbilt University) efficiently integrated
with advanced device/circuit response computations by CFDRC NanoTCAD
three-dimensional (3D) mixed-level simulator. This will also enable a big number
of statistically meaningful runs on a massively parallel supercomputing cluster.
The extreme low temperature physics models combined with radiation effects
simulations will be obtained by leveraging another CFDRC project for Extreme
Environment Electronics, serving the NASA RHESE Program (led by NASA-MSFC).
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Prediction of electrical performance and radiation hardness of
electronic components in extreme environments (wide temperatures, high
radiation) are crucial to design reliable electronics for all NASA Exploration
Missions (Moon, Mars, etc.), for both crewed and robotic systems. Since
electronic parts are getting smaller, the radiation/temperature effects are more
severe – the life time and reliability become essential – the capability to
predict them increases confidence and reduces risk. The new tools will be
immediately applicable to the NASA Radiation Hardened Electronics for Space
Exploration (RHESE) Program, and other mission programs. The new models and
design tools will help NASA to: 1) assess and select new electronics
technologies, materials, and devices for very low temperature operation in
radiation environments; 2) investigate, generate, test, and validate new
fast/compact engineering models ("toy models") used in designing larger circuits
and systems; 3) design low-temperature rad-hard electronics with better
understanding and control of design margins, and evaluate redundancy scenarios;
4) predict circuit and system level characteristics, such as error rates; 5)
better evaluate the wide-temperature performance and radiation response at an
early design stage; 6) set requirements for hardening and testing; 7) reduce the
amount of testing cost and time.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential other
users include all space electronics suppliers, in particular for DoD space
communication, surveillance, and imaging systems, as well as commercial
satellites. Since modern electronic technologies and parts are getting smaller
all the time, the radiation and extreme temperature effects become more severe,
the life time and reliability become essential, and the capability to predict
them increases confidence and reduces risk. The new computer aided design (CAD)
tools can also be applied for cryogenic electronics for high-sensitivity,
low-noise analog and mixed-signal applications, such as metrology, infrared (IR)
imagers, sensors (radiation, optical, X-ray), radiometrology, precision
instruments, radio and optical astronomy, infrared and photon detectors, and
other high-end equipment. For all such devices and systems, predictive and
accurate modeling and design tools reduce the amount of required
radiation/temperature testing, thus decreasing their cost, and time to market or
field application.
TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling
Environment
Radiation-Hard/Resistant Electronics
| PROPOSAL NUMBER: | 06-I X3.01-8268 |
| SUBTOPIC TITLE: | Spacecraft Cabin Atmospheric Management and Habitation Systems |
| PROPOSAL TITLE: | CNT-Based Smart Electrostatic Filters for Capturing Nanoparticulate Lunar Regolith |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Agave BioSystems Inc
PO Box
80010
Austin, TX 78708-0010
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Joel Tabb
jtabb@agavebio.com
401 E State Street
Ithaca, NY 14850-0000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The abrasive, reactive, and
ubiquitous nature of lunar regolith created significant and serious problems
during the Apollo moon missions. In this Phase I, Agave BioSystems, in
collaboration with Dr. Randy Vander Wal of the Universities Space Research
Association, propose to develop next generation smart filters using novel carbon
nanotube (CNT)-based structures in electrostatic devices. Since CNTs have
extremely high surface area, can function without the mass transfer limitations
of traditional filtrations systems, and they can be charged to emit very high
charge densities, they constitute an ideal material for integration into
spacecraft air handling systems as electrostatic filtration components. The
overall goal of this program is to build upon the unique structural and
electronic nature of carbon nanotubes to create novel smart filters. By
synthesizing the CNTs in situ on solid mesh supports and integrating them into a
novel electrostatic particle collection unit, we aim to create novel filtration
media capable of removing airborne lunar regolith from spacecraft airlock and
cabin atmospheres.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
During
the Apollo moon missions, lunar regolith created significant problems. Regolith
stirred up by astronauts on the lunar surface covered almost every surface,
leading to: the clogging of equipment; abrasion and degradation spacesuit fabric
and materials; the blocking of astronaut vision; degradation and failure of
vacuum seals; and the inhalation of regolith by Apollo astronauts. If NASA is to
meet the goals put forth by President Bush 2004 to return humans to the moon by
2020, then a variety of technologies will be needed to handle the problems
associated with lunar regolith. The CNT-based electrostatic smart filters
described in this proposal can integrate with lunar module and spacecraft
environmental air handling systems to capture, trap and airborne regolith
particles from airlocks and cabin atmospheres. These electrostatic smart filters
will also have applications in spacecraft to trap and inactive airborne
microorganisms present in cabin environments.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Airborne
particulates present a major environmental problem today. Epidemiological
studies have shown that a variety of respiratory and cardiovascular diseases are
associated with increased exposure to airborne particulates. Major sources of
particulate material include cars, trucks, construction equipment, coal-fired
power plants, wood burning, vegetation, and livestock. Occupational exposure to
airborne particulates is an especially serious concern, especially in mining,
manufacturing and agricultural professions. The development of highly effective,
energy efficient methods to remove particulate contamination from occupational
environments could significantly reduce work-related illness in these
industries. Applications for carbon nanotube-based electrostatic filters
described in this proposal include indoor filtration systems, personal
protective equipment for workers exposed to occupationally high levels of
ultra-fine dust, and equipment for military personnel, firefighters, emergency
medical professionals, and other first responders.
TECHNOLOGY TAXONOMY MAPPING
Airlocks/Environmental
Interfaces
Multifunctional/Smart Materials
| PROPOSAL NUMBER: | 06-I X3.01-8461 |
| SUBTOPIC TITLE: | Spacecraft Cabin Atmospheric Management and Habitation Systems |
| PROPOSAL TITLE: | Nanostructured Catalytic Reactors for Air Purification |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Synkera Technologies Inc.
2021 Miller
Drive, Suite B
Longmont, CO 80501-6787
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Stephen Williams
swilliams@synkera.com
2021 Miller Drive, Suite B
Longmont, CO
80501-6787
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR Phase I project
proposes the development of lightweight compact nanostructured catalytic
reactors for air purification from toxic gaseous organic pollutants, particulate
matter, and microorganisms. Volatile organic compounds will be catalytically
oxidized when the contaminated air stream is passed through high-density arrays
of uniform ultra-high aspect ratio, high surface area, cylindrical nanoreactors.
Such unique architecture provides improved mass and heat transfer and ensures
conversion of volatile organics into non-toxic products with unmatched
efficiency. Room temperature oxidation of formaldehyde at low ppm level has
already been confirmed. In addition, particulate matter, bacteria and fungi will
be filtered out from the air stream at the reactor surface (nanopore diameter of
the proposed reactors will not exceed 300 nm). The proposed low-mass, low-volume
and low-power-consumption reactors are intended to replace and extend
functionality of conventional packed-bed catalytic oxidizers used currently for
removal of trace organic contaminants from spaceship atmospheres. The Phase I
work will focus on fabricating the reactor prototypes and evaluating of their
performance in catalytic oxidation of selected volatile organic compounds.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Removal
of trace organic and some other contaminants (e.g., carbon monoxide, ammonia,
hydrazine, etc.), particulate matter, and microorganisms from spacecraft and
spacesuits atmospheres.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Proposed
catalytic filters could be used in wide range of non-NASA applications, from gas
masks and air respirators for individual protection to small- and medium-scale
collective protection systems. Users of this technology will include facilities
utilizing hazardous chemicals, military personnel, counter-terrorism and
security forces, first responders, emergency medical personnel, and the
personnel involved in chemical weapons demilitarization and chemical site
remediation programs.
TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and
Conditioning
| PROPOSAL NUMBER: | 06-I X3.01-9427 |
| SUBTOPIC TITLE: | Spacecraft Cabin Atmospheric Management and Habitation Systems |
| PROPOSAL TITLE: | Electrospray Collection of Airborne Contaminants |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
CONNECTICUT ANALYTICAL CORPORATION
696
Amity Road
Bethany, CT 06524-3006
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Joseph Bango
jbango@ctanalytical.com
696 Amity Road
Bethany, CT 06524-3006
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In stark contrast to current
stagnation-based methods for capturing airborne particulates and biological
aerosols, our demonstrated, cost-effective electrospray technology employs an
entirely different approach based on the remarkable effectiveness of small,
highly charged liquid droplets formed from an electrospray source to "getter"
both particles and polar molecules dispersed in a gas. Less capable and
expensive collection system technologies are generally based on stagnation of
high velocity ambient airflow on a collecting surface. The momentum of particles
and heavy molecules precludes their following gas streamlines during this
stagnation. Instead, they concentrate and are trapped on the detector's surface
if the surface is "sticky," or concentrated in the surface boundary layer, which
can be separated from the mainstream flow and collected. Typically, current
separation methodology collects about 50 percent of the particles between 1.0
and 10 microns in diameter from a flow of 500 L/min with a power consumption of
up to 500 watts; i.e., about 1 watt of power is required for a small fan to
compress 1 liter of air per minute to produce the high velocity airflow
necessary for effective trapping of small bio-particles and heavy molecules.
However, our electrospray technology consumes negligible power and achieves
virtually 100 percent particle collection. In fact, we have demonstrated that
the power efficiency of electrospray gettering for a single electrospray emitter
to collect 100 percent of the particles, without a fan, at 10,000 times greater
than the power efficiency of state of the art systems.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Spacecraft and spacesuit environmental particulate and hazardous
chemical and biological species mitigation will be of paramount concern on
future moon missions and possible Mars exploration. The electrospray gettering
technology can be used to continuously remove particulate and chemical species
listed in NASA's SMAC list, offering all the advantages of conventional
electrostatic filtration methods but devoid of any ozone production.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Electrospray
gettering may be applied to Building HVAC "Collect-To-Protect" applications for
counter-terror protection, home HVAC use, automotive ventilation filtration
applications, airplane air filtration, and submarine air filtration to name just
a few commerical uses.
TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and
Safety
Particle and Fields
Biomedical and Life Support
Biomolecular
Sensors
Sterilization/Pathogen and Microbial
Control
Biochemical
Portable Life Support
Suits
| PROPOSAL NUMBER: | 06-I X3.01-9555 |
| SUBTOPIC TITLE: | Spacecraft Cabin Atmospheric Management and Habitation Systems |
| PROPOSAL TITLE: | Plasma Air Decontamination System (PADS) |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Orbital Technologies Corporation
1212
Fourier Drive
Madison, WI 53717-1961
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Yonghui Ma
may@orbitec.com
1212 Fourier Drive
Madison, WI 53717-1961
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed Plasma Air
Decontamination System (PADS) is a trace contaminant control device based on
non-thermal atmospheric pressure plasma technology that operates at ambient
pressure and temperature and has the potential to replace the existing Trace
Contaminant Control System (TCCS) used on the International Space Station and
future exploration vehicles. Non-thermal atmospheric plasma has been proven
successful in the destruction of a variety of organic carbons found in space
craft environments. The prototype plasma reactor on which the PADS will be based
has also shown successful destruction of organic carbon with good power
efficiency. Incorporation of this technology would facilitate a decrease in size
or total elimination of the intensive re-supply of activated carbon for
adsorbent beds, and possible elimination of the high temperature catalytic
reactor. This would result in significant savings in launch mass and cost for
long duration missions and a reduction in power requirements with the
elimination of the catalytic reactor. This system also has great potential to be
scaled to a variety of applications, allowing realization of the benefits that
come with having systems common to multiple life support systems such as lower
mass logistics and spares.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The PADS
technology will likely produce a higher quality of trace contaminant control in
a space craft or habitat than is provided by the current technology, and will
eliminate many of the disadvantages including the significant re-supply mass of
the disposable adsorbent beds, and the risk of large adsorbent beds releasing
adsorbed pollutants. It also does not require a vacuum source as do regenerable
adsorbent solutions, giving significant advantages for use in planetary surface
base applications. The system is also suitable for use both on spacecraft and on
surface habitats where a ready source of vacuum does not exist. The ability to
scale the system allows it to be reduced in size for use in a small volume such
as the Lunar Surface Access Module (LSAM), Lunar Outpost (LO), or Crew
Exploration Vehicle (CEV). Multiple applications will allow for commonality of
components and reduced crew training for maintenance and operation.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology
has broad possibilities for air purification in commercial systems. Portable,
plasma-based, air purifiers are a relatively new entrant to the home health
market. This opens the possibility for ORBITEC to license the advanced plasma
technology created from this SBIR application to major manufacturers. Targeted
markets such as office buildings, airplanes, buses, and trains, where large
numbers of people are grouped together could benefit from a compact system that
would both decompose pollutants and neutralize biological contamination
introduced by others. This system would be readily integrated into existing
ventilation infrastructure in these applications. Larger scale applications may
include accommodation of large air flows from industrial processes where
quantities of VOCs or other pollutants are required to be removed or altered
prior to release into the atmosphere. This same larger system also has
applications in homeland security, protecting military personnel from certain
chemical attacks, or remediation of polluted ecosystems.
TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and
Conditioning
Biomedical and Life Support
Sterilization/Pathogen and
Microbial Control
Ceramics
| PROPOSAL NUMBER: | 06-I X3.02-8898 |
| SUBTOPIC TITLE: | Water Processing and Waste Management |
| PROPOSAL TITLE: | High Recovery, Low Fouling Reverse Osmosis Membrane Elements for Space Wastewater Reclamation |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Santa Fe Science and Technology, Inc.
3216
Richards Lane
Santa Fe, NM 87507-2940
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Ian Norris
norris@sfst.net
3216 Richards Lane
Santa Fe, NM 87507-2940
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With the expected extension of
duration of the space missions outlined in NASA's Vision of Space Exploration,
such as a manned mission to Mars or the establishment of a lunar base, the need
to produce potable water from onboard wastewater streams in a closed-loop system
becomes critical for life support and health of crew members. Reverse osmosis
(RO) is a compact process that has proven its ability to remove inorganic and
organic contaminants from space mission wastewater. The objective of this Phase
I study is to ascertain whether composite hollow fiber membrane elements are a
more efficient alternative to the current generation of spiral wound membrane
elements for the reclamation of space mission wastewater. In particular, the use
of low-energy composite hollow fiber membrane elements being developed at SFST
for treating multi-component (both inorganic and organic contaminants)
wastewater streams found aboard spacecraft will be investigated. The higher
membrane surface area of these composite hollow fiber membrane elements enables
the RO membrane element to have 30% higher water productivity at substantially
higher single-pass recoveries (60-75% vs 10-20% for spiral wound elements).
Furthermore, we will also investigate possible solutions to minimize fouling of
these hollow fiber membranes by increasing the hydrophilicity of the membrane
surface using a variety of surface modification techniques. Such hollow fiber
membranes are expected to show better resistance to fouling by hydrophobic
compounds, and thus these membranes will be less likely to be clogged by
potential foulants. These improvements to the RO membrane element have the
potential to decrease the mass, size and power requirements of the RO subsystem,
and also decrease the size of the pre-treatment unit.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
technology is specifically targeted towards the wastewater treatment systems on
board spacecraft to produce potable water on long duration missions, such as the
establishment of bases on the lunar surface or human planetary exploration.
Reverse osmosis technology is well suited for wastewater treatment in space
because it has the advantages of high rejection of contaminants, durability for
removing inorganic contaminants with high water recoveries, a compact
configuration and minimal re-supply of consumables for continuous operation when
to compared to other physical-chemical treatment processes. The current design
of the RO subsystem in NASA's Integrated Water Recovery System employs spiral
wound membrane elements. Composite hollow fiber membrane elements have many
advantages over spiral wound membrane elements for reclamation of space mission
wastewater applications (i.e. higher module productivity/lower feed pressure,
higher recovery and reduced mass). These advantages should make the use of
composite hollow fiber membrane elements a viable alternative to spiral wound
membrane elements being considered for the Integrated Water Recovery System.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Reverse osmosis
membranes consist of a dense surface layer (50 – 500 nm) that is highly
permeable to water, but highly impermeable to dissolved salts, organic
molecules, microorganisms, and colloids. Consequently, reverse osmosis membrane
elements have been successfully used in municipal water treatment (desalination
of brackish water and seawater desalination), industrial water treatment (power
generation/boiler feed water, food & beverages, wastewater treatment and
reclamation), and producing ultra-pure water for microelectronics and
semiconductor manufacturing. End-users of reverse osmosis membranes continue to
look for products that perform at lower pressures and have improved fouling
resistance. If this project is successful, these composite hollow fiber
membranes offer significant performance improvements over spiral wound membrane
elements in terms of being able to operate at lower pressures or by operating
with lower numbers of membrane elements with the additional benefit of reduced
fouling.
TECHNOLOGY TAXONOMY MAPPING
Waste Processing and
Reclamation
| PROPOSAL NUMBER: | 06-I X3.02-9557 |
| SUBTOPIC TITLE: | Water Processing and Waste Management |
| PROPOSAL TITLE: | Enhanced Brine Dewatering System |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Orbital Technologies Corporation
1212
Fourier Drive
Madison, WI 53717-1961
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
William Butrymowicz
butrymowiczb@orbitec.com
1212 Fourier Drive
Madison, WI
53717-1961
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of the Enhanced
Brine Dewatering System (EBDS) is to provide an easily scalable means of
completely recovering usable water from byproducts created by reverse osmosis
water purification systems without the use of consumable wicks. Extended
duration Lunar and Mars missions will require the conservation and recovery of
water to allow for autonomous closed environments that in turn can dramatically
reduce launch mass and reduce stowage volumes. The EBDS will build on previous
developments in condensing heat exchangers to establish reliable, passive, and
energy-efficient methods for recovering water by focusing on the phase
separation methods employed at the brine evaporator. The EBDS uses evaporation
surfaces treated with antifouling agents to eliminate biological growth and
hydrophilic coatings to increase efficiency. These surface treatments are also
employed at the condensing heat exchanger. In addition to limiting bio-fouling
the brine evaporation system is designed to completely and autonomously recover
usable water and isolate waste salts. Crew interaction is limited to
periodically removing the bio-isolated waste byproducts from the system.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The EBDS
enables water reclamation from waste water brines without the use of consumable
wicks. EBDS can interface with the Advanced Water Recovery Systems (AWRS) of the
Advanced Life Support (ALS) project or similar systems required for all
long-duration human spaceflight systems and extraterrestrial colonization to
process waste water created by reverse osmosis treatments and provide water
suitable for post-treatment and human consumption. The EBDS can be used to
recover water from laundry washing and drying applications. By using EBDS,
launch mass and volume can be greatly reduced by limiting the amount of water
needed to support the mission by reducing the amount of water lost to waste. In
addition to saving the volume and mass associated with carrying extra water,
crew time and stowage are reduced by greatly increasing the time between service
operations.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
EBDS provides a
reliable, scalable, energy efficient, and low maintenance method of recovering
usable water from brines. Primary use of the EBDS technology is in microgravity
due to the gravity independent nature of the phase separation provided by the
brine evaporator and condenser, thus commercial space travel will benefit.
Immediate terrestrial applications of this system could be as a self-contained
package for concentration and stabilization of non-volatile toxic or high-value
wastes (e.g., dyes, heavy metal salts, or lumber-treatment solutions) from
environmental cleanup sites or small scale manufacturing processes. The system
is especially suitable for mercury salt remediation because the closed air loop
will contain any volatile organomercury compounds present in the water feed
solution. The EBDS could also be used for recovery of solvents or fuels from
spills or leak sites in areas of saline groundwater.
TECHNOLOGY TAXONOMY MAPPING
Waste Processing and
Reclamation
| PROPOSAL NUMBER: | 06-I X3.03-9131 |
| SUBTOPIC TITLE: | Crewed Spacecraft Environmental Monitoring and Control and Fire Protection Systems |
| PROPOSAL TITLE: | Simple, Micro-Miniature Total Organic Carbon Analyzer |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
ENVIRONMENTAL AND LIFE SUPPORT TECH.
6600
E. Lookout Drive
Parker, CO 80138-0770
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Clifford Jolly
cdjels@aol.com
6600 E. Lookout Drive
Parker, CO 80138-0770
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of a simple method
for on-orbit or advanced mission Total Organic Carbon (TOC) monitoring has been
a goal for many years. This proposal seeks to develop a method that is, above
all else, simple, inexpensive, and maintenance-free. Previous programs to
develop flight hardware, including CHeCS, PCWQM, and previous SBIR-funded
efforts, failed to produce workable hardware and were relatively complex and
expensive. Since the product water in a closed life support system will not
likely vary in characteristics as much as terrestrial water and wastewater
samples for which commercial TOC instrumentation is designed to analyze,
adaptation of the complex commercial methods for spacecraft application should
not be required. We therefore propose to fabricate a simple, low-volume,
flow-through device that is based on a micro-reactor to convert organics to
organic acids, followed by liquid-phase detection of the acids. Innovative
detection methods that do not require frequent calibration are proposed. Phase I
will consist of prototype fabrication followed by feasibility tests to
quantitatively assess reactor performance and detector sensitivity and
precision. Phase II will result in high-fidelity instrumentation that is
suitable for flight qualifiication.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This
device will have applications in ISS, Lunar bases, and Mars bases, and will be
developed based on the assumption that the system(s) in which it is employed
will be of Crit 1 or Crit 2 hardware fidelity.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This device
will have immediate application in the >$100M commercial market for TOC
instrumentation. The PI of this program has twenty years experience in TOC
instrumentation, and has the capability to successfully implement the technology
in industry.
TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Waste
Processing and Reclamation
| PROPOSAL NUMBER: | 06-I X4.01-8138 |
| SUBTOPIC TITLE: | Lunar Regolith Excavation and Material Handling |
| PROPOSAL TITLE: | MPED: An ISRU Bucket Ladder Excavator Demonstrator System |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
sysRAND Corporation
15306 Foxglove
Ct.
Parker, CO 80134-9589
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Bradley Blair
bblair@sysrand.com
15306 Foxglove Ct.
Parker, CO 80134-9589
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is a
planetary surface tool called the Multi Purpose Excavation Demonstrator (MPED),
which is intended to both extract Lunar Soil to feed an in-situ resource
utilization (ISRU) processing plant, and to perform lunar civil engineering
applications. The proposed MPED prototype is an excavation tool known as a
'bucket ladder,' a device with a long heritage of industrial use that is
intrinsically abrasion and dust-resistant. The device will be a prototype bucket
ladder excavation tool with a pivot arm, and will have a target mass of 20kg and
a target production rate of 500kg/hr. It is intended to be integrated into a
roughly 80kg mobile platform for a total projected mobile system mass of 100kg.
The system will be designed for minimum power consumption for the lunar case,
with a target power consumption of less than 200 watts for the terrestrial
demonstrator (note: lunar power consumption is expected to be lower due to
gravitational differences). Productivity goals include a maximum berm height of
3 meters (based upon multiple passes), a single-pass excavation depth of 30 cm
(with a width of between 10 and 25 cm), and a multi-pass road width of 4 meters.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MPED is
offered in support of NASA's ISRU efforts, with the expectation that lunar
resources will be utilized as specified in the NASA Exploration Vision.
Continuous excavation is key to maximizing ISRU productivity because of its
ability to acquire a steady stream of ore. The system will also be capable of
performing civil engineering operations that could be required for the setup and
preparation for a lunar outpost or base, as well as other activities such as
building of infrastructure, or site preparation for telescope deployment. A
future robotic system based on MPED could also use its trenching capability to
assist human geologic explorers, and is expected to become a candidate payload
as a component of future ISRU missions. It could also qualify as an secondary
payload for a future robotic surface mission under the LPRP (Lunar Precursor and
Robotic Program).
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The early
development and demonstration of a key lunar ISRU system element (the excavator)
is expected to have a strong impact on risk reduction for future commercial
lunar mining and ISRU product development. Pending a successful outcome of this
project, the interest of commercial investors is anticipated. Through previous
work we have identified companies that are positioned to exploit the
commercialization and development effort, and cultivated contacts with key
personnel. Numerous terrestrial commercial opportunities within the mining and
civil construction industries exist, pending technical advances in
abrasion-resistance and dust mitigation, and fall within the larger scope of the
proposed effort (i.e., Phase II). Certain methodology embodied in our approaches
to applications are also expected to enhance modular robotics for assembly and
repair in field conditions, leading to commercial market applications.
TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated
Robotic Concepts and
Systems
Mobility
Manipulation
Teleoperation
Spaceport Infrastructure
and Safety
Thermal Insulating Materials
Architectures and
Networks
Autonomous Control and Monitoring
Production
Human-Computer
Interfaces
Tools
General Public Outreach
K-12 Outreach
Mission
Training
Radiation-Hard/Resistant Electronics
In-situ Resource
Utilization
Microgravity
Radiation Shielding Materials
Power Management
and Distribution
| PROPOSAL NUMBER: | 06-I X4.01-8247 |
| SUBTOPIC TITLE: | Lunar Regolith Excavation and Material Handling |
| PROPOSAL TITLE: | Non-Lubricated Diamond-coated Bearings reinforced by carbon fibers to work in Lunar Dust |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
DIAMOND MATERIALS INC.
120 Centennial
Ave.
Piscataway, NJ 08854-3908
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Oleg Voronov
ovoronov@aol.com
120 Centennial Ave.
Piscataway, NJ 08854-3908
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop low cost
diamond composite bearings utilizing our new high pressure technology for carbon
fiber reinforced 3-D C/C composites and mixtures of pitch, fullerenes and
nanotubes. Functionally graded bearings will be engineered to function without
lubrication and to operate in Lunar dust. Tests have shown that these new
materials are thermally and chemically stable, have a very high wear resistance
on the diamond coated surface and can work in sand and regolith like
unlubricated sliding fits. Such bearings are also extremely lightweight. Our
variety of diamond coated composite would be easily scalable and cost effective
to fabricate. In Phase I, we will focus on designing and prototyping precision
unlubricated bearings. For Phase II and III, we will work in collaboration with
leading companies that produce ceramic bearings.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
applications: Potential applications of this material are bearings for Lunar
regolith excavators and other planetary missions.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non NASA
applications: The bearings that we plan to develop could be utilized for high
speed applications at low temperature and high temperature ranges. They are
corrosion and wear resistant and can work in aircraft engines, rock drilling and
other abrasive environments.
TECHNOLOGY TAXONOMY MAPPING
In-situ Resource
Utilization
Ceramics
Composites
Tribology
| PROPOSAL NUMBER: | 06-I X4.02-8511 |
| SUBTOPIC TITLE: | Oxygen Production from Lunar Regolith |
| PROPOSAL TITLE: | Modular Distributed Concentrator for Solar Furnace |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
DR Technologies, Inc.
7740 Kenamar
Court
San Diego, CA 92121-2425
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Theodore Stern
tstern@drtechnologies.com
7740 Kenamar Court
San Diego, CA
92121-2425
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This research proposes to
develop a lightweight approach to achieving the high concentrations of solar
energy needed for a solar furnace achieving temperatures of 1000-2000C.
Conventional solar-fired furnaces face significant challenges in fabricating,
deploying and pointing the large aperture, high concentration ratio reflectors
that power them. The Modular Distributed Concentrator (MDC) is a systems
solution comprising an array of identical, modestly sized solar concentrator
dishes with a network of optical or thermal transmission links that route the
high quality concentrated energy to a centralized receiver. The approach
provides lower mass because of the ability to optimize the scale of the
individual reflectors to achieve high concentration ratio without the heavy
structure needed to achieve and maintain optical alignment found in large
aperture optics. The minimum deployed height associated with an array of
concentrators allows for good packaging efficiency and minimum deployment
complexity, and since the dishes are one-piece and identical, tooling and
manufacturing costs are significantly reduced. The proposed program performs
system optimization trades and then proceeds to the preliminary design and
development of key components such as the optical light guide and thermal heat
pipe transmission links that carry the energy to the furnace, as well as the key
input and output interfaces. A proof-of-concept demonstration in Phase I will be
used to validate the performance model and guide the detailed design,
development and environmental testing of system components in Phase II.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In
addition to application to the needs for high temperature regolith processing
for oxygen, silicon and other materials on the lunar surface, NASA can benefit
from the application of this technology to manned spacecraft requirements. The
MDC provides an alternative to the large deployable solar concentrators which
were the main impediment preventing the realization of benefits from solar
dynamic converters with thermal energy storage for space station and other large
habitable space modules. The use of solar energy directly as light and heat also
provides a more efficient resource for climate control functions of space, lunar
and planetary habitats.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are a
significant number of applications that could be enabled by a modular
concentrator approach that allows transmission of the high-power, concentrated
solar energy. Medium- and high-temperature industrial processes could enjoy
significant monetary savings by replacing electrical energy with direct solar
firing, but most processes cannot be reasonably located at the focus of a solar
concentrator. A significant energy user that would benefit from the MDC is in
the fabrication of solar grade silicon from sand – a process that can take place
in desert areas where direct solar is abundant. Another potential significant
user of this technology is the environmental remediation industry which can
purify water by dissociating chlorofluorocarbons with concentrated sunlight
piped directly to the ground water table.
TECHNOLOGY TAXONOMY MAPPING
Solar
In-situ Resource
Utilization
Power Management and Distribution
Renewable
Energy
Thermodynamic Conversion
| PROPOSAL NUMBER: | 06-I X4.02-9046 |
| SUBTOPIC TITLE: | Oxygen Production from Lunar Regolith |
| PROPOSAL TITLE: | Multi-use Solar Thermal System for Oxygen Production from Lunar Regolith [7227-060] |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Physical Sciences, Inc.
20 New England
Business Center
Andover, MA 01810-1077
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Takashi Nakamura
nakamura@psicorp.com
20 New England Business Center
Andover,
MA 01810-1077
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Physical Sciences Inc. (PSI),
in collaboration with the Lockheed Martin Space Systems Company (LMSSC) and
Orbital Technologies Corporation (Orbitec), proposes to develop the multi-use
solar thermal system for oxygen production from lunar regolith. In this system
solar radiation is collected by the concentrator array which transfers the
concentrated solar radiation to the optical waveguide (OW) transmission line
made of low loss optical fibers. The OW transmission line directs the solar
radiation to the thermal receiver for thermochemical processing of in-situ
resources or for manufacturing of materials and components on the planetary
surface. Key features of the proposed system are: 1. Highly concentrated solar
radiation (10^3 ~ 10^4 suns) can be transmitted via the flexible OW transmission
line directly to the thermal receiver for thermochemical or manufacturing; 2.
Power scale-up of the system can be achieved by incremental increase of the
number of concentrator units; 3. The system can be autonomous, stationary or
mobile, and easily transported and deployed on the lunar surface; and 4. The
system can be applied to a variety of ISRU processes.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
specific application of the proposed solar power system is for production of
oxygen and other useful materials on the lunar surface. The solar thermal system
could be set in place prior to the initiation of various lunar projects such as
mining, processing or manned outposts. Therefore, the solar thermal system is
the key enabling technology for building up the infrastructure for the lunar
base. The solar thermal power system to be developed in this program can also be
used for electric power conversion using dynamic electric power generator, such
as Stirling converter.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Application of
the proposed solar power system to other space applications will be possible as
its technical maturity progresses. PSI is developing solar thermal rocket system
for satellite propulsion under Air Force SBIR funding. The solar thermal rocket
system will enable communication satellites to utilize solar power for station
keeping and orbit change. For terrestrial applications the proposed system will
be used for a small scale, transportable solar heat source for: detoxification
of contaminated soil; small power plant using compact heat engine; air
conditioning cycle; and industrial process heat.
TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization
| PROPOSAL NUMBER: | 06-I X4.02-9797 |
| SUBTOPIC TITLE: | Oxygen Production from Lunar Regolith |
| PROPOSAL TITLE: | Lunar Oxygen and Silicon Beneficiation Using Only Solar Power |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Packer Engineering
1950 N.
Washington
Naperville, IL 60563-1366
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Peter Schubert
pschubert@packereng.com
1950 N. Washington
Naperville, IL
60563-1366
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Element beneficiation from a
moving, ionized plasma can be accomplished through the principles of mass
spectroscopy. Two US patents were recently awarded to the PI on a means to
separate all isotopes of regolith in a single pass using either a continuous or
pulsed operation. This method of in-situ resource utilization has been studied
at a system level, and results published at a national space conference. Phase I
of the proposed work will extend the favorable results obtained so far towards a
system-level model of the process suitable for more accurate computation of
performance metrics. Mathematical models of the SiO2 molecule dissociation,
ionization, transport and separation will be derived and applied to the patented
apparatuses. Preliminary calculations on silicon extraction indicate the
potential for solar cell production at approximately $6/Watt, a 50 times
improvement over other proposed methods of space-based manufacture. We will
apply this novel method of beneficiation to a simultaneous extraction of oxygen
and silicon. Key questions to be answered include estimates of the physical
dimensions conducive to efficient extraction (Watts/kg, kg/sec), which will
drive system parameters of mirror size, solar power needs (for magnetrons and
chillers), shielding, thermal management and infrastructure. Milestones within
the six-month project will be: (1) vaporization, energy flow and system
architecture; (2) addition of self-shielding, double-ionization,
three-dimensional considerations and slag rates; (3) inlet design
considerations, multiple molecule separation, and velocity profiling; and (4)
composite separation rates and overall tranfer function characterization. Upon
completion of Phase I we will have detailed design equations needed to construct
a prototype oxygen extraction unit during Phase II.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Oxygen
molecules separated from a plasma will be condensed on a cold plate and
gravity-collected for use as a fuel oxidizer. Oxygen is also a component of a
breathable atmosphere, and as a raw material for other ISRU applications.
Silicon extraction is used for solar cell production using float-zone
crystallization and ion implantation to form photodiodes. Aluminum extraction
(also possible with these inventions, but not studied herein) provides for
conductors and Ohmic contacts to the silicon to form solar arrays capable of
supplying power. This power can be used to power additional beneficiation
apparatuses, or for baseline power to a lunar habitat or science station. A
machine delivered to the moon in advance of a manned mission can be readily
assembled and operated during lunar day. Waste slag from the separation process
can be deposition-formed into bricks of any convex shape. Waste heat from these
bricks can drive a Sterling cycle engine for mechanical power, and the bricks
can be assembled into shelters for equipment or habitats. This concept leverages
the capability to produce 100s of times the mass of extracted resources compared
to the delivered payload mass. Adaptations of the same invention, covered by
patents, allow use in microgravity environments, thereby extending applicability
to future missions to the moons of Mars or to target asteroids, where additional
beneficial elements (such as nitrogen and carbon) can be found.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The three
biggest problems facing mankind today are nuclear proliferation, global warming
and peak oil. If it can be made cost-effective, space solar power can ameliorate
all three. To be cost-effective, extra-terrestrial sources of silicon and
aluminum are needed for the solar cells. Transportation of workers and material
throughout cislunar space, a non-trivial contributor to overall costs, can be
greatly reduced with a source of extra-terrestrial oxygen. Therefore a system
capable of extracting all three of these vital elements from lunar regolith
represents a considerable economic benefit to any enterprise producing space
solar power. Therefore, these patents, and the work proposed herein, could
represent the foundation upon which mankind develops a sustainable, long-term
solution to the growing needs of an expanding civilization.
TECHNOLOGY TAXONOMY MAPPING
Erectable
In-situ Resource
Utilization
Semi-Conductors/Solid State Device Materials
| PROPOSAL NUMBER: | 06-I X4.03-8139 |
| SUBTOPIC TITLE: | Lunar Polar Resource Prospecting and Collection |
| PROPOSAL TITLE: | Pneumatic Excavation Mechanism for Lunar Resource Utilization |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W 34th
Street
New York, NY 10001-4236
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Kris Zacny
zacny@honeybeerobotics.com
NASA Research Park, Building 19, Room 1073,
Box 370
Moffet Field, CA 94035-1000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As part of the NASA goal of
"locating and characterizing lunar volatile resources", Honeybee Robotics
proposes to investigate two novel technologies that both are powered by a new
monopropellant, NOFB3, developed by Firestar Engineering. Honeybee will test key
concepts for a pneumatic drill, intended for use in the lunar cold traps, and
will also investigate a method for mining the top few centimeters of lunar
regolith with a gas system that has no moving parts. Analogous to the
high-powered drilling done on Earth, the proposed pneumatic drill will derive
its mechanical power from a chemical fuel (NOFB3), and it will use a fluid (in
this case, low temperature exhaust gases extracted from the power system) to
remove drill cuttings. A drill of this sort will have a number of advantages
over traditional electromechanical drill/auger systems, including reduced power
consumption, lower mass, less mechanical complexity, and better durability at
extreme temperatures. In Phase I, the team proposes to investigate the
production of mechanical power from the monopropellant via a small turbine, and,
separately, to study removal of cuttings with gas flow while drilling in a
laboratory vacuum chamber. The second part of the proposed research will be to
investigate a method for mining the top few centimeters of lunar regolith using
a method similar to "jet-lift dredging". This method will use a stream of gas,
also provided by the partial decomposition of NOFB3, to draw simulated lunar
regolith into a delivery pipe connected to a storage bin. The system has no
moving parts and is thus well suited for the abrasive lunar environment. The
proposed coupled propulsion/pneumatic system for excavation and prospecting will
enable robust, rapid, subsurface access into an in-situ medium, and particularly
into permanently shadowed regions on the moon without requiring solar
illumination, potentially large nuclear power systems, or potentially
complicated distributed power systems.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
drilling and mining technologies stemming from this research will directly meet
the Lunar Precursor and Robotic Program (LPRP) and human lunar exploration
mission objectives. To date, traditional methods of drilling and mining have
failed to reach high TRL levels. If this research is successful, the resulting
technologies will have the simplicity and robustness to operate under the
extreme lunar conditions, particularly in terms of exposure to the abrasive
lunar regolith and the large temperature extremes. The same drilling technology
could have applications on Mars and the mining system may also be suitable for
future use on asteroids. Given the large range of applications for gas
generators in both aerospace and commercial applications, Firestar Engineering,
LLC anticipates that this work will lead into focused product development after
Phase 2. One immediate and closely related application that will be investigated
for application is a pressurant system for upper stages and launch vehicles that
may operate from NOFB3 monopropellant.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The
turbine-powered pneumatic drill system could be useful for terrestrial drilling
in Polar Regions, where gasoline engines perform poorly at very cold
temperatures. The basic system for generating power via a small turbine could
also be adapted to other mechanical devices, such as pumps or winches. The
monopropellant pressurant system (see previous section) could also be used by
the commercial launch industry. In the distant future, on the order of several
decades, the gas flow mining method investigated in this project could evolve
into a commercial system for lunar or asteroid mining.
TECHNOLOGY TAXONOMY MAPPING
Chemical
Micro
Thrusters
Monopropellants
Integrated Robotic Concepts and
Systems
Operations Concepts and Requirements
Simulation Modeling
Environment
Testing Facilities
Testing Requirements and
Architectures
Cooling
Earth-Supplied Resource Utilization
In-situ
Resource Utilization
Combustion
Energy Storage
Thermodynamic
Conversion
Aircraft Engines
| PROPOSAL NUMBER: | 06-I X4.03-9564 |
| SUBTOPIC TITLE: | Lunar Polar Resource Prospecting and Collection |
| PROPOSAL TITLE: | Selective Photoinitiated Electrophoretic Separator |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Physical Optics Corporation
20600 Gramercy
Place, Bldg 100
Torrance, CA 90501-1821
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Kang-Bin Chua, Ph.D
sutama@poc.com
20600 Gramercy Place, Bldg 100
Torrance, CA
90501-1821
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To address NASA Johnson Space
Center needs for gas separation and collection technology for lunar in-situ
resource utilization, Physical Optics Corporation (POC) proposes to develop a
new Selective Photoinitiated Electrophoretic Separator (SPIES) System, based on
selective photoionization and electrophoresis. This approach incorporates a
novel system design for selective photoionization for electrophoresis of
selected gases, for electrophoretic processing, to meet the NASA requirement for
equipment with low launch mass to separate hydrogen, carbon dioxide, nitrogen,
helium, water, ammonia, and methane. The SPIES system launch weight and energy
consumption will be 33% of those of the current distilling/purification systems
because it eliminates the requirements for consumables and downstream
distillation equipment. While requiring minimal system maintenance, this system
will operate without consumables, and will be easily reconfigurable for
different ISRU scenarios. In Phase I POC will establish the feasibility of the
SPIES system by assembling a proof-of-concept prototype and demonstrating
separation of a simulated lunar volatile, reducing development risk in Phase II.
In Phase II POC plans to optimize the SPIES system design and assemble an
advanced system prototype that can perform multiple gas separation tasks,
enabling NASA to selectively remove and purify a range of gas streams in lunar
solar resource prospecting.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
POC
expects substantial NASA opportunities for the SPIES system for selective
removal/purification of a wide range of gas streams, including hydrogen, helium,
oxygen, ammonia, nitrogen, and water vapor. It will be particularly beneficial
in space, on the moon, Mars, and beyond because of its universality, and will
replace a large number of diverse individual modules for distillation of gases.
At the same time its only consumables are long-lasting excimer lamps (if solar
collectors are not used).
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial
applications of the SPIES system technology are even broader. For example, this
technology can address the need for energy-efficient production of industrial
gases such as production of oxygen at a cost that is significantly lower than
that of current energy-intensive processes. Another example is the direct
production of hydrogen for fuel cells.
TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization
| PROPOSAL NUMBER: | 06-I X5.01-8741 |
| SUBTOPIC TITLE: | Motors and Drive Systems for Cryogenic Environments |
| PROPOSAL TITLE: | Gear Bearing Transmission for the Lunar Environment |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W 34th
Street
New York, NY 10001-4236
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Jack Wilson
wilson@honeybeerobotics.com
460 W. 34th Street
New York, NY
10001-2320
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Honeybee Robotics proposes to
build upon technology we have previously developed with Goddard Space Flight
Center and redesign specifically for the lunar environment a "gear bearing"
transmission. We intend to bring this technology to a higher Technology
Readiness Level (TRL) for the number of applications imagined for future
missions to the lunar poles requiring motors and drive trains ranging from
mobility systems, in situ resource utilization (ISRU) machinery, and robotic
systems mechanisms. The advantages of this design lend themselves well to
spaceflight mechanisms in general and specifically to the extreme conditions at
the lunar poles. The high gear reductions possible within a single stage,
coupled with the already compact size make gear bearing transmissions ideal for
spaceflight hardware where size and weight are at a premium. The relative
simplicity, the elimination of traditional bearings in the transmission, and the
avoidance of sliding friction altogether have significant advantages in
cryogenic and hard vacuum environments where material and lubricant selection
are limited.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's
2006 Strategic Plan identifies as a key goal the establishment of a lunar return
program with the intention of facilitating later missions to Mars. Beginning
with ground testing of enabling technology on the moon by 2012 and culminating
with a long-term human outpost at one of the lunar poles , there will be a great
need for cryogenic motors and mechanisms for the lunar environment. By bringing
gear bearing transmission technology to a high TRL, Honeybee will be enabling a
wide range of essential systems, key to robotic precursor missions designed to
survey and characterize lunar landing sites and later for in-situ resource
utilization (ISRU) activities essential to a long-term human presence on the
moon. Honeybee hopes to build on this heritage and continue to play a vital role
in the development of spaceflight hardware for these future NASA missions.
Honeybee has in development robotic systems to be flown on every recent and
future planned mission to Mars, beginning with the very successful MER missions,
through Phoenix, and including the Mars Science Laboratory (MSL) mission. It is
our intension in designing and testing this technology for the extreme
environment of the lunar poles that these fundamental, robust components will
have transferable application to the demanding environment of Mars as well.
Honeybee plans to continue our successful relationship with NASA through the
further development of this technology.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
As with past
successful SBIR efforts, we will seek to patent the novel aspects of our designs
and pursue licensing the technology to other industries. We will utilize our
experience and contacts in the aerospace industry, as well as continue to
perform market research and identify companies in other industries that could
utilize this technology. We have identified one potential application of
advanced cryogenic actuators in laboratory testing equipment for a number of
industries.
TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and
Systems
Mobility
Manipulation
| PROPOSAL NUMBER: | 06-I X6.01-8619 |
| SUBTOPIC TITLE: | Radiation Shielding Materials and Structures |
| PROPOSAL TITLE: | Multifunctional Polymers Incorporating High-Z Neutron-Capture Nanoparticles |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
International Scientific Technologies, Inc.
P O Box 757
Dublin, VA 24084-0757
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Russell Churchill
intlsci@earthlink.net
P O Box 757
Dublin, VA 24084-0757
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has identified the need
for the development of lightweight structures technologies to support Lunar
Lander and Lunar Habitats programs and for the transfer of relevant technology
to Crew Exploration Vehicle and Crew Launch Vehicle programs. NASA further calls
for revolutionary advances in radiation shielding materials and structures
technologies to protect humans from the hazards of space radiation during NASA
missions. To address this need and in response to NASA Subtopic X6.01,
International Scientific Technologies, Inc. in conjunction with the College of
William and Mary, proposes the development of lightweight multifunctional
polymeric materials with nanoparticle metallic additives that will provide
radiation protection of humans engaged in long-duration space missions. The
Phase I program Technical Objectives include selection and functionalization of
metallic nanoparticles for incorporation into polymers, fabrication of
nanocomposite films of space-compatible polymers, and measurement of radiation
shielding effectiveness. The anticipated result of the Phase I and Phase II
programs is the fabrication of polymeric materials incorporating metallic
nanoparticles that will have multifunctional properties of radiation shielding
against galactic cosmic radiation and neutrons and electromagnetic radiation,
and structural integrity to permit use in flexible and rigid structures and
habitats during deep-space missions.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed multifunctional nanocomposites will find application in the Exploration
Systems mission in protecting astronauts and sensitive optical, electronic,
thermal and acoustic components from environmental hazards including radiation,
dust and thermal transients while, at the same time, providing lightweight
structural functions. It is expected that nanocomposite systems will provide a
high-performance-to-weight radiation shield that can be used within human
habitations, spacecraft and protective apparel. Other missions supported by NASA
could also make use of the nanocomposite materials in low earth orbit or in
other orbital paths traversing high radiation regions of space.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Lightweight
multifunctional radiation shielding will find application in the commercial
(e.g., hospitals and nuclear power plants) and defense (e.g., nuclear-powered
ships and surveillance satellites) sectors. The shields will provide protection
for homeland security first responders employed by law enforcement agencies,
fire departments and hospitals. It is also expected that the shielding can be
fabricated into temporary shelters used by defense personnel and considered for
use in the protection of individuals in case of a nuclear or radiological event.
The radiation shielding material will be suitable for fabrication into
protective clothing for healthcare professionals involved in X-ray and nuclear
medicine.
TECHNOLOGY TAXONOMY MAPPING
Erectable
Inflatable
Launch and
Flight Vehicle
Thermal Insulating
Materials
Suits
Composites
Radiation Shielding
Materials
Multifunctional/Smart Materials
| PROPOSAL NUMBER: | 06-I X6.02-8701 |
| SUBTOPIC TITLE: | Lightweight Pressurized Structures Including Inflatables |
| PROPOSAL TITLE: | Lightweight, Composite Cryogenic Tank Structures |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Microcosm, Inc.
401 Coral Circle
El
Segundo, CA 90245-4622
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Aaron Leichner
aleichner@smad.com
401 Coral Circle
El Segundo, CA 90245-4622
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Microcosm has developed and
qualified strong, all-composite LOX tanks for launch vehicles. Our new 42-inch
diameter tank design weighs 486 lbs and burst without leaking at 2,125 psi,
within 3.5% of the predicted burst pressure. This SBIR will analyze, design,
build, and test much lighter weight all composite cryogenic tanks and examine,
develop, and test alternative insulation techniques to minimize boil-off. This
SBIR will also examine the reuse of propellant tanks as crew and storage
habitats. During Phase I, we will design and fabricate 12 10-inch diameter and 2
25-inch diameter cryogenic tanks with a design burst pressure of approximately
850 psi. Eight of the 10-inch tanks and one 25-inch tank will be thermally
cycled and burst tested using liquid nitrogen to obtain statistical data. The
remaining 4 10-inch tanks will first be thermally cycled, then flushed out and
re-pressurized with gaseous helium to simulate reuse as a crew habitat. The
remaining 25-inch tank will be delivered to NASA for further testing. Phase II
will fabricate, build, and test larger tanks and tanks specifically intended to
meet the needs of future NASA programs, and alternative insulation approaches
will be evaluated to minimize boil-off.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
innovation proposed here is a new design and fabrication process for
all-composite cryogenic tanks that in experiments to date has improved the
performance per unit mass by a factor of 3 to 4. These tanks can be implemented
into the CEV and CLV programs, as well as lunar lander and habitat programs, for
the pressurized storage of a wide range of cryogenic propellants, including
liquid oxygen, liquid hydrogen, and liquid methane. The significance is that the
potential now exists to dramatically reduce the mass and cost of cryogenic tanks
for launch and space applications, and to reuse these tanks for crew habitats.
With this substantial weight reduction, any NASA programs utilizing propellant
tanks could experience a significant improvement in performance, allowing larger
payloads and more instrumentation to be launched.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Because tanks
typically represent the largest component of the mass of most launch vehicles,
the potential exists to dramatically increase launch and in-space performance at
little or no increase in cost. Specifically, the performance of the Sprite Small
Launch Vehicle increases from 809 lbs to LEO with the prior composite tanks to
1050 lbs to LEO with the new, light-weight composite tanks. And, many other
liquid stage launch vehicle programs could realize substantial weight and cost
savings by implementing these tanks into their propulsion systems. As such,
these launch vehicles could experience a considerable improvement in
payload-to-orbit performance, allowing larger payloads and more instrumentation
to be launched on each vehicle.
TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Launch and Flight
Vehicle
Reuseable
Thermal Insulating Materials
Structural Modeling and
Tools
Tankage
Fluid Storage and
Handling
Production
Composites
| PROPOSAL NUMBER: | 06-I X6.02-9365 |
| SUBTOPIC TITLE: | Lightweight Pressurized Structures Including Inflatables |
| PROPOSAL TITLE: | High-Strength and Optically Transparent Fiber-Reinforced Composites |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Mo-Sci Corp
P.O. Box 2
Rolla, MO
65401-8277
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Mariano Velez
mvelez@mo-sci.com
P.O. Box 2
Rolla, MO 65401-8277
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For many applications there
exists a need for mechanically strong composite materials of high optical
quality and transparency equivalent to window glass. One method of increasing
the mechanical strength of polymers is to reinforce them with high-strength
cylindrical glass fibers. In most cases, however, the introduction of glass
fibers into an optically transparent polymer destroys the transparency of the
polymer and an object at distances greater than a few feet cannot be clearly
seen through them. MO-SCI Corporation proposes to develop novel large
high-strength and optically transparent, flexible panels of glass fiber
reinforced polymer matrix composites, as light-weight structural components, by
layering a polymer matrix reinforced with glass ribbons (micron-size glass
fibers with rectangular cross section) and a tough compliant polyurethane film.
MO-SCI Corporation has produced research quantities of rigid epoxy-matrix
composites which use glass ribbons that are index matched to the polymer matrix
to be used as high-strength windows as described in U.S. patent 5,665,450 and
licensed to MO-SCI Corporation. The objective of this proposal is to use this
technology to produce nearly defect-free composites as demonstration samples for
marketing structurally strong and impact resistant composites that are optically
transparent.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The main
application of high-strength ribbon-reinforced flexible composites is as a
component of light-weight inflatable structures, as requested by the NASA SBIR
Subtopic. These flexible composites may be opaque if carbon-fibers, for instance
are used, or transparent, if glass ribbons are used. Transparent flexible
composites may have applications as deployable domes for the Mars environment
for plant growing. Rigid transparent composites may have applications as
high-strength windows. Rigid and opaque composites, reinforced with glass
ribbons may have applications as cryotanks, as the glass ribbons may offer a
much lower permeability than circular fibers.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential
applications of high-strength rigid transparent composites described in this
proposal include protective eyeglasses and face shields, high security display
cases, airplane windows and fighter jet cockpit canopies, transparent armor and
security shields, display and filter elements, blast-resistant windows in
buildings, and solar cell substrates. These composites are light-weight, as
compared to laminated high-strength window glass or ceramic-based composites,
and would be of high value in Home Land Security applications, structural
windows for resisting hurricanes and tornadoes, and as protective armor for
vehicles and airplanes.
TECHNOLOGY TAXONOMY MAPPING
Inflatable
Airport Infrastructure
and Safety
Fluid Storage and Handling
Composites
Radiation Shielding
Materials
| PROPOSAL NUMBER: | 06-I X6.03-8197 |
| SUBTOPIC TITLE: | Material Concepts for Lightweight Structure Technology Development |
| PROPOSAL TITLE: | Ultra-Lightweight Nanocomposite Foams and Sandwich Structures for Space Structures Applications |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Wright Materials Research Co
1187 Richfield
Center
Beavercreek, OH 45430-1120
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Seng Tan
sctan@sprintmail.com
1187 Richfield Center
Beavercreek, OH 45430-1120
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Space structures that are
ultra-lightweight, and have gas barrier property, space durability, radiation
resistance and high impact resistance are desirable to improve the reliability
and provide a safe resting environment for astronauts and equipment operation.
Some of the components currently in use such as stations or habitats use
double-wall thick films with high internal pressure. Some components are in thin
film form and the specific rigidity and dimensional stability needs improvement.
Components of landers and vehicles are subject to dust impact. All these solid
or hollow components are vulnerable in space because of the foreign object
impact or radiation attack. In this Phase I project, we propose to develop
ultra-lightweight, microcellular nanocomposite foams and sandwich structures
that possess all the desirable properties mentioned above. The structural module
can be compacted into a small volume to facilitate launching. The proposed
microcellular nanocomposite foam and sandwich structures do not involve or
release any toxicity and will have much higher specific mechanical properties
than foams and sandwich structures processed by the conventional techniques.
They can be used to either replace or supplement to the inflatable technology
for improvement in reliability, durability, and safety in space operation.
Preliminary research results are very encouraging.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed ultra-lightweight microcellular nanocomposite foam and sandwich
structures have a number of potential applications for space structures
including space stations and habitats, Lunar mission vehicles, landers,
rigidified boom and support structures for Gossamer space structures, rover
subsystems like wheels, chasis, insulation boxes masts, solar array deployment
devices, shelters and hangars for space habitats, airlocks, electronics boxes,
tanks/shells/shields, insulation for propellant tanks, solar arrays radar
boards, and support structures for telecommunication subsystems like struts and
beams, etc.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential
commercial markets for this ultra-low density polymer and nanocomposite foams
and sandwich structures may include commercial aircraft, boots, ships, trains,
buses, trucks, posts, bridges, decks, automobiles, shipping containers, building
panels, etc.
TECHNOLOGY TAXONOMY MAPPING
Propellant
Storage
Airframe
Airlocks/Environmental
Interfaces
Erectable
Kinematic-Deployable
Launch and Flight
Vehicle
Reuseable
Thermal Insulating Materials
Fluid Storage and
Handling
Earth-Supplied Resource Utilization
Composites
Radiation
Shielding Materials
Multifunctional/Smart Materials
| PROPOSAL NUMBER: | 06-I X6.03-8922 |
| SUBTOPIC TITLE: | Material Concepts for Lightweight Structure Technology Development |
| PROPOSAL TITLE: | A Nanotechnology Approach to Lightweight Multifunctional Polyethylene Composite Materials for Use Against the Space Environment |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
TDA Research, Inc.
12345 W. 52nd
Ave.
Wheat Ridge, CO 80033-1917
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Michael Diener
mikee@tda.com
12345 W. 52nd Ave.
Wheat Ridge, CO 80033-1916
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Polyethylene-based composite
materials are under consideration as multifunctional structural materials, with
the expectation that they can provide radiation shielding, micrometeorite
shielding, and pressure containment during interplanetary missions. While
ultrahigh molecular weight polyethylene (UHMWPE) is the hardest known
thermoplastic, its impact strength and wear resistance still pale in comparison
to many other known materials. We propose composites of UHMWPE with these
materials, with the expected outcome of increasing its ability to perform as a
micrometeorite shield.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
technology developed on this project will be immediately useful for
multifunctional radiation shielding/ micrometeorite shielding, a key need for
manned interplanetary and lunar missions.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology
has terrestrial applications in lightweight armor (for soldier and policemen,
e.g.) and in long-lasting joint replacement materials (hips, etc.).
TECHNOLOGY TAXONOMY MAPPING
Composites
Radiation Shielding
Materials
Multifunctional/Smart Materials
| PROPOSAL NUMBER: | 06-I X6.03-9045 |
| SUBTOPIC TITLE: | Material Concepts for Lightweight Structure Technology Development |
| PROPOSAL TITLE: | Lightweight High Temperature Non-Eroding Throat Materials For Propulsion Systems |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Materials Research and Design
300 E.
Swedesford Road
Wayne, PA 19087-1858
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Joseph Pluscauskis
pluscauskis@m-r-d.com
300 E. Swedesford Road
Wayne, PA
19087-1858
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation in this
proposed effort is the development of lightweight, non-eroding nozzle materials
for use in propulsion systems. Lightweight structures are desirable for space
transportation vehicle systems in order to reduce launch costs, increase mission
flexibility/efficiency, and add robustness with respect to the ability to add
weight or additional materials to the mission with minimum sacrifice in
performance. The use of non-eroding materials, coupled with lightweight
materials, as rocket nozzles can further increase mission flexibility by
allowing an increase in performance, higher maximum temperatures, greater
speeds, greater range, bigger payloads, and longer lifetimes. The higher maximum
temperatures may eliminate the need for cooling air, while simultaneously
increasing engine efficiency. Higher maximum use temperature additionally allows
for increased stagnation temperatures and pressures, increasing the propellant
enthalpy, which, in return, can significantly increase the velocity and
performance of the projectile. These benefits result in increased fuel savings.
The advanced materials study will include monolithic ceramics, refractory
metals, and high temperature ceramic matrix composite (CMC) materials. The
manufacturing processes for the monolithic ceramics and refractory metal
materials will include hot isostatic processing (HIP), vacuum plasma spraying
(VPS), electrodeposition. The CMC fabrication processes will include braiding,
filament winding, tape wrapping, and involute layup.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
MR&D's core business is design and structural analysis of high
temperature materials. The fundamental technology and design tools developed in
this SBIR program will allow us to expand our client base and offer more
capabilities to our existing customers. Additionally, the technology developed
here will be translated to other commercial and government applications to
expand the market for refractory material leading edges, nozzles, hypersonic
airframes and ramjet engines.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The results of
this lightweight, high temperature, non-eroding nozzle material study will have
broad ranging applications in the civil aerospace, governmental aerospace
companies, as well as aircraft jet engine manufactures and power generation
equipment manufacturing companies. Potential customers include Boeing, Lockheed
Martin, General Electric Power Systems, and ATK-Thiokol.
TECHNOLOGY TAXONOMY MAPPING
Chemical
High Energy Propellents
(Recombinant Energy & Metallic Hydrogen)
Simulation Modeling
Environment
Testing Facilities
Cooling
Thermal Insulating
Materials
Database Development and
Interfacing
Ceramics
Composites
Metallics
| PROPOSAL NUMBER: | 06-I X6.03-9290 |
| SUBTOPIC TITLE: | Material Concepts for Lightweight Structure Technology Development |
| PROPOSAL TITLE: | Magnesium MMC for Aerospace Structures |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Technology Assessment & Transfer, Inc.
133 Defense Hwy Suite 212
Annapolis, MD 21401-8907
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
David Palaith
palaith@techassess.com
133 Defense Hwy Suite 212
Annapolis, MD
21401-8907
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA will return to the IIS by
2014 and the moon by 2020. To accomplish these missions, NASA will exploit to
the maximum degree possible the Apollo architecture and especially the lessons
learned and technological advances that have occurred over the intervening 40
years in building robust, cost effective, efficient, and, partly reusable
launch, lander, explorer, and resupply vehicles. In support of this effort,
Technology Assessment & Transfer (TA&T) proposes to develop a magnesium
metal matrix composite (MMC) for use as aerospace structural members. This
material exhibits three times the specific stiffness of the best
aluminum-lithium alloys and two times that of PMCs. TA&T will demonstrate
the feasibility and practicality of a low temperature method for achieving high
loading of ceramic particles in a magnesium matrix that will enable a cast or
extruded structural material of non-uniform cross-section exhibiting the unusual
combination of light weight, high specific stiffness and strength, radiation
shielding, and low cost. The MMC will be protected from corrosion by a unique
thin film coating designed specifically to prevent corrosion of aluminum and
magnesium alloys.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
went to the moon with 1960s technology. The President's Vision program will use
technology developed during the intervening 40+ years. NASA is proposing to use
technology at least TRL-6. Thus, NASA cannot develop all the needed technology
internally – it will have to use technology developed outside of agency funded
research. Magnesium MMCs promises to provide performance characteristics in many
areas comparable if not superior to advanced polymer composites, ceramic matrix
composites, fiber composites, high performance light weight alloy systems, light
weight refractory alloys, hybrid material systems, multifunctional material
systems, nano-structured materials. Thus, continued research to expand the
global metal matrix market should profoundly impact future NASA mission.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential
commercial market for magnesium MMCs is staggering. The global market predicted
for all MMCs predicts a growth rate of 6.3% dominated by the automotive industry
as the demand for fuel efficiency compels lighter cars and trucks. It has been
predicted that China represents the fastest growing market for MMCs. Magnesium
MMCs have been restricted by the difficulty of achieving high loading and by
corrosion. The solution of those two problems removes both impediments to market
entry.
TECHNOLOGY TAXONOMY MAPPING
Airframe
Erectable
Launch and
Flight Vehicle
Modular Interconnects
Structural Modeling and
Tools
Manned-Manuvering Units
Composites
Metallics
| PROPOSAL NUMBER: | 06-I X6.03-9695 |
| SUBTOPIC TITLE: | Material Concepts for Lightweight Structure Technology Development |
| PROPOSAL TITLE: | Composite Shell / Nanoporous Organosilica Core -Multifunctional Structures |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Iten Industries, Inc.
4602 Benefit
Ave
Ashtabula, OH 44005-2150
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Paula Watt
pwatt@itenindustries.com
4602 Benefit Ave
Ashtabula, OH
44005-2150
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Planetary exploration presents
challenges for mobility, fuel efficiency, payload weight management, robustness,
and thermal as well as radiation protection. There is a need for lightweight
structures in space transport, vehicle systems, instrumentation, planetary
access, as well as operations including facilities and habitats. These vehicles,
equipment, and structures will be subjected to rigorous environmental exposures
and assaults. Innovations that increase specific strength and stiffness, reduce
weight, provide radiation shielding, enhance thermal management, and improve
robustness, in a safe, reliable, cost effective manner will contribute to the
success of these missions. This proposal offers an innovative solution utilizing
fundamental mechanical engineering principles taken to a multi-hierarchical
level. Directionally oriented reinforced composites, structural foam, honeycomb,
and core-shell designs are mature technologies. The distinguishing element of
the approach for this proposal is the unique, new to the world, X-aerogel core
material developed by NASA GRC. Aerogels are touted as the lowest-density solid
materials known and have excellent insulation capacity but are extremely
fragile. Through conformal polymer crosslinking of the silica structure, these
sol-gel castings can be strengthened into the realm of load bearing materials at
densities in the 0.2 to 0.3 g/cc range. Further, this proposal explores
manipulation of the core material nanostructure through surfactant induced
micelle formation. This will create controlled morphology nano-honeycomb, which
is expected to greatly enhance the strength and reliability versus the sol-gel
random nanofoam through elimination of stress concentrators and optimal
distribution of load. When these cores are coupled with advanced composite
skins, resulting structures are extremely lightweight with strength, stiffness,
and insulation performance far beyond what is currently commercialized.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High
strength, light weight, robust, thermally insulative, and radiation protecting,
structures for planetary exploration are needed. The largest anticipated
applications for this development is building structures for operations
facilities and habitats that can be kitted and quickly erected with minimal
effort. These structures will have conductivity imparted as required to provide
lighting strike deterrence, will have very high thermal insulation efficiency,
be very impact, abrasion, and wind resistant, and provide radiation protection.
A typical building kit would consist of anchoring, framing, and load bearing
wall and roofing panels. The lightweight panels could consist of an outer shell
utilizing either carbon fibers or carbon nanotubes to impart electrostatic
dissipation in the case of lighting strike. This skin will be ballistic/storm
grade composite to withstand aggressive impacts. The highly insulative core
material will be X-aerogel or polymer modified nano-honeycomb siliceous
structures that have been modified with high hydrogen content species to impart
radiation shielding. The inner skin could be less robust and aesthetically
desirable. Other areas of use will be in armoring vehicles and aircraft for the
same hazards with reduced weight. Thermal and acoustic insulation benefits for
these transport applications in addition to impact resistance, radiation
protection, and low weight will be realized.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
These
nanoporous composites have a wide range of utility for defense applications. It
is a logical extension that the DOD will have interest in these materials and
structures for aerospace, marine, vehicles, and ballistic protected facilities.
As the technology is proven successful and processes are streamlined,
commercialization will follow into civilian marine, airline, consumer, and
construction markets. Because of the unique combination of exceptional
properties, a network of eager end-users for a number of applications including
boat cores, building panels, skylights, aircraft, automotive, pressure vessel,
ballistic protection, and refrigeration insulation already exists. In buildings,
the combination of structural walls and highly efficient insulation could reduce
overall materials and installation costs. The Office of Energy Efficiency and
Renewable Energy reports that in our buildings today we consume 39% of the
energy and more than 70% of the electricity in the nation. In these energy
conscious times, improved insulation materials will be quickly be approved for
use. Drywall type forms could replace the need for foamed in or fiberglass
insulation allowing for thinner wall sections and reduced material costs. The
weight and bulk of roofing structures could be greatly reduced. With a single 1"
windowpane of aerogel equivalent to the insulation provided by 32 windowpanes of
glass, translucent X-aerogel are a highly desirable material for daylighting.
TECHNOLOGY TAXONOMY MAPPING
Airframe
Erectable
Launch and
Flight Vehicle
Thermal Insulating Materials
Fluid Storage and
Handling
Composites
Radiation Shielding Materials
| PROPOSAL NUMBER: | 06-I X7.01-9703 |
| SUBTOPIC TITLE: | Supportability Technologies for Long-Duration Space Missions |
| PROPOSAL TITLE: | Vacuum-Compatible Multi-Axis Manipulator/Machining Center for Long-Duration Space Missions |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
BECK ENGINEERING, INC.
3319 21st Ave
NW
Gig Harbor, WA 98335-7992
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Douglas Beck
dbeck23@aol.com
3319 21st Ave NW
Gig Harbor, WA 98335-7992
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has many needs for
maintenance and repair technologies for long-duration human space missions. We
propose to develop a compact, portable, vacuum-compatible, multi-axis
Manipulator/Machining Center (M/MC) to satisfy many of NASA's needs. Our M/MC
will provide complex manipulation during: layer-additive manufacturing;
collection of geometric data for reverse-engineering; real-time non-destructive
evaluation; and non-destructive material property determination. Our M/MC will
also finish-machine near-net-shape parts produced using layer-additive
manufacturing. Design features of our M/MC will: minimize mass, volume, and
power consumption while providing required capabilities; maximize life and
reliability; and enable our M/MC to operate in space-based vacuum, microgravity,
and partial-gravity environments. In Phase I, we will: generate a preliminary
design of our M/MC; project the machining performance, mass, volume, and power
consumption of our M/MC; and show how our M/MC can be integrated with
layer-additive equipment. In Phase II, we will design-in-detail, build, and test
a prototype M/MC. In Phase III, we will design, build, and sell M/MCs to the
government and private sector.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our
Manipulator/Machining Center (M/MC) will satisfy many of NASA's needs for
space-based manufacturing applications. Our compact, portable, multi-axis M/MC
will perform: (1) reverse-engineering data generation; (2) additive
manufacturing; (3) real-time non-destructive evaluation during layer-additive
processing; (4) non-destructive material property determination; (5)
recycling/generation of feedstock materials for deposition processes; and (6)
five-axis subtractive manufacturing.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We will adapt
our space-based Manipulator/Machining Center (M/MC) to produce an Earth-baced
M/MC for many military and private-sector manufacturing applications, including:
military in-theater fabrication of spare parts; and private-sector
manufacturing, including die/mold work, prototyping, small production runs, and
cases in which raw materials are expensive.
TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and
Systems
Manipulation
Airframe
Launch and Flight Vehicle
Testing
Facilities
Data Input/Output Devices
Expert Systems
Human-Computer
Interfaces
Portable Data Acquisition or Analysis Tools
Earth-Supplied
Resource Utilization
In-situ Resource
Utilization
Microgravity
Ceramics
Composites
Metallics
Optical
& Photonic Materials
Tribology
| PROPOSAL NUMBER: | 06-I X7.02-8690 |
| SUBTOPIC TITLE: | Human-System Interaction |
| PROPOSAL TITLE: | An Integrated Human System Interaction (HSI) Framework for Human-Agent Team Collaboration |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Intelligent Automation, Inc.
15400 Calhoun
Drive, Suite 400
Rockville, MD 20855-2785
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Margaret Lyell
mlyell@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville, MD
20855-2785
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA commitment to a human
presence in space exploration results in the interaction of humans with
challenging environments in space, on lunar, and on planetary bodies. Meeting
these challenges requires the development of technologies that will support
human system interaction by integrating monitoring, feedback and situational
awareness across all types of mission parameters and observables. A successful
human system interaction (HSI) system could extend based on existing agent
frameworks and software architectures in which NASA is interested. Our proposed
approach enables the design of embedded protocols for human-agent interactions
to support crew health, safety, and cognitive load modeling in the context of
supporting plan execution as well as overall mission goals and activities.
Particularly, our proposed HSI framework consists of various types of agents
(including sensing and situational awareness abilities, etc.), a suite of HSI
protocols for delegation, adjustable autonomy, situational awareness, HSI and
mission-oriented coordination, and the integration of the proposed framework
with existing systems to assist mission task operations by providing previously
hard to observe, yet vital dynamic information, e.g. human health conditions.
Our innovation is an agent-based integrated framework for modeling, simulation
and implementation of context and mission aware human-system interaction
protocols and interfaces.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
primary result from this SBIR project will be the integrated HSI framework for
collaboration of human-agent teams, which addresses the key concepts including
human agent delegation, situational awareness, adjustable autonomy, and
HSI/mission-oriented coordination. Our efforts on this project will result in a
full design for the HSI framework including its associated components and a
communication protocol suite. A working prototype for HSI in a crew health
monitoring and performance scenario, built on IAI's CybeleTM agent platform,
will support NASA mission needs.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The HSI
framework is being developed for managing human system interaction. It will
provide real time health and mission-oriented situational awareness and
assistance for mission planning. The HIS framework includes various supporting
elements in the design e.g. ontological representation of domain knowledge and
team capabilities, protocol development, extensibility. The HSI framework can be
utilized in any domain areas that involve humans in the decision loop, where the
human is supported by software elements. This includes areas of DOD as well as
commercial applications such as first responder support, equipment maintenance
and troubleshooting support, etc.
TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Autonomous
Reasoning/Artificial Intelligence
Human-Computer Interfaces
| PROPOSAL NUMBER: | 06-I X7.02-9092 |
| SUBTOPIC TITLE: | Human-System Interaction |
| PROPOSAL TITLE: | Software Tools that Control a Framework of Perceptual Interfaces and Visual Display Systems for Human-System Interaction with Robotic and Autonomous S |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Turbogizmo, LLC
6040 Rockton
Court
Centreville, VA 20121-3082
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Stephen Schwartz
sschwartz@turbogizmo.com
6040 Rockton Court
Centreville, VA
20121-3082
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Turbogizmo, LLC will develop
new software technology for Human-System Interaction (HSI) for NASA that
increases performance and reduces the risk of conducting manned exploration
missions. This HSI technology combines intelligent software agents, decision
support systems and perceptual interfaces to facilitate human collaboration with
robotic and autonomous systems while supporting the use of augmented cognition
models. This will provide the optimal configuration of multi-modal user
interfaces to improve performance and safety during critical mission operations.
Future exploration missions will involve greater information availability for
crewmembers and enhancements to EVA systems will provide visual information for
situational awareness. HSI technology that manages the exchange of information
between Human and Robotic or Autonomous systems using augmented cognition models
will result in reduced cognitive load caused by inappropriate information while
minimizing the effort required when interacting with autonomous systems.
Turbogizmo proposes to develop a service-based architecture for configuring a
suite of multi-modal HCI technologies based on operational scenarios, evaluation
of perceptual interfaces with cost/value propositions for interface
configurations. This framework will be validated by experimentation and
demonstration This technology will close a critical technology gap by enabling
improved interaction for exploration crewmembers performing routine and
contingency operations.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Software
Tools that Control a Framework of Perceptual Interfaces and Visual Display
Systems for Human-System Interaction with Robotic and Autonomous Systems are a
critical tool that has been missing from mobile, wireless and pervasive
information technology. As miniaturization and wireless technology has improved
and user demographics have increased, the usefulness has been limited by the
requirement of using not only the hands to operate, but also the heavy cognitive
load placed on the user to interact with the visual information delivered. Often
the information is delivered during a critical tasks causing an interruption and
lowering performance or imposing a risk to task or safety. Our technology, once
developed for commercialization, will enable the use of hands-free perceptual
interfaces for controlling and managing the information flow essential to mobile
work task improvements and optimal efficiency with less risk than experienced
today.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Most
appropriate to the commercialization of technology developed for this topic will
be the applications for use by first responders for homeland security and public
safety officials for hazard mitigation during local emergency situations. HSI
with visual information display technology can provide users with improved
access to visual information such as procedures, checklists, technical drawings,
images and training materials. This allows workers to access visual information
even while they are engaged in demanding tasks in mobile environments. HSI for
robotic and autonomous system collaborations will enable increased use of
robotic assets for dangerous tasks to provide increased public safety and
industrial productivity. Commercialization opportunities include the following
market sectors: • Public Safety: Firefighters, Police, Military, Security,
Search and Rescue, Hazard Mitigation • Industrial: Construction, Repair,
Training, Inspection, Inventory, Logistics, Safety • Commercial: IT for the
Office, Sales, Marketing, Insurance, Analysis, Network • Consumer: Shopping,
Travel, Entertainment, Education, Security, Correspondence, Finance
TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated
Robotic Concepts and Systems
Intelligence
Teleoperation
| PROPOSAL NUMBER: | 06-I X7.02-9316 |
| SUBTOPIC TITLE: | Human-System Interaction |
| PROPOSAL TITLE: | A Software Framework for Coordinating Human-Robot Teams |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Traclabs, Inc.
8610 N. New Braunfels, Suite
110
San Antonio, TX 78217-2356
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Debra Schrechenghost
schreck@traclabs.com
8610 N. New Braunfels, Suite 110
San
Antonio, TX 78217-2356
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Robots are expected to fulfill
an important role in manned exploration operations. They can reduce the risk of
crew EVA and improve crew productivity on routine tasks. They can be supervised
locally by astronauts or remotely by ground control. In a sense, robots will
become members of the operational team. Just like human teams, these human-robot
teams must exchange information, follow established protocols, and coordinate
their activities to ensure that mission operations are safe and effective.
Supporting such team operations requires infrastructure for human-robot
interaction. TRACLabs proposes to develop a software framework that facilitates
human-robot teaming, from team formation until completion of team operations. We
will build on the existing Distributed Collaboration and Interaction (DCI)
System, a software multi-agent system developed by TRACLabs to assist
human-automation interaction. DCI provides a software agent for each human team
member that delivers services supporting mission duties. An innovation of this
project is providing DCI agents for robots as well as humans in the team.
Another innovation is the use of human models to give robots insight into human
behavior to improve interaction. Phase I will produce a software framework
prototype for human-robot interaction and a framework design for implementation
in Phase II.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Exploration missions will require that humans and robots work
together. Robots will perform high risk tasks like EVA and routine or repetitive
tasks to improve crew productivity. Introducing robots into manned space
operations, however, will change the way these operations are conducted. It will
introduce new supervisory tasks for crew and ground control, including
maintaining awareness of robotic activities and handling problems the robot
cannot resolve. The proposed human-robot interaction framework will enable
effective human supervision of robots, both nearby and remotely. Such capability
will first be needed for lunar surface operations and will be enabling for
manned missions into deep space.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Unmanned air
and ground vehicles are becoming more common in battlefield situations. Future
Combat Systems envision manned and unmanned vehicles of all sizes working
side-by-side. Additionally, Congress has mandated that one-third of all military
vehicles must be unmanned by 2015. The military envisions robots and soldiers
working side-by-side to accomplish missions, as well as remote operators
supervising robot teams. Currently several operators control one autonomous
vehicle. The proposed framework for human-robot interaction will help reverse
this ratio. Non-military markets include civilian SWAT teams, urban search and
rescue and hostage situations. There are approximately 100 US cities with
populations over 200,000 that could have use of a mobile robot for search and
rescue, bomb disposal or hazardous materials handling. Often a single mobile
robot will perform many different tasks. Operators will typically have less
training and experience in using robots than military operators, thus support
for effective human-robot interaction is essential.
TECHNOLOGY TAXONOMY MAPPING
Human-Robotic
Interfaces
Intelligence
Perception/Sensing
Autonomous
Reasoning/Artificial Intelligence
Human-Computer Interfaces
| PROPOSAL NUMBER: | 06-I X7.03-8448 |
| SUBTOPIC TITLE: | Surface Handling and Mobility, Transportation, and Operations Equipment (Lunar or Mars) |
| PROPOSAL TITLE: | Lunar All-Terrain Utility Vehicle for EVA |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
ProtoInnovations, LLC
1908 Shaw
Ave.
Pittsburgh, PA 15217-1710
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Stuart Heys
sheys@protoinnovations.com
1908 Shaw Ave.
Pittsburgh, PA
15217-1710
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ProtoInnovations, LLC proposes
to develop a new type of planetary rover called a Lunar All-terrain Utility
Vehicle ("Lunar ATV") to assist extra-vehicular activities in future lunar
missions. The vehicle will operate unmanned or with an astronaut driving
onboard. It will have a roughly 4 m2 footprint and be able to about twice as
fast as an astronaut can walk on the Moon. The vehicle will feature four-wheel,
all-terrain mobility with traction control. A multi-purpose tool interface and
interchangeable cargo bays will support a variety of mission payloads. The Lunar
ATV will be used for mission such as site preparation, emplacing beacons,
equipment and commodity distribution, and sampling. It will also be useful for
human/robot interaction experiments taking place at NASA research centers. The
primary innovations of this effort are: • A high-efficiency, long-life,
lunar-relevant traction drive system • A simplified steer / suspension chassis
built for speeds over 1 m/s without sacrificing weight or maneuverability • A
multi-purpose tool interface for earthmoving, sampling, emplacing, etc. •
Traction control software to maximize performance in earthmoving and negotiating
rough terrain • CLARAty-compatible vehicle and tool interfaces to leverage
NASA-developed teleoperation and autonomy software ProtoInnovations brings an
impressive amount of experience to the task of designing the Lunar ATV. Working
at Carnegie Mellon University, members of our team have developed robots to
operate in some of the harshest environments on Earth: surveying Antarctic ice
fields, traversing the Atacama Desert, exploring into an Alaskan volcano and
mapping Chernobyl. In total, our robots have traveled roughly 500 km through
some of the most difficult terrain on Earth. We've accomplished these tasks by
building robots that are, above all else, controllable and reliable. Our team
has experience building all of the subsystems involved in this project.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
ProtoInnovations will vigorously push our Lunar ATV technology
into NASA's manned and unmanned lunar exploration program. This will require
close interaction with the customer. We will foster this by making the vehicle
available for testing wherever possible. With our rapid and iterative approach
to development and the flexible design of the Lunar ATV, we will adapt as NASA's
lunar exploration program continues. The Lunar ATV also represents a new class
of space robotics research rover: larger, faster, and more capable than K9 and
K10 with a high payload capacity. Its ability to be driven by an astronaut opens
up new types of EVA simulations. We hope that adoption of the Lunar ATV by NASA
will provide ProtoInnovations with a sustainable R&D effort until the Lunar
ATV design gains a high TRL level and is infused into the lunar exploration
program.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercially,
work on unmanned ground vehicles (UGVs) is often directed towards the defense
market. Our work on traction control has applicability to UGVs that use electric
drive motors, including defense products such as iRobot's PackBot and
Foster-Miller's TALON. Members of our team have worked as subcontractors to
Foster-Miller, so we plan to pursue business development opportunities with this
prominent defense robotics manufacturer. Our traction drive design will also
benefit terrestrial UGVs operating at speeds of several meters per second. It
will consume power more efficiently and feature a longer operating life than
traditional high-speed motors coupled with harmonic drives. A multi-purpose tool
interface for UGVs will also be useful to the hazmat robots and UGVs that handle
explosives. We will pursue R&D opportunities from the Department of Justice,
the Department of Homeland Security, and DARPA to adapt our lunar-relevant
design to terrestrial applications.
TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and
Systems
Mobility
Manipulation
Manned-Manuvering Units
Tools
| PROPOSAL NUMBER: | 06-I X7.03-9595 |
| SUBTOPIC TITLE: | Surface Handling and Mobility, Transportation, and Operations Equipment (Lunar or Mars) |
| PROPOSAL TITLE: | A field reconfigurable manipulator for rovers |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Traclabs, Inc.
8610 N. New Braunfels, Suite
110
San Antonio, TX 78217-2356
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Robert Burridge
burridge@traclabs.com
1012 Hercules
Houston, TX 77058-2356
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Robots will be precursors to
human exploration of the lunar surface. They will be expected to prepare the
lunar surface for human habitation as well as conduct scientific investigations.
As humans arrive the robots should be able to shift to providing direct
assistance to human exploration activities. Such tasks require a new generation
of robotic vehicles -- a generation that has flexible, dexterous manipulation
capabilities and adjustable software controllers that can shift between remote
teleoperation, autonomy and co-located human interaction. Our innovation
consists of two components. The first component is a reconfigurable, dexterous
manipulator that is designed to be mounted on a mobile robot. The manipulator
will be light-weight and low-power. It will contain a reconfigurable number of
up to seven degrees-of-freedom. The second component is a software system that
can adjust control of the manipulator from teleoperated to autonomous and that
can control the mobile robot and the manipulator as a coordinated unit. We
propose to implement a method called Coordinated Resolved Motion Control that
will automatically and jointly control the rover as well as the manipulator such
that the manipulator will stay away from singularities. Together these two
innovations will substantially increase the capabilities of NASA rovers, making
them more efficient and effective.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
exploration missions will require significantly more complicated robots than are
currently being used. Several NASA research projects, including Robonaut, K-10
and Athlete are working towards highly dexterous, intelligent robots. Our NASA
applications will focus on our software as much as our hardware. While only a
small number of dexterous manipulators will be needed by NASA, many of NASA's
research robots will require coordinated motion of rover and manipulation. For
example, Centaur is a four-wheeled base with Robonaut on it being developed at
NASA Johnson Space Center. NASA Ames Research Center (ARC) and the Jet
Propulsion Laboratory also have research robots that combine mobility and
manipulation. We will work with all of these researchers in Phase 3 to adapt our
coordinated control software to their robots. In addition we expect to deliver
our reconfigurable manipulator to NASA ARC for permanent mounting on one of
their K-10 robots.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Unmanned
vehicles are becoming more and more common in battlefield situations. The Future
Combat Systems (FCS) program envisions manned and unmanned vehicles of all sizes
working side-by-side. In addition, Congress has mandated that one-third of all
military vehicles must be unmanned by 2015. Explosive Ordnance Disposal (EOD) is
the primary domain in which robots are currently used. No EOD robot on the
market has a dexterous manipulator. We believe our reconfigurable technology
will make us the clear choice in this market. Non-military markets such as
civilian EOD, urban search and rescue and hostage situations are also
increasingly using robots. Often a single mobile robot will have to perform many
different tasks giving our reconfigurable technology an edge. Another market is
the research robotics community such as universities and government
laboratories. The reconfigurable aspect of our manipulator is a selling point
because it allows laboratories to upgrade to more DOF over time and allows them
to reconfigure the manipulator for different research objectives. We will also
generalize our mobile robot interface to allow integration with commercially
available robots. We expect that the next generation of robotics research will
focus on mobile manipulation with programs being supported by NSF, NASA, DARPA
and other funding agencies.
TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated
Robotic Concepts and
Systems
Intelligence
Mobility
Manipulation
Perception/Sensing
Teleoperation
Autonomous
Reasoning/Artificial Intelligence
| PROPOSAL NUMBER: | 06-I X8.02-9409 |
| SUBTOPIC TITLE: | Space Based Nuclear Fission Power Technologies |
| PROPOSAL TITLE: | A Novel, Ultra-Light, Heat Rejection System for Nuclear Power Generation |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Creare Inc
P.O. Box 71
Hanover, NH
03755-0071
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Jay Rozzi
jcr@creare.com
P.O. Box 71
Hanover, NH 03755-0071
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For lunar-based fission power
systems that will support In-Situ Resource Utilization (ISRU) or Mars robotic
and manned missions, power requirements may vary from 10s to 100s of kWe to
support initial human missions and longer term lunar bases. Due to the large
amounts of waste heat generated by these systems, a key consideration is the
development of lightweight, highly efficient heat rejection systems (HRS) that
can operate at elevated temperatures (~550 K). Currently, an approach that is
being strongly considered is the use of titanium sheathed heat pipe with a
carbon composite over-wrap, combined with a carbon composite radiator panel to
decrease the system mass. Our innovation is the integration of an ultra-light
radiator panel material with a lightweight titanium heat pipe. Our calculations
show that our approach will reduce the total mass by as much as 20% compared to
the carbon-composite systems under consideration and represents a lower risk
approach to achieve a practical HRS.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our
innovative heat rejection system, which is based on the integration of an
ultra-light radiator panel material with a lightweight titanium heat pipe, will
reduce the total mass by as much as 20% compared to the carbon-composite systems
under consideration. The results of our work would have far-reaching benefits
for government space and military systems. These include nuclear power
generation for long-duration interplanetary and planetary-based missions, mobile
power systems, and satellites.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
While the main
applications for our innovation are space-based systems, our novel heat
rejection systems can be applied to commercial thermal management systems that
are severely weight constrained. Such systems can benefit from the lightweight,
high-temperature capability of our unique innovation. These applications can
include radar, aerospace, large-scale power systems, and energy recovery
applications.
TECHNOLOGY TAXONOMY MAPPING
Cooling
Nuclear Conversion
Power
Management and Distribution
| PROPOSAL NUMBER: | 06-I X8.03-8162 |
| SUBTOPIC TITLE: | Space Rated Batteries and Fuel Cells for Surface Systems |
| PROPOSAL TITLE: | Phase I Nano-Engineered Materials For Rapid Rechargeable Space Rated Advanced Li-Ion Batteries |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Yardney Technical Products Inc
82 Mechanic
St
Pawcatuck, CT 06379-2167
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Joseph Gnanaraj
joeg@lithion.com
82 Mechanic Street
Pawcatuck, CT 06379-2154
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lithium-ion (Li-ion) batteries
are attractive candidates for use as power sources in aerospace applications
because they have high specific energy, energy density and long cycle life.
Yardney/Lithion Inc has become the leader in cutting edge Lithium Ion batteries.
At the present moment, two of the Lithion batteries are operating on the surface
of Mars with great success. In a conventional Li-ion battery when the rate is
higher than C, their charge/discharge performance is severely degraded and loss
its capacity permanently. Now we are focusing our interest to develop Li-ion
batteries that can rapidly charge/discharge at high current rates. Yardney in
collaboration with researchers at Worcester Polytechnic Institute, MA, proposes
to investigate a new non-toxic nano-engineered electrode that significantly
shortens the Li+ diffusion length within the electrode materials and increases
the rate capability of Li-ion batteries. The goal of Phase I of this project
will be to develop new nano-architectured anode that has rapid Li+ recharge
characteristics. Emphasis will be placed upon the construct of Fe3O4 based
nano-engineered electrodes with Cu nanorods as current collectors. The high-rate
capabilities change with the change in the diameter, packing density and aspect
ratio of the Cu nanorods will be studied.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
target application for this nano engineered Li ion battery technology is space
applications that require high energy and power densities. This technology will
have superior performance at low temperatures due to the very small internal
impedance of the nano-engineered electrode materials.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High power
applications include power tools, electric vehicles and telecommunications.
Automotive and industrial sectors, where the slim, small-sized battery will
deliver large amounts of energy while requiring only a minute to recharge. For
example, the battery's advantages in size, weight and safety highly suit it for
a role as an alternative power source for hybrid electric vehicles.
TECHNOLOGY TAXONOMY MAPPING
Energy Storage
| PROPOSAL NUMBER: | 06-I X8.03-8784 |
| SUBTOPIC TITLE: | Space Rated Batteries and Fuel Cells for Surface Systems |
| PROPOSAL TITLE: | Low Flammability, Wide Temperature Range Electrolytes for Lithium Ion Batteries |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
T/J Technologies Inc
3850 Research Park
Drive
Ann Arbor, MI 48108-2240
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Greg Less
gless@tjtechnologies.com
3850 Research Park Drive
Ann Arbor,
MI 48108-2240
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA, the military, and even
consumer product manufacturers are limited in their ability to impliment lithium
ion battery technology by the effective operating temperature of the
state-of-the-art electrolytes. In this effort T/J Technologies will develop
novel ionic liquid electrolytes. Ionic liquids, salts that melt at very low
temperatures, show potential as solvents that will allow lithium ion batteries
to operate at temperatures as low as -80<SUP>o</SUP>C and as high as
100<SUP>o</SUP>C. Additionally, ionic liquid electrolytes are well
suited for space applications because they have near zero vapor pressure and are
a non-flammable alternative to the organic solvents commonly used in batteries.
It is anticipated that this technology will benefit a broad range of Exploration
mission applications including portable power for landers, rovers, and astronaut
equipment, as well as stationary energy storage applications such as base power,
and storage systems for crew exploration vehicles and spacecraft. In phase I we
will deliver a laboratory prototype cell capable of performing between the NASA
temperature extremes of -60<SUP>o</SUP>C and
60<SUP>o</SUP>C while retaining greater than 80 % of its room
temperature capacity and cycle life. In a Phase II effort, the electrolyte will
be transitioned to production type cells and fully qualified for safety, life
and space use.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This
program directly addresses the market needs of NASA by providing a safe, fast
lithium ion battery capable of operating over a wide range of temperatures. The
development of safe, wide temperature range lithium ion batteries is important
for a variety of NASA near term and long term goals. Namely, high discharge
rate, low temperature batteries could see useful deployment on exploration
mission applications including portable power for landers, rovers, and astronaut
equipment, as well as stationary energy storage applications such as base power,
and storage systems for crew exploration vehicles and spacecraft. Nearly 40% of
all lithium ion batteries, approximately 400 million units, will be used by the
military and other government agencies by 2010. By increasing the useful
temperature range, decreasing the fire hazard, and allowing for periodic
state-of-health checks of the batteries used in important components for our
space and military needs, the electrolyte proposed here will not only increase
the usability of lithium ion batteries but will also increase their safety and
reliability.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Increasing the
operational temperature range and safety of lithium ion batteries offers the
potential for huge market opportunities in both military and civilian markets.
There are currently many lithium ion battery applications that could benefit
from the development of a wide temperature electrolyte; Military and telecom
applications are the projected two largest consumers of lithium ion batteries
and have some of the most demanding temperature ranges for their batteries.
Military applications currently span from -60<SUP>o</SUP>C to
80<SUP>o</SUP>C, however, the upper operational temperatures
required for military use is likely to increase as our forces are being deployed
into more and more inhospitable locations. Munitions stored in the desert are
expected to reach temperatures as high as 125<SUP>o</SUP>C.
Telecommunication batteries used in cellular phones and Personal Data Assistants
have become an integral part of our daily personal and business lives. Consumers
expect these devices to work both outdoors in the winter time in Fairbanks,
Alaska and after having been left on the dashboard of a car in Tucson, Arizona.
Both of these markets would see a large benefit from a wide temperature range
electrolyte.
TECHNOLOGY TAXONOMY MAPPING
Energy Storage
| PROPOSAL NUMBER: | 06-I X8.03-9013 |
| SUBTOPIC TITLE: | Space Rated Batteries and Fuel Cells for Surface Systems |
| PROPOSAL TITLE: | Composite Conducting Polymer Cathodes For High Energy Density Lithium-Ion Batteries |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Santa Fe Science and Technology, Inc.
3216
Richards Lane
Santa Fe, NM 87507-2940
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Ian Norris
norris@sfst.net
3216 Richards Lane
Santa Fe, NM 87507-2940
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future NASA planetary
exploration missions require secondary (rechargeable) batteries that can operate
at extreme temperatures (-60<SUP>o</SUP>C to
60<SUP>o</SUP>C) yet deliver high specific energies (> 180
W·hr/kg) and long cycle life (>2,000 cycles). Functional organic materials
are a promising technology for use as the cathode in Li-Ion batteries due to
their high specific energy density. It is also expected that the use of
polymeric cathodes instead of lithium metal oxides will make Li-Ion batteries
thinner, lighter and less environmentally hazardous. This Phase I proposal is
based on demonstrating the feasibility of fully packaged Li-Ion batteries that
have a superior specific energy (>200 W·hr/kg) through the use of novel
polymeric cathodes (composite conducting polymer/disulfide materials) when
coupled with room temperature ionic liquid (RTIL) electrolyte. Compared to
traditional organic electrolyte systems (e.g. (e.g. lithium salts dissolved in
alkyl carbonates), RTIL electrolytes have favorable electrochemical windows
(> 5 V) and high ionic conductivity over a wide range of temperatures from
–60?C to 250?C and are known to prolong the lifetime of conducting polymer
electrochemical devices. Besides these highly desirable characteristics for use
in these novel Li-ion batteries, RTILs have inherent safety characteristics by
virtue of their thermal stability, non-flammability, non-volatility and low heat
of reaction with active materials.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
High-energy, rechargeable batteries capable of operating over a
wide temperature range are of interest for a number of NASA applications.
Rechargeable Li-Ion batteries offer significant advantages over nickel (Ni-Cd
and NiMH) systems for use in space mission applications, including reduced
weight and volume of the energy storage system. The proposed work will develop
batteries with higher specific energies and extend the low temperature range of
these batteries allowing their use on a wider variety of missions. Specifically
these Li-Ion rechargeable batteries are can be used in many aerospace
applications that include planetary landers, planetary rovers, planetary
orbiters, earth orbiting spacecraft (geosynchronous earth orbit and low earth
orbit) and astronaut equipment (lighting, power tools, communication devices).
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The exponential
growth in portable electronics such as laptop computers, digital cameras, and
cellular phones has created enormous interest in the development of smaller,
lighter, and safer Li-Ion rechargeable batteries. Although Li-ion batteries are
the state-of-the-art power sources for a variety of portable electronic devices,
during the past decade there have been numerous recalls of these batteries due
to overheating problems. Li-ion batteries combine highly energetic materials in
contact with a flammable and volatile electrolyte based on organic solvents.
Room temperature ionic liquids electrolytes possess inherently desirable safety
characteristics by virtue of their thermal stability, non-flammability and
non-volatility. The non-flammability is effective in preventing these Li-Ion
batteries from catching fire, while their non-volatility prevents the batteries
from bursting. These inherent safety characteristics are highly beneficial for
the use Li-ion batteries in hybrid and electric vehicles.
TECHNOLOGY TAXONOMY MAPPING
Multifunctional/Smart
Materials
Energy Storage
| PROPOSAL NUMBER: | 06-I X8.03-9246 |
| SUBTOPIC TITLE: | Space Rated Batteries and Fuel Cells for Surface Systems |
| PROPOSAL TITLE: | Closed-loop Pure Oxygen Static Feed Fuel Cell for Lunar Missions |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Distributed Energy Systems
10 Technology
Drive
Wallingford, CT 06492-1955
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Luke Dalton
ldalton@protonenergy.com
10 Technology Drive
Wallingford, CT
06492-1955
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In order to address the NASA
lunar mission, DESC proposes to develop a proton exchange membrane (PEM)
closed-loop pure oxygen fuel cell for application to lunar surface exploration,
building upon DESC's expertise and fundamental demonstrations in closely related
technology. Building upon the recent NASA SBIR Phase II and Navy SBIR Phase I
work, the static feed URFC hardware will be converted for primary fuel cell
performance. The cell performance will be characterized with two or more
membrane-electrode assembly configurations with a goal of achieving the highest
efficiency. Sub-scale stacks will be tested for durability. Thermal modeling
will be conducted to predict the level of heat removal required by scale-up
stacks. Thermal management techniques will be investigated to permit effective
scale-up.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Based on
DESC's unique experience in commercializing PEM-based products, transitioning to
military and civilian aerospace applications are important outcomes of this
technology development effort. Civilian commercial derivatives of this
technology would be enabling technology for airship-based telecommunications
systems and reliable remote power applications. Impacts of this technology on
military operations include enabling high altitude unmanned aerial vehicle
operations and a variety of underwater vehicle operations, especially unmanned
underwater vehicles. The similarity between the high altitude and undersea
applications is that both require the storage of oxidant in addition to the
storage of fuel. Pure oxygen capable fuel cells are a critical need for both
operating environments. The high altitude UAV's can be used for missile defense,
surveillance and communications. Undersea applications include long-term
distributed data gathering with long endurance buoys, transport of special
forces personnel, and mine neutralization among others.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition,
DESC is working to commercialize discrete RFC (DRFC) systems for terrestrial
back-up power applications. DESC's UNIGEN<SUP>REG</SUP> regenerative
fuel cell is under development for telecommunications backup power systems as a
replacement for valve regulated lead acid batteries and commercial generator
sets. This back-up power system provides both ride-through capability and rapid
response characteristics at a lower overall life cycle cost than conventional
technology. A natural extension of back-up power is application in conjunction
with inherently intermittent renewable energy sources. Additional massive
undeveloped markets are emerging as the two billion inhabitants of the planet
now without electricity move toward access to power. Small-scale power
generation and/or storage will become another distributed technology analogous
to cell phones for communications.
TECHNOLOGY TAXONOMY MAPPING
Tankage
Energy
Storage
Photovoltaic Conversion
Power Management and
Distribution
Renewable Energy
| PROPOSAL NUMBER: | 06-I X8.03-9828 |
| SUBTOPIC TITLE: | Space Rated Batteries and Fuel Cells for Surface Systems |
| PROPOSAL TITLE: | Advanced Composite Bipolar Plate for Unitized Regenerative Fuel Cell/Electrolyzer Systems |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
GINER ELECTROCHEMICAL SYSTEMS, LLC
89
Rumford Avenue
Newton, MA 02466-1311
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Cortney Mittelsteadt
cmittelsteadt@ginerinc.com
89 Rumford Avenue
Newton, MA
02466-1311
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of an advanced
composite bipolar plate is proposed for a unitized regenerative fuel cell and
electrolyzer system that operates on pure feed streams (H2/O2 and water,
respectively). The composite bipolar plate can greatly simplify "closed-loop"
unitized fuel cell/electrolyzer power systems, as it eliminates the need for
saturators, a second stack and water/gas phase separation. It provides a
substantial system improvement over presently used alkaline systems in that it
allows for simple high pressure operation with a high differential pressure.
Additionally, it allows for dead-ended H2 and O2 feed for the fuel cell,
eliminating parasitic pumping losses required for water removal. Phase I will
demonstrate composite bipolar plate-based fuel cell and electrolyzers, and
quantify the composite bipolar plate transport and mechanical properties
required for system design. In Phase II a full unitized composite bipolar plate
stack would be designed and built to size according to NASA requirements.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
PEM
based electrolyzer/fuel cell systems have the potential of replacing power
systems in many of NASA's current applications, including manned space
applications, high altitude flight, and manned stations on the moon and Mars.
These composite-bipolar-plate-PEM based systems have real systematic advantages
over both traditional PEM and alkaline systems, including integrated cooling and
water management systems; dead-ended fuel cell operation, and elimination of
gas-liquid separation.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential
products foreseen are: the composite bipolar plate PEM electrolyzer; the
composite bipolar plate PEM fuel cell; and closed loop, discrete, and unitized
PEM regenerative fuel cell (RFC) systems. Electrolyzer applications include H2
generation for gas chromatography, industrial uses and hydrogen refueling
stations. PEMFC applications include vehicles and stationary power, where the
internal water management provides a large system advantage. Closed-loop
regenerative fuel cell systems could use a unitized stack which provides the
promise of decreasing stack weight by half for combined PEM fuel cell and
electrolyzer systems. A composite bipolar plate greatly simplifies water
management for a unitized stack by managing water completely in the vapor phase.
Industrial applications include power back-up for computer and energy related
systems.
TECHNOLOGY TAXONOMY MAPPING
Composites
Liquid-Liquid
Interfaces
Energy Storage
| PROPOSAL NUMBER: | 06-I X8.03-9877 |
| SUBTOPIC TITLE: | Space Rated Batteries and Fuel Cells for Surface Systems |
| PROPOSAL TITLE: | Control of Internal and External Short Circuits in Lithium Ion and Lithium Batteries |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Giner Inc
89 Rumford
Avenue
Newton, MA 02466-1311
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Robert McDonald
rmcdonald@ginerinc.com
89 Rumford Avenue
Newton, MA 02466-1311
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has identified needs for
compact high-energy-density primary and secondary batteries. Lithium and Lithium
Ion cells, respectively, are meeting these needs for both manned and unmanned
needs. The high power available in some of these cell chemistries can cause
substantial internal heating in the event of sustained internal and external
heating. At sufficiently elevated temperatures, cell components can react
energetically causing cell case rupture, and in some cases, fire. The proposed
will develop and demonstrate an internal means of controlling short circuit,
which is chemically and electrochemically compatible with the cell's active
materials. Using suitable controls, safe handling of an external short circuit
will be demonstrated in small cells.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed technology will offer a substantial improvement in system and personnel
safety on NASA mission where high-energy-density lithium primary and lithium ion
secondary batteries are required for mission success. GI will work with
companies who current manufacture these cells for NASA so that the proposed idea
can be efficiently and cost-effectively incorporated. Lithium and lithium ion
cells are important sources of compact, reliable power for extravehicular
activities (e.g., lighting) and manned planetary and lunar exploration.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Primary lithium
batteries, like the Lithium/Thionyl Chloride and Lithium/Iodine cells, have
found important use for implantable medical devices including neurostimulators,
defibrillators, and drug-delivery systems. Primary lithiums are also used in
Manpack military power and in aviation for emergency locator beacons. Primary
lithium cells provide high cell voltage (3 Volts) and much longer operating time
than conventional primary cells. Lithium Ion rechargeable cells are used in a
rapidly expanding market for laptop computers, cell phones, power tools and
other portable communication and entertainment devices for the consumer. In all
cases, there is the risk that physical abuse, excessive heating or manufacturing
defects could result in a sustained short circuit, leading to cell thermal
runaway and cell venting. GI will work with selected battery manufacturers of
these consumer, medical and industrial batteries to incorporate the proposed
concept for greatly improved user and system safety.
TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and
Safety
Ultra-High Density/Low Power
Pilot Support
Systems
Composites
Energy Storage
| PROPOSAL NUMBER: | 06-I X9.01-8488 |
| SUBTOPIC TITLE: | Long Term Cryogenic Propellant Storage, Management, and Acquisition |
| PROPOSAL TITLE: | Integrated MLI: Advanced Thermal Insulation using Micro-molding Technology |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Quest Product Development Corporation
4975
Miller Street
Wheat Ridge, CO 80033-2215
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Scott Dye
sdye@quest-corp.com
4975 Miller Street
Wheat Ridge, CO 80033-2215
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Current Multilayer Insulation
(MLI) technology is over 50 years old, and is typically comprised of 10 to 120
layers of metalized polymer films separated by polyester netting. MLI is the
best thermal insulation in a vacuum, and is the insulation of choice for
spacecraft and cryogenic system insulation, but has problems relating to density
control and performance, application labor, and difficulty covering small and
large scales. An innovative concept for improved cryogenic insulation,
Integrated MLI, is proposed based on a micro-machined or micro-molded
substructure. Thermal conductivity will be lower than conventional MLI, layers
would be inherently attached to each other and support one another, construction
would be easier, and the vacuum shell could be supported by the IMLI, greatly
reducing the mass of the insulation system with vacuum shells used to insulate
cryogenic dewars or tanks. An improved insulation should provide lower thermal
conductivity, lower specific thermal conductivity, vacuum compatibility, layers
inherently attached to each other that support themselves, efficient assembly
and provide structural reliability. Recent advances in injection molding has
resulted in the ability to mold structures with very small features, comprised
of materials with low thermal conductivity and low outgassing. Integrated MLI
will consist of small micro-machined or micro-molded structures that support
radiation barrier layers, and will offer significant advantages. Preliminary
analysis of several potential designs indicates IMLI has a theoretical thermal
conductivity less than half that of MLI, allowing improved long term cryogenic
propellant storage and spacecraft thermal performance. It may provide improved
structural assembly, strength and integrity over current MLI. This proposal is
to work on the design, material selection, assembly processes and preliminary
physical property testing of a prototype of this innovative new thermal
insulation.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Integrated MLI might provide improved thermal performance and have
improved structural integrity for spacecraft cryogenic propellant storage and
thermal insulation. Other standard spacecraft insulation uses, such as
insulating instruments, or insulating and preserving liquid hydrogen or liquid
oxygen cryogenic systems and dewars, might also be well served by IMLI. IMLI
could provide the cryogenic insulation and vacuum shell used to insulation and
maintain cryogenics on space instruments, satellites, CEV/CLV spacecraft cabins
and lunar surface habitats. It may be able to provide substantially longer term
cryogenic storage, helping enable longer term manned space flights. Low mass,
low thermal conductance cryotank structural systems are of interest to NASA.
IMLI may have excellent properties required for spacecraft use; low thermal
conductance, vacuum compatibility of materials, inherent control of layer
dimensions and density, self-supporting layers with a post-and-beam
substructure, ease of assembly for small and large areas, potential for both
tight seams and material flexibility.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Extremely
efficient thermal insulation, easily assembled and applied to cover various
surfaces, would have utility in commercial cryogenic applications such as
cryogenic vessels and pipes in scientific and industrial applications. A major
use would be insulating dewars for liquid nitrogen, liquid helium, liquid
oxygen, etc., which are widely found in research and industrial uses. Other
potential applications include large commercial tanks, industrial boilers and
industrial hot and cold process equipment, refrigerated trucks and trailers,
insulated tank, container and rail cars, liquid hydrogen fueled aircraft or fuel
cells, appliances such as refrigerators and freezers, hot water heaters, Thermos
type liquid containers, picnic and mobile containers to keep foods hot or cold,
marine refrigeration, potentially even house structures.
TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Thermal
Insulating Materials
Fluid Storage and Handling
| PROPOSAL NUMBER: | 06-I X9.01-8756 |
| SUBTOPIC TITLE: | Long Term Cryogenic Propellant Storage, Management, and Acquisition |
| PROPOSAL TITLE: | Lightweight aerogel structural and insulation materials |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Aspen Aerogels, Inc.
30 Forbes
Road
Northborough, MA 01532-2501
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Wendell Rhine
wrhine@aerogel.com
30 Forbes Road, Building B
Northborough, MA
01532-2501
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Exploration Systems
architecture presents some propulsion challenges that require new technologies
to be developed. To solve these challenges, NASA needs new technologies for long
term cryogenic propellant storage, management and acquisition applications
in-space as well as on the lunar surface. These technologies will impact
cryogenic systems for space transportation orbit transfer vehicles, space power
systems, spaceports, spacesuits, lunar habitation systems, robotics, and in situ
propellant systems. The sizes of these systems range from the small (< 20 m3
for supercritical air and payload cooling) to very large (> 3400 m3 for LOX
and LH2 propellant storage). Advanced materials are needed to help solve the
unique requirements of these small to very large storage systems. Thus, this
SBIR project will focus on improving the strength of aerogels which are the
lightest weight and best insulation material known. Improvements in the strength
of aerogels would allow these materials to be used as advanced insulation
materials capable of retaining structural integrity while accommodating large
operating temperatures ranging from cryogenic to elevated temperatures. The
properties of the aerogels will be tailored by controlling their densities and
strengthened by reinforcing them with fibers and modifying the aerogel framework
with organic crosslinking agents.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
aerogel-based materials will have applications as cryogenic insulation and as
lightweight structural components for composite cryogenic tanks.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The aerogels
developed in this project would find applications as the insulation used for LNG
storage containers as well as for other cryogenic fluids. Lightweight structural
aerogels would find applications as a component of composite sandwich panels
that are both lightweight and insulating. Such panels could find many
applications including uses in energy efficient buildings.
TECHNOLOGY TAXONOMY MAPPING
Thermal Insulating Materials
| PROPOSAL NUMBER: | 06-I X9.01-9928 |
| SUBTOPIC TITLE: | Long Term Cryogenic Propellant Storage, Management, and Acquisition |
| PROPOSAL TITLE: | High Efficiency Regenerative Helium Compressor |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Advanced Mechanical Technology Inc
176
Waltham St
Watertown, MA 02472-4809
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Charles Hannon
chuckh@amtimail.com
176 Waltham St
Watertown, MA 02472-4809
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Helium plays several critical
rolls in spacecraft propulsion. High pressure helium is commonly used to
pressurize propellant fuel tanks. Helium cryocoolers can be used to sub-cool and
thereby densify cryogenic propellants such as liquid hydrogen (LH2) and liquid
oxygen (LO2). The use of densified cryogenic propellants can reduce the gross
payload weight of a launch vehicle by up to 20%, or increase payload capability.
Helium compressors are critical components for cryogenic propellant storage and
distribution systems, whether used in cryocoolers for densification or to
compress gaseous helium for propellant pressurization. Regenerative compressor
technology can serve high head, low flow helium pressurization applications in a
compact form with high reliability. Pressure ratios on the order of 3:1 per
impeller-stage are commercially available. Non-lubricated gas-bearing supported
prototypes have been successfully demonstrated. However, even state-of-the-art
prototype regenerative compressors are limited to efficiencies of about 55%.
This was achieved using aerodynamic rotor blades rather than the straight radial
blades previously used. Commercially available regenerative compressors with
straight vaned rotors operate at much lower efficiency. An innovation is
proposed that promises to improve the efficiency of regenerative compressors
well beyond the current state of the art.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Potential NASA related applications for a high efficiency
regenerative compressor include propellant management in space, in-situ resource
recovery from the lunar or Martian surface, and as a component in high
efficiency cryocoolers in space. Successful development of a high efficiency
regenerative compressor will enable development of high efficiency DC flow and
hybrid cryocooler cycles that will eliminate the need for large-scale cryogen
storage for cooling of electronics and optics in space. A regenerative
compressor is ideally employed in and low specific speed gas compression
application (high head, low flow).
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There is
current commercial interest in using regenerative compressors to pressurize
natural gas fuel to micro-turbine power generators (terrestrial). Closed cycle
cryocoolers are beginning to replace stored liquid helium to cool MRI and NMR
magnets. The efficiency of AC flow cryocoolers currently used is low. A high
efficiency, high head helium compressor will enable development of highly
efficient compact DC flow cryocoolers for this and other terrestrial
applications. The compressor innovation is also applicable to regenerative pumps
and blowers which find widespread industrial use.
TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Feed System
Components
Fluid Storage and Handling
In-situ Resource
Utilization
Superconductors and Magnetic
| PROPOSAL NUMBER: | 06-I X9.01-9950 |
| SUBTOPIC TITLE: | Long Term Cryogenic Propellant Storage, Management, and Acquisition |
| PROPOSAL TITLE: | Advanced insulation Materials for Cryogenic Propellant Storage Applications |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Advanced Materials Technology, Inc
9324
Mandrake Ct
Tampa, FL 33647-3289
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Akbar Fard
AdvancedMaterialsTech@gmail.com
9324 Mandrake Ct
Tampa, FL
33647-3289
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Materials Technology,
Inc (AMTI) responds to the Topic X9 entitled "Propulsion and Propellant Storage"
under subtopic X9.01, "Long Term Cryogenic Propellant Storage, Management, and
Acquisition". The proposed program will focus on developing new multifunctional
insulation materials that will impact cryogenic systems for space transportation
orbit transfer vehicles, space power systems, spaceports, spacesuits, lunar
habitation systems, robotics, and in situ propellant systems. These innovative
materials will be capable of retaining structural integrity while accommodating
large operating temperatures ranging from cryogenic to elevated temperatures
conditions. These advanced materials can be incorporated into thermal protection
systems (TPS), reducing the amount of TPS and its structure. To meet and exceed
the NASA's requirements, we propose to develop multifunctional organic/inorganic
nanocomposites foams for structural and insulation applications offering
affordable cost, lightweight, and high strength, low thermal conductivity, high
thermal stability, and easy processability which will result in improved
efficiency and reliability of the cryogenic systems. The approach proposed in
this program will provide with more flexibility in designing cryogenic
insulators. Once the feasibility of the concept of strong, lightweight cryogenic
insulating materials is demonstrated in Phase I, we shall scale-up this concept
in a Phase II program to meet the NASA's requirements.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Foamed
organic-inorganic materials will be a new generation of advanced foams. It will
provide to the NASA exceptional resistance to temperature changes, maintaining
property stability from –250 C to more than +400 C and is non-flammable and non
toxic compared to normal insulation products like fiberglass, polyurethane, and
polystyrene The technology proposed in this program will help the NASA to reduce
the cost of space flight. Our materials will provide the NASA with robust
cryogenic solutions and, therefore, will significantly decrease space mission
failures. These materials will benefit NASA's programs, namely, the X-33 and
Reusable Launch Vehicle (RLV) programs.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The innovative
foamed organic-inorganic materials can be used in a variety of commercial
applications. These materials are expected to outperform polyimide foams in
structural and insulation including shipbuilding, aircraft, and medical
prosthetics. A major difficulty in the commercialization of polyimide
nanocomposite is that the raw materials are still very expensive. The potential
applications for the materials developed under this program: include (i) Flame
retardant and fire protection. (ii) Thermal insulation, (iii) Acoustic
insulation, (iv) Weight reduction, (v) Gaskets and seals, (vi) Vibration damping
pads, (vii) Spacers in adhesives and sealant, (viii) Extenders, (ix)
Flow/leveling aids.
TECHNOLOGY TAXONOMY MAPPING
Thermal Insulating Materials
Fluid
Storage and Handling
Composites
Organics/Bio-Materials
| PROPOSAL NUMBER: | 06-I X9.02-8357 |
| SUBTOPIC TITLE: | Innovative Booster Engine Manufacturing, Components, and Health Management |
| PROPOSAL TITLE: | Maturation of Structural Health Management Systems for Solid Rocket Motors |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Acellent Technologies, Inc.
155 C-3 Moffett
Park Drive
Sunnyvale, CA 94089-2108
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Amrita Kumar
akumar@acellent.com
155 C-3 Moffett Park Drive
Sunnyvale, CA
94089-2108
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Solid rocket motor cases are
subject to a variety of external environmental and loading conditions from
cradle-to-grave. These conditions can significantly impact the performance and
decrease safety of the rocket motor. Fueling of the rocket motor adds an
additional complexity in that inspection of the interior becomes impossible
while creating the possibility of disbonds between the case and fuel. These
factors can have potentially catastrophic consequences for the space vehicle
performance. Acellent Technologies is currently developing structural health
monitoring systems to address this issue. The TRL at completion of the current
technology development is anticipated to be TRL 5-6. The proposed program
focuses on maturing the technology to a TRL level 7 for implementation on
existing and future space transportation vehicles. The development will be
conducted in close collaboration with ATK-Thiokol who fully support the
developmental and commercialization efforts.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Next
Generation Space Vehicles architecture definitions will require built-in damage
monitoring tools such as those based on the proposed system. Structural
integrity determination of critical components of a reusable launch vehicle such
as impact damage monitoring for solid rocket motors can be extremely important
especially during ascent, in-orbit and re-entry. Unforeseen impact events during
this time can cause damage that if not monitored can lead to catastrophic
failure of the vehicle. Since nearly all next generation launch vehicle
structures will require some form of inspection and maintenance procedures to
monitor their integrity and health condition during pre-launch, during space
operations and post-flight, the potential applications of the proposed system
are very broad. In the future, this system can potentially be used to monitor
all major structural components of launch vehicles.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The system to
be developed under the present proposal offers the potential to provide a
complete solution for a wide range of structural analysis, evaluation, and
maintenance requirements and enable a number of high value economic benefits to
the aircraft, missile and spacecraft industries. The largest and nearest-term
impact areas for the technology are critical but inaccessible areas on
structures. The system can potentially be used for applications ranging from
aircraft (to monitor impacts on door surrounds, fuselage, wings etc. )to
automobiles (crash sensing) and monitoring of bridges and buildings.
TECHNOLOGY TAXONOMY MAPPING
Launch Assist (Electromagnetic, Hot Gas
and Pneumatic)
Propellant Storage
Launch and Flight Vehicle
Testing
Facilities
Spaceport Infrastructure and Safety
Reuseable
Thermal
Insulating Materials
Tankage
Airport Infrastructure and
Safety
Autonomous Reasoning/Artificial Intelligence
Sensor
Webs/Distributed Sensors
Composites
Metallics
Multifunctional/Smart
Materials
| PROPOSAL NUMBER: | 06-I X9.02-8412 |
| SUBTOPIC TITLE: | Innovative Booster Engine Manufacturing, Components, and Health Management |
| PROPOSAL TITLE: | Friction Stir Processing of Cast Superalloys |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Transition45 Technologies, Inc.
1963 North
Main Street
Orange, CA 92865-4101
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Edward Chen
transition45@sbcglobal.net
1963 North Main Street
Orange, CA
92865-4101
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR Phase I effort
examines the feasibility of an innovative fabrication technology incorporating
sand casting and friction stir processing (FSP) for producing affordable near
net shape components made from high performance Ni-based superalloys. Sand
casting is a relatively inexpensive casting method not traditionally used to
manufacture superalloy castings. Instead of invested ceramic shells, the molds
are produced from a mixture of fine sand and/or rammed graphite powder. Friction
stir processing is an emerging microstructural modification technique based on
friction stir welding (FSW). It can be applied to enhance the
microstructure-properties of the cast material thus improve the damage tolerance
capabilities. This step is needed to allow cast superalloy rocket propulsion
components to be used without a casting factor.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced
superalloy castings can be used for rocket and air propulsion applications.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential
non-NASA commercial applications include components for land-based gas turbines
and petrochemical pumps and valves.
TECHNOLOGY TAXONOMY MAPPING
Beamed Energy
Chemical
High
Energy Propellents (Recombinant Energy & Metallic Hydrogen)
Launch Assist
(Electromagnetic, Hot Gas and Pneumatic)
Monopropellants
Nuclear (Adv
Fission, Fusion, Anti-Matter, Exotic Nuclear)
Propellant
Storage
Airframe
Launch and Flight
Vehicle
Cooling
Reuseable
Thermal Insulating Materials
Structural
Modeling and Tools
Fluid Storage and
Handling
Ceramics
Metallics
Aircraft Engines
| PROPOSAL NUMBER: | 06-I X9.02-9519 |
| SUBTOPIC TITLE: | Innovative Booster Engine Manufacturing, Components, and Health Management |
| PROPOSAL TITLE: | Advanced Numerical Tools For Design And Analysis Of In-Space, Valve And Feed Systems |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Combustion Research and Flow Technology
6210 Keller's Church Road
Pipersville, PA 18947-1020
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Ashvin Hosangadi
hosangad@craft-tech.com
6210 Keller's Church Road
Pipersville,
PA 18947-1020
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In-space valves for the main
fuel and oxidizer feed systems are required to provide precise control, wide
throttling range and handle rapid on-off control. These design requirements
result in significant unsteady, transient effects both on the fluid mass flow
rate, as well as the torque required from the actuators controlling the valve.
However, there currently are no fundamental analytical or numerical modeling
tools that can predict the unsteady/transient performance of these valves;
current design tools are limited to quasi-steady models and empirical
correlations. The innovation proposed here is a high-fidelity, comprehensive
numerical tool that can characterize the transient performance of these flight
valves and provide design support. Geometry complexity and numerical accuracy
problems associated with resolving valve configurations with moving surfaces are
addressed via a grid adaption strategy within an unstructured framework.
Unsteady effects due to both turbulence interactions as well as multi-phase
cavitation are addressed with advanced numerical framework that incorporates
both real-fluid thermodynamics for cryogens as well as advanced LES models for
unsteady turbulence modeling. The tools and technology developed here would
directly impact design support efforts for the J-2X upper-stage engine in the
Ares 1 launcher envisioned under the Constellation program for the mission to
the moon.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
end-product will be a high-fidelity, numerical simulation software (CRUNCH
CFD<SUP>REG</SUP> code) that would predict the transient performance
of flight valve configurations , provide design support by supplementing current
empirical rules, and diagnose system anomalies. Our product addresses core needs
of NASA in the Constellation program, and the mission to the moon, for reliable
and well-validated computational tools that can provide accurate simulations of
performance in an accurate and efficient manner to be useful within a design
cycle timeline. The technology developed here would directly impact analysis of
the valves and the feed systems to be designed for the upper-stage J-2X feed
system in the Ares 1 launcher by providing the transient mass flow through the
valve, unsteady torque loads on the actuator controlling the valve, as well
diagnosing the potential for damaging water-hammer as well as multi-phase
cavitation effects that may result during rapid on-off control.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial
market for our product is very large and includes the broad market of rapid
response control valves in industries such as nuclear power generation, chemical
process plants, and hazardous waste facilities among others where the transient
performance characterization of valves play a vital safety role. In addition to
these traditional markets, commercial space ventures ranging from space
transportation systems (COTS) for the international space station (ISS), to
low-cost satellite launch systems are getting an infusion of venture capital and
would be receptive to accurate simulation tools. The primary market for this
product will be in the design and analysis of high-performance, high-reliability
valves used for inherently transient operations in the nuclear and chemical
process industry. Here characterizing the transient performance is a critical
safety issue and the availability of a well-validated, reliable computational
tool can play a key role in the design process for these critical elements.
TECHNOLOGY TAXONOMY MAPPING
Chemical
Simulation Modeling
Environment
Feed System Components
Fluid Storage and Handling
Power
Management and Distribution
| PROPOSAL NUMBER: | 06-I X9.03-8629 |
| SUBTOPIC TITLE: | Cryogenic and Non-Toxic Storable Propellant Space Engines |
| PROPOSAL TITLE: | Physical Improvements in Exciter/Igniter Units |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Alphaport, Inc.
6002 Fleet
Avenue
Cleveland, OH 44105-3408
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Tony Johnson
tjohnson@weltech.us
6002 Fleet Avenue
Cleveland, OH 44105-3408
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed project consists
of developing a prototype exciter/igniter unit that can operate to a subset of
expected flight performance requirements. The main focus of this development
effort will be the physical integration of a small, compact exciter with a
"flight like" igniter or spark plug. This exciter/igniter prototype will
represent the exciter/igniter units used to generate sparks that ignite fuels in
engines and propulsion systems. The development of this prototype unit will
follow a phased approach covering design, development, analysis, assembly, test
and verification. This prototype will represent a "stand alone" integrated unit
capable of providing ionizing voltage greater than 20 kV for a spark energy of
45 to 50 mJ at a rate of 200-300 sparks per second. The proposed prototype will
integrate both the exciter electronics and an igniter (spark plug) to
demonstrate "end-to-end" functionality. Additionally, the integrated unit will
be as compact as possible. The implications of the proposed project are for
space and weight savings in the overall development of green propulsion systems
as applicable to research projects in Exploration Systems and specifically
applicable to Topic X9 Propulsion and Propellant Storage.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
potential NASA applications are for the development of fast, high energy spark
exciters and spark plugs required to support any propulsion systems. Further,
potential applications exist for the development of non-toxic (green) propulsion
systems. As a specific example, the proposed exciter can be used to support the
Crew Exploration Vehicle (CEV). The CEV has been proposed with GOX ethanol or
GOX GCH4, both requiring exciter/igniter units that can produce more spark
energy.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential
non-NASA applications are reduced size & weight with improved performance of
automobile, watercraft and aircraft engines. Additionally, applications exist to
support the development of Department of Defense (DoD) propulsion systems.
TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
| PROPOSAL NUMBER: | 06-I X9.03-8824 |
| SUBTOPIC TITLE: | Cryogenic and Non-Toxic Storable Propellant Space Engines |
| PROPOSAL TITLE: | Innovative Swirl Injector for LOX and Hydrocarbon Propellants |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
IN Space, L.L.C.
1220 Potter Dr., Suite
100
West Lafayette, IN 47906-1334
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
B.J. Austin
bjaustin@inspacellc.com
1220 Potter Dr., Suite 100
West
Lafayette, IN 47906-1334
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Gases trapped in the
propellant feed lines of space-based rocket engines due to cryogenic propellant
boil-off or pressurant ingestion can result in poor combustion efficiencies,
combustion instabilities, or long startup transients. To assist NASA in the use
of the high performing liquid oxygen propellant combinations in space engines,
IN Space proposes to investigate the feasibility of an innovative swirl injector
design for liquid oxygen and hydrocarbon propellants to achieve high combustion
efficiencies, stable operation, and short and smooth startup transients despite
potential two-phase oxidizer flow. Additionally anticipated benefits of the
injector include low inert mass and low manufacturing costs. IN Space plans to
carry out the feasibility assessment of the injector design by conducting broad
parametric test fire evaluations of a notional LOX/hydrocarbon workhorse
thruster based on present NASA needs to assess the effects of several design
considerations on the combustion efficiency, static combustion stability, and
startup transient duration performance merits. A preliminary flightweight
injector design will also be generated in order to compare the estimated
injector mass with similar injector designs.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA
space-based propulsion systems deriving the most benefit from the innovative
swirl injector characteristics are LOX/hydrocarbon engines that may experience
significant LOX boil-off due to long periods of inactivity or thermal soak-back.
These engines include reaction/attitude control systems onboard crew vehicles or
science probes and deceleration/orbital insertion engines on science probes.
Other space engines benefiting from the high performance and stable operation
injector features are satellite apogee boost/orbital transfer engines, earth
departure stages for scientific payloads, and as the turbopump gas generator
powering booster engines of the same propellants.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Additional
applications of innovative swirl injector design-based thrusters include serving
as the turbopump gas generator for U.S. Air Force and space tourism/low cost
space access LOX/hydrocarbon booster engines currently of interest for several
different payload types, apogee boost/orbital transfer engines on satellites,
and reaction control systems onboard civilian suborbital vehicles using
LOX/hydrocarbon propellants for the main engine.
TECHNOLOGY TAXONOMY MAPPING
Chemical
| PROPOSAL NUMBER: | 06-I X9.03-8904 |
| SUBTOPIC TITLE: | Cryogenic and Non-Toxic Storable Propellant Space Engines |
| PROPOSAL TITLE: | Transpiration Cooled Thrust Chamber Technology |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
WASK Engineering, Inc.
4120 Cameron Park
Drive, Suite 303
Cameron Park, CA 95682-7213
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Paul Phillipsen
paulp@waskengr.com
4120 Cameron Park Drive, Suite 303
Cameron
Park, CA 95682-7213
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has determined that it
requires extremely durable, high-performance, low cost engines to meet future
multi-use in-space, non-toxic, cryogenic propulsion requirements such as orbit
transfer, descent, ascent and pulsing attitude control. Transpiration-cooling
technology has long been considered a candidate for long-life thrust chambers
but has never been deployed on a domestic rocket engine. In this program WASK
Engineering, Inc. demonstrates methane transpiration cooling of an
oxygen/methane thrust chamber at 260 psia chamber pressure and a range of
mixture ratios up to 3.2 O/F in a 65 lbf engine assembly. Key tasks are the
design and fabrication of a transpiration-cooled chamber spool section that
integrates into existing hardware from an on-going USAF program and then hot
fire testing it in the existing test stand. Post-test data analyses are used to
anchor and refine thermal and performance algorithms in transpiration cooling
models that then validate, or invalidate, transpiration cooled thrust chambers
for this set of requirements.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150
WORDS)
Extremely durable, high-performance, low cost engines to meet
future multi-use in-space, non-toxic, cryogenic propulsion requirements such as
orbit transfer, descent, ascent and especially pulsing attitude control.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial
space tourism missions (both axial and RCS engines), multiple USAF reusable
propulsion applications, actively-cooled aero-shell and leading edge
applications, and commercial heat-transfer both for cooling electronics and in
process control applications.
TECHNOLOGY TAXONOMY MAPPING
Chemical
Cooling
| PROPOSAL NUMBER: | 06-I X9.04-9251 |
| SUBTOPIC TITLE: | Nuclear Thermal Propulsion |
| PROPOSAL TITLE: | Improved CVD coatings for NTP Fuel Elements |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
CERAMIC COMPOSITES, INC.
133 Defense
Highway, Suite 212
Annapolis, MD 21401-8907
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Steven Seghi
steve@techassess.com
133 Defense Highway, Suite 212
Annapolis,
MD 21401-8907
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
One of the great hurdles to
further development and evaluation of nuclear thermal propulsion systems is the
issue surrounding the release of radioactive material from the fuel during
ground testing and its subsequent impact on test facility siting and operation.
Therefore, the development of a crack resistant coating system on fuel elements
nuclear thermal propulsion that is insensitive to hydrogen corrosion and erosion
is considered enabling. Ceramic Composites Inc. (CCI) proposes a systematic
approach for CVD deposition and evaluation of a family of zirconium carbide
(ZrC) and niobium carbide (NbC) coating systems for both uranium
carbide-zirconium carbide solid solution [(U,Zr)C]-graphite composite fuel
elements and advanced triple carbide (uranium carbide-ziconium carbide-niobium
carbide) solid fuel elements designed for use in space nuclear power and
propulsion reactors. These refractory metal coating systems will be evaluated in
high temperature hydrogen in concert with a preliminary performance modeling
effort.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
development of a high quality coating for space nuclear reactors will be
enabling for the development of nuclear thermal propulsion (NTP), in particular
if one uses fuel elements based on the Rover/NERVA heritage design or the Pebble
Bed design. The higher specific impulses afforded by NTP will provide
significantly shorter travel times to the moon and Mars, reducing the time in
zero gravity for manned missions and greatly increasing the speed of
cargo/supply deliveries and unmanned exploration missions.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development
of a high quality coating for space nuclear reactor fuel elements could have
potential across a variety of nuclear applications. A variety of designs exist
for the next generation nuclear power plant, such as the Gas Cooled Fast Reactor
(GCFR) and the Very High Temperature Reactor (VHTR). In the case of both of
these the final fuel form has not been decided. The triso fuel particle has been
suggested for both as well as clad solid fuel pins. Either of these two fuel
forms could benefit from an improved fuel coating of this type. The idea of
using mixed carbides (U,Zr)C, (U,Nb)C, which would allow for much higher
operating temperatures, for both pellets and solid fuel pins has been put forth
and both would require a cladding material. Most of these systems will operate
above the temperature limit of SiC or would have compatibility issues with the
standard C/C/SiC/C (triso) coating developed for pebble type fuel. The case of
the VHTR the reactor has the ability to generate hydrogen by splitting water
molecules, the presence of hydrogen and oxygen pose serious problems for the
triso coating.
TECHNOLOGY TAXONOMY MAPPING
Nuclear (Adv Fission, Fusion,
Anti-Matter, Exotic Nuclear)
Ceramics
| PROPOSAL NUMBER: | 06-I X10.01-8793 |
| SUBTOPIC TITLE: | Ablative Thermal Protection System for CEV |
| PROPOSAL TITLE: | Low Intrusive Fiber Optic-Plug for TPS Materials |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
ElectroDynamic Applications, Inc.
P.O. Box
131460
Ann Arbor, MI 48113-1460
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Timothy Smith
timsmith@edapplications.com
P.O. Box 131460
Ann Arbor, MI
48113-1460
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Heat shield technology is a
critical component of manned spaceflight. In particular, the new Crew
Exploration Vehicle (CEV) requires thermal protection systems (TPS) beyond the
current state of the art. While new TPS shields are under development, a key
difficulty is the ability to diagnose TPS performance. Technology demonstrator
missions are being planned, but designing instrumentation capable of surviving
the reentry environment is a non-trivial challenge. We propose the development
of a low intrusive fiber optic plug insert for TPS materials that will enable
spectrographic measurements of the reentry environment surrounding an ablating
TPS. This would provide benchmark data for fundamental flow, radiation, and
materials modeling as well as provide operational correlations between vehicle
reentry drag and radiation if implemented in a TPS flight test. In addition to
spectrographic data, the proposed technology will also intrinsically provide a
highly reliable measurement of TPS ablation rates. These fiber-optic plug
inserts provide an enabling capability for reentry spacecraft development. The
program proposed here will take the concept, originally encouraged at the
request of researchers at NASA Ames, from concept to demonstration, through
prototype, to a technology readiness level suitable for inclusion in the design
of an ablation shield flight demonstrator mission.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
system proposed here will provide an enabling diagnostic capability for NASA
programs developing Thermal Protection Systems. Potential applications include
development for the CEV TPS, and any other NASA program requiring an entry,
re-entry, aero braking, or other TPS technology. In addition, this device will
allow placement of spectrometers onboard spacecraft where previously there was a
concern due to the requirement of a conventional sapphire window. As such, it
will enable scientific uses of spectrographic data, including measurement of
planetary atmospheric constitution during landing.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are
potential applications to DoD program in systems involving hypersonics as well
as various reentry vehicle applications. In addition there are potential
applications in terrestrial high energy plasmas where the abilities to survive
extreme environments and to place multiple sensors quickly and flexibly within a
system are of value.
TECHNOLOGY TAXONOMY MAPPING
Ablatives
Control
Instrumentation
Testing Facilities
Thermal Insulating
Materials
Optical
High-Energy
Aerobrake
| PROPOSAL NUMBER: | 06-I X10.01-9224 |
| SUBTOPIC TITLE: | Ablative Thermal Protection System for CEV |
| PROPOSAL TITLE: | High specific-strength C-Zr(O)C / C-ablator TPS for CEV |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
MATECH Advanced Materials
31304 Via
Colinas, Suite 102
Westlake Village, CA 91362-4586
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
HeeMann Yun
heemann@matechgsm.com
31304 Via Colinas, Suite 102
Westlake
Village, CA 91362-4586
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase I NASA SBIR
Proposal seeks to demonstrate a new zero-erosion ablative thermal protection
system (TPS) technology that is based upon an ultra-high temperature (UHT)
ceramic fiber pre-form / organic ablative matrix composite structure. In this
TPS material concept, the "char" phase is pre-engineered UHT zirconium carbide
(Zr(O)C) ceramic fiber pre-forms, which have dual functions of high compressive
strength of ligaments and non-recession of fiber components after matrix
ablation. To increase the pre-form ligament strength and stiffness, Zr(O)C fiber
reinforcements will be combined with the high-modulus carbon fibers. MG's
ablative TPS are designed to retain their shape in extreme environments, thereby
reducing the thickness requirement and lowering the TPS total mass, which will
be crucial at high re-entry velocity. MG's new ablator slowly absorbs high
levels of energy when ablated at higher temperatures. The ablative carbonaceous
phase has been identified by the use of a melamine-formaldehyde and/or
polyethylene polymer resin. This selection was based upon its high heat of
volatilization and decomposition. At the completion of the Phase I and Phase II
program, MG will have fabricated a high specific strength C-Zr(O)C / C-ablator
and have demonstrated an completely integrated 5'x5' size TPS with attachment
features, operational at > 6000oF.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
CEV
thermal protection systems, Space transportation vehicle thermal insulation and
propulsion insulation systems, Hypersonic vehicle and propulsion insulation
systems
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
DoD missile
thrusters, Missile hot control-structure insulations, refractory-carbide fibers
as a new type of insulation and CMC reinforcements for DOE, DoT, EPA, and the
private transportation and filter industries
TECHNOLOGY TAXONOMY MAPPING
Ablatives
Thermal Insulating
Materials
Ceramics
Composites
| PROPOSAL NUMBER: | 06-I X11.01-8432 |
| SUBTOPIC TITLE: | Thermal Control for Lunar Surface Systems |
| PROPOSAL TITLE: | Vapor Compressor Driven Hybrid Two-Phase Loop |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Advanced Cooling Technologies, Inc.
1046
New Holland Avenue
Lancaster, PA 17601-5688
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Chanwoo Park
chanwoo.park@1-ACT.com
1046 New Holland Avenue
Lancaster, PA
17601-5688
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation
Research Phase I project will demonstrate a vapor compressor driven hybrid
two-phase loop technology. The hybrid two-phase loop technology incorporates an
advanced evaporator design that is capable of passive separation of liquid and
vapor phases at high heat flux conditions. Combining the hybrid two-phase loop
technology with a vapor compressor increases the technology's operating range.
The integral phase separation feature in the evaporator greatly improves the
vapor compressor performance and reliability by preventing two-phase flows in
the compressor. The proposed technology is particularly suited for the lunar
surface systems where the cooling system size, mass, reliability and operation
under widely varying environmental conditions are critically important.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's
vision of establishing lunar colony requires innovative advances in the thermal
management technology to reject waste heat to much higher heat sink
temperatures. Vapor compressor driven hybrid two-phase loops will provide high
performance refrigeration for lunar surface systems and other NASA planetary
missions where higher heat sink temperature and higher radiator temperature are
required.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA
commercial applications will be the vapor compressor
air-conditioning/refrigeration systems for residential and commercial
applications. High performance electronics cooling and vehicle climate control
where high compression efficiency and high heat flux capability are important.
TECHNOLOGY TAXONOMY MAPPING
Cooling
| PROPOSAL NUMBER: | 06-I X11.01-8656 |
| SUBTOPIC TITLE: | Thermal Control for Lunar Surface Systems |
| PROPOSAL TITLE: | SAFE, NON-CORROSIVE DIELETRIC FLUID FOR STAGNATING RADIATOR THERMAL CONTROL SYSTEM |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Paragon Space Development Corp.
3481 E.
Michigan Street
Tucson, AZ 85714-2221
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Christine Iacomini
ciacomini@paragonsdc.com
3481 E. Michigan Street
Tucson, AZ
85714-2221
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Paragon proposes to develop a
single-loop, non-toxic, stagnating active pumped loop thermal control design for
NASA's Orion or Lunar Surface Access Module (LSAM) program. While this
technology was developed in the Apollo era, it has not been used in space since
then. Furthermore, the fluids used in those first-generation units are not
compatible with today's human-rated flight requirements as they could be
considered toxic and/or flammable. Though work at JSC by Tuan et al. has
targeted modeling and verifying the model of a stagnating radiator with one
candidate fluid, Paragon proposes to parallel this effort with an alternative
fluid as a back-up to that currently base-lined in the Orion program. This
technology will be a significant innovation in that stagnating radiator designs
provide self regulation of thermal dissipation parameters. As heat flow to the
radiator is reduced, less cooling capacity is required; stagnating radiators
incorporate fluids that gradually change properties. If increased heating loads
are encountered, the radiator working fluid changes again to increase the heat
transfer capability of the radiator. This technology is directly relevant to
NASA's Orion and LSAM development. Our plan for Phase I and II is in-line with
bringing this technology from a TRL 2 to a TRL 4-6 depending on Phase II
assumptions.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Assuming
successful implementation of Phase I and II activities, this enabling technology
will be of extreme value to NASA as already demonstrated with the non-human
rated fluid use in the Apollo program. While the applications will most likely
be constrained to space systems, stagnating radiator design systems could enable
many of the next-generation systems that are currently in the conceptual design
phase, to become a reality. Of obvious and primary application are human rated
spacecraft applications such as the Lunar Surface Access Module and the newly
named crew exploration vehicle "Orion". However, the technology can also be
applied to variable power spacecraft applications as well as interplanetary
space vehicles that require reliable, less complex and elegant thermal control
systems.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Assuming
successful implementation of Phase I and II activities, this enabling technology
will also be of extreme value to an emerging commercial space industry. This
includes the following types of spacecraft: High power commercial satellites and
emerging commercial orbital flight vehicles such as Bigelow's space hotels.
TECHNOLOGY TAXONOMY MAPPING
Cooling
| PROPOSAL NUMBER: | 06-I X11.01-9369 |
| SUBTOPIC TITLE: | Thermal Control for Lunar Surface Systems |
| PROPOSAL TITLE: | Lightweight, Flexible, and Freezable Heat Pump/Radiator for EVA Suits |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Creare Inc
P.O. Box 71
Hanover, NH
03755-0071
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Michael Izenson
mgi@creare.com
P.O. Box 71
Hanover, NH 03755-0071
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Manned lunar exploration will
require extravehicular activity (EVA) suits that surpass existing technology. We
propose an innovative thermal control system for EVA suits that uses an
absorption heat pump with a flexible radiator that offers reduced size, lighter
weight, conformability, rugged construction, and freeze tolerance. The heat pump
absorbs a crew member's metabolic heat and rejects it via radiation to the
environment. Innovative materials and construction enable a very lightweight and
flexible system that is rugged and easily repairable. In Phase I we will prove
feasibility by assessing material suitability for lunar operations,
demonstrating the critical fabrication steps for key components, then testing
these components to demonstrate thermal performance. In Phase II we will build,
demonstrate, and deliver a complete prototype heat pump system.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed heat pump radiator can provide thermal control in extravehicular
activity (EVA) suits designed for lunar and Mars exploration, as well as EVA
suits used for zero-gravity operations such as space station or satellite
construction or assembly and maintenance of space-based telescopes. The
absorption heat pump system offers light weight, flexibility and ease of
integration, ruggedness, and freeze tolerance. NASA needs this device for
future, long-duration space exploration missions—such as extended stays on the
moon or Mars—in which in-situ repair is vital and freeze tolerance is required
for operation in extreme thermal environments. The non-venting heat pump system
is also needed for construction of scientific instruments in space that require
a very clean extravehicular environment.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed
heat pump can provide a lightweight, portable cooling unit to wear with sealed
or heavy garments in hazardous environments, such as level A HAZMAT suits needed
for homeland security missions. The absorption cooling process can be used to
provide portable, regenerable refrigeration and air conditioning for recreation,
transportation, and medical applications.
TECHNOLOGY TAXONOMY MAPPING
Portable Life Support
| PROPOSAL NUMBER: | 06-I X11.01-9477 |
| SUBTOPIC TITLE: | Thermal Control for Lunar Surface Systems |
| PROPOSAL TITLE: | Efficient, Long-Life Biocidal Condenser |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
Creare Inc
P.O. Box 71
Hanover, NH
03755-0071
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail,
Mail Address, City/State/ZIP, Phone)
Michael Izenson
mgi@creare.com
P.O. Box 71
Hanover, NH 03755-0071
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Environmental control systems
for manned lunar and planetary bases will require condensing heat exchangers to
control humidity. Condensing surfaces must be hydrophilic to ensure efficient
operation and biocidal to prevent growth of microbes in the moist, condensing
environment. The coatings must be extremely stable and adhere to the condensing
surface for many years. We propose an innovative condenser that will enable
highly efficient heat transfer using an innovative coating that has proven to be
highly biocidal, hydrophilic, and stable. In Phase I we will prove feasibility
by demonstrating the performance of the proposed hydrophilic and biocidal
surface under prototypical conditions. In Phase II we will demonstrate a
full-size, prototype condenser designed to meet the requirements for future
lunar and planetary bases.
POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The
proposed condenser will enable efficient and reliable operation for
environmental control systems in manned lunar and planetary bases as well as
future manned spacecraft. By enabling recovery of water from the base or
spacecraft atmosphere without using consumable absorber materials, the condenser
enables simple operation of the environmental control system with minimal
logistical support. The condenser or the coating alone will be useful for future
upgrades of the environmental control system on the International Space Station,
which has experienced degraded operation due to failure of hydrophilic coatings
on condensing heat exchangers.
POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Efficient,
reliable condensers will be needed for fuel cell generators or fuel reforming
systems for portable electric power generation or on-board vehicular fuel cells
or reformers. These condensers are required for water-neutral operation, and
hydrophilic and biocidal surfaces are needed for long-term reliability of the
system. Efficient condensation is required to minimize parasitic power loss for
water recovery. The condenser developed in the proposed program will be ideal
for these applications.
TECHNOLOGY TAXONOMY MAPPING
Cooling
Air Revitalization and
Conditioning
| PROPOSAL NUMBER: | 06-I X12.01-8932 |
| SUBTOPIC TITLE: | Food Access Beyond Low Earth Orbit |
| PROPOSAL TITLE: | Biodegradable Long Shelf Life Food Packaging Material |
SMALL BUSINESS CONCERN: (Firm Name, Mail Address,
City/State/ZIP, Phone)
SVT Assoc
7620 Executive Dr
Eden
Prairie, MN 55344-3677
PRINCIP