| Proposal Info. |
Abstract |
A1.02-9516 (SBIR 06-2)
Damage Adaptation Using Integrated Structural, Propulsion, and Aerodynamic Control
Barron Associates, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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Over the past decade, researchers have been making great strides in the development of algorithms that detect and compensate for damaged aircraft. Before these algorithms can be used in civil aviation, progress is needed to (a) ensure that these innovative and frequently non-deterministic algorithms will always perform as expected and (b) address challenges associated with integrating these algorithms into an overall avionics system. The authors addressed the second challenge by developing an integration approach called Operational Envelope Safety Assurance (OESA). In Phase I, the authors showed that OESA can integrate control, path planning, diagnostics, and structural health monitoring algorithms in a way that ensures the subsystems will never issue commands that put the aircraft outside its safe-operating envelope. In Phase II, the authors will formalize the approach, develop a general set of OESA subsystem specifications, and demonstrate safe integration of algorithms developed by other researchers under related research efforts. Phase II will culminate in real-time high-fidelity demonstrations of an integrated controller for a NASA testbed (either the Langley AirSTAR GTM or the Dryden A-53 F-18 testbed) and will set the stage for Phase III flight tests.
Technology Areas:
Guidance, Navigation, and Control; On-Board Computing and Data Management
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A1.03-8436 (SBIR 06-2)
Grain Boundary Engineering for Assessing Durability and Aging Issues with Nickel-Based Superalloys
Integran Technologies USA, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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The Grain Boundary Engineering (GBE) approach, successfully demonstrated in Phase I, that microstructural optimization provides a very significant improvement in reducing susceptibility to intergranular crack initiation and growth in conventional wrought Inconel 718.
The principal objective of the Phase II research development program is to extend the applicability of the GBE technology from conventional wrought superalloys to more advanced powder metallurgy (PM) alloys, and in particular, the Low Solvus High Refractory (LSHR) developed by NASA. In addition, the program also includes a limited effort to optimize the GBE process for application to wrought Inconel 718Plus.
The phase II program will build upon the success of the phase I effort, and will have the following specific technical objectives: (1) develop and optimize GBE processing strategies for optimizing the bulk microstructure of an advanced PM disk alloy developed by NASA (i.e., LSHR) and Inconel 718Plus, (2) develop a cost-effective GBE processing strategy for locally optimizing the microstructure of the PM alloy (i.e., LSHR) at the near surface, and (3) evaluate the mechanical properties of the GBE-processed alloys and benchmark with properties of their conventional counterparts.
Technology Areas:
Aircraft Engines; Metallics
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A1.03-8886 (SBIR 06-2)
Cradle-to-Grave Monitoring of Composite Aircraft Structures
NextGen Aeronautics, Inc.
HubZone: No
Women Owned: No
Minority Owned: Yes
Center: LaRC
Proposal Abstract/Firm Contact
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NextGen Aeronautics, after achieving promising results in Phase I, is proposing a simple yet powerful damage identification technique for honeycomb advanced composite structures in Phase II. The proposed Phase II program is focused to achieve at least TRL of 5 and quickly commercialize technology in Phase III. The specific objectives are: 1) Improve Raleigh –Lamb (RL) wave based statistical detection technology; 2) Reduce NDE time by field usable automated data collection; 3) Develop end-to-end system software; 4) Develop detailed early commercialization plan. The Phase II development will provide a significant improvement in functionality of the system and put strong emphasis on process automation. NextGen is pursuing teaming arrangement with Boeing and Northrop Grumman to test the proposed system in realistic environment. During Phase I, the NextGen team established feasibility of the proposed system by evaluating it on a honeycomb plate, a common construction used in many secondary structures of aircraft. NextGen has chosen an outstanding team that has considerable prior experience, an in-depth understanding of damage modes in advanced composite structures, and comprehensive knowledge of damage detection techniques. Our team's combined expertise in health monitoring systems and our relationship with system integrators will ensure near-term technology transition.
Technology Areas:
Composites; Data Acquisition and End-to-End-Management; Integrated Robotic Concepts and Systems; Portable Data Acquisition or Analysis Tools
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A1.06-9659 (SBIR 06-2)
NIR LIDAR for Hazard Mitigation
RL Associates, Inc.
HubZone: No
Women Owned: Yes
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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We have investigated the feasibility of employing a hazard detection and mitigation system based upon a polarization discriminating range-gated Lidar system. This dual use system will be capable of both imaging targets in low visibility scenarios, such as smoke, fog, haze, light rain, and low light levels, and providing an early warning of in-flight hazards, primarily icing conditions in clouds. The polarization discriminating optical system and accompanying image processing software are capable of differentiating highly depolarizing surfaces from those that contribute little to depolarization. Examples of this type of differentiation include water and ice phases in clouds and hard-target surfaces surrounded by an aerosol particulate media. The NIR Lidar system is designed to operate around 1.5 m for maximum eye-safety, even when used from the ground. Major components of the Lidar unit include a laser transmitter, a fast gated detector, and polarization switching components. The performance of this type of system has been demonstrated in the Phase I project in laboratory experiments using custom built rain and fog generating chambers. Both image enhancement of a hard target and detection differing depolarization ratios were demonstrated. Backscattered noise from obscurants is greatly reduced by the fast-gated camera system, and a narrowband optical filter provides additional noise rejection. The NIR Lidar system can be easily integrated with a database of common object types for identification of hard targets, such as obstacles on a runway. Illuminated NIR imagery is ideal for providing images of hard targets, as object detail is very near that seen with a visible camera, unlike FLIR (forward-looking infrared) imagery, and the performance is equivalent in day or night conditions.
Technology Areas:
Guidance, Navigation, and Control; Optical; Photonics; Pilot Support Systems
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A1.07-8798 (SBIR 06-2)
Aircraft Electrical Power System Diagnostics and Health Management
Techno-Sciences, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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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 have demonstrated the approach using simulations and experimental test beds. The successful completion of this phase of the project provided a prototype health monitoring system and established 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. In Phase II, we will develop a diagnostics and prognostics toolbox that will allow the transition of advanced techniques for on-line health monitoring of power system components to operational situations. Outputs from the computational toolbox will be useful for scheduling both routine and preventive maintenance. The developed software and real time implementations will be well suited for packaging and integrating into vehicle health management systems for both military and commercial aircraft.
Technology Areas:
Data Acquisition and End-to-End-Management; Database Development and Interfacing; On-Board Computing and Data Management; Portable Data Acquisition or Analysis Tools; Power Management and Distribution
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A1.07-9512 (SBIR 06-2)
Real-Time Adaptive Algorithms for Flight Control Diagnostics and Prognostics
Barron Associates, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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The overall objective of this research program is to improve the affordability, survivability, and service life of next generation aircraft through the use of ADAPT --- an integrated adaptive diagnostic and prognostic toolbox. The specific focus of the research effort is adaptive diagnostic and prognostic algorithms for systems with slowly-varying dynamics. 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 failures; however, if a static model is used, modeling errors may increase over time, which can adversely affect 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 rendering it undetectable by the diagnostic algorithms. An inherent trade-off exists between accurately tracking normal variations in system dynamics and potentially obscuring slow-onset failures by adapting to failure precursors that would be evident using static models. The proposed ADAPT will feature an innovative new parameter estimation algorithm and new adaptive observer / Kalman filter techniques designed specifically for health monitoring. The research team of Barron Associates, Inc., the University of Virginia, and Lockheed Martin Aeronautics Company will demonstrate ADAPT using a high-fidelity electro-hydrostatic actuator simulation.
Technology Areas:
Autonomous Reasoning/Artificial Intelligence; Expert Systems
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A2.01-9428 (SBIR 06-2)
Ceramic Composite Mechanical Fastener System for High-Temperature Structural Assemblies
Hyper-Therm High-Temperature Composites
HubZone: No
Women Owned: No
Minority Owned: No
Center: NSSC
Proposal Abstract/Firm Contact
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Under Phase I, the feasibility of a novel thermal stress-free ceramic composite mechanical fastener system suitable for assembly of high-temperature composite structures was successfully demonstrated. The innovative 2-dimensional (2D) fastener design facilitates joining load-bearing hot structural assemblies and can be produced at a cost much lower than other competing designs and methods. Functional SiCf/SiCm composite fasteners having two (2) fiber reinforcement orientations of 0/90-degrees (cross-ply) and ±45-degrees (bias-ply) were fabricated for characterization. Testing of the respective fasteners included both axial tension and single-lap shear. The cross-ply reinforced SiCf/SiCm fasteners exhibited axial tensile and single-lap shear strengths of 38.0 and 33.1 ksi, respectively. The bias-ply fasteners exhibited axial tensile and single-lap shear strengths of 31.3 and 29.8 ksi, respectively. Using a generalized analytical method for determining the distribution of forces and stresses in the 2D mechanical fastener developed in Phase I, optimized configurations will be designed and produced in Phase II for evaluation. The metallic subcomponents used for Phase I demonstration will be produced using a high temperature-capable material (e.g., ceramic, superalloy). Aerodynamically smooth Cf/SiCm and SiCf/SiCm composite structural lap joints will be assembled using the optimized composite fastener system for characterization. Testing of the lap joint assemblies will performed to determine the flexibility and structural efficiency of the joint as a function of off-axis loading relative to the principal axis of the fasteners. Elevated temperature testing will be performed to establish the effects of temperature on the mechanical properties of the joint.
Technology Areas:
Ablatives; Aircraft Engines; Airframe; Ceramics; Composites; Launch and Flight Vehicle; Reuseable
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A2.01-9593 (SBIR 06-2)
Space-Qualifiable Cyanate Ester Elastomer
Cornerstone Research Group, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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In Phase 1, CRG demonstrated the feasibility of a novel approach to prepare cyanate ester based elastomers. This approach polymerizes in-situ siloxane within a reactive elastomer precursor matrix in order to achieve an elastomeric material with highly tunable and desired mechanical properties. This methodology shows great potential in materials development for applications such as space deployable structures, space seals, and aeroshells. Using this methodology CRG was able to show that elastomeric cyanate ester materials having a vary broad range of thermal and mechanical properties could be formulated using a relatively small amount of CRG's synthesized monomers and other low-cost, commercially available components, such as low-cost, low molecular weight silicone materials. The cyanate ester elastomer materials exhibited excellent thermal stability, maintaining their elastomeric properties to temperatures below -100 C and as high as 300 C. The proposed Phase 2 effort will leverage Phase 1 results and CRG's other extensive R&D in elastomeric material technologies to bring the methodology to readiness for transition to operational use.
Technology Areas:
Aerobrake; Aircraft Engines; Airframe; Airlocks/Environmental Interfaces; Composites; Inflatable; Kinematic-Deployable; Large Antennas and Telescopes; Multifunctional/Smart Materials; Thermal Insulating Materials
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A2.02-8522 (SBIR 06-2)
A Laser-Based Diagnostic Suite for Hypersonic Test Facilities
Los Gatos Research
HubZone: No
Women Owned: No
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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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 utilize diode laser spectroscopy to determine several critical parameters including gas temperature, velocity, and composition. Moreover, by using both multiple lines-of-sight and multiple wavelengths, the analyzer will also provide a measure of the spatial distribution of these important gas parameters in an engine test facility. The SBIR instrument will be the first system capable of providing real-time, rapid quantification of these important combustion parameters in NASA's hypersonic test facilities. Such quantification is essential to the development of improved reactive CFD models and subsequent hypersonic propulsion systems for future aerospace vehicles.
Technology Areas:
Aircraft Engines; Fundamental Propulsion Physics; Optical; Testing Facilities
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A2.02-9540 (SBIR 06-2)
A Renewed Approach for Large Eddy Simulation of Complex Geometries
Flow Parametrics, LLC
HubZone: No
Women Owned: No
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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The potential benefits of Large Eddy Simulation (LES) for aerodynamics and combustion simulation hvae largely been missed, due to the complexity of generating grids for complex topologies, and the requirement for boundary fitted grids which reduce the accuracy of the method. The Phase 2 Program builds on the Cartesian grid LES flow solver developed under Phase 1, and includes new techologies such as immersed boundary conditions, multigrid code acceleration, compressibility, and advanced subgrid scale models for turbulence and combustion. Experimental validation cases using NASA-sponsored experiments, and using actual aeroengine combustor hardware will be performed, comparing the LES flow solver results with experimental combustor exit temperatures, and with other code predictions, providing a unique opportunity for validation of the flow solver.
Technology Areas:
Aircraft Engines; Biochemical Conversion; Chemical; Combustion; Fundamental Propulsion Physics; Micro Thrusters; Simulation Modeling Environment; Testing Facilities; Thermodynamic Conversion
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A2.04-8242 (SBIR 06-2)
Integrated Variable-Fidelity Tool Set for Modeling and Simulation of Aeroservothermoelasticity-Propulsion (ASTE-P) Effects for Aerospace Vehicles Ranging From Subsonic to Hypersonic Flight
Advanced Dynamics, Inc.
HubZone: No
Women Owned: No
Minority Owned: Yes
Center: NSSC
Proposal Abstract/Firm Contact
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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 toolset 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. The results achieved in Phase I have demonstrated the initial capability; the end software in Phase II will be fully capable of ASTE-P analysis and evaluation for aerospace vehicles.
Technology Areas:
Ablatives; Airframe; Computational Materials; Controls-Structures Interaction (CSI); Fundamental Propulsion Physics; Guidance, Navigation, and Control; Simulation Modeling Environment
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A2.05-8507 (SBIR 06-2)
High-Fidelity Aerodynamic Design with Transition Prediction
Desktop Aeronautics, Inc.
HubZone: No
Women Owned: Yes
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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To enhance aerodynamic design capabilities, Desktop Aeronautics proposes to significantly improve upon the integration (performed in Phase 1) of 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.
Technology Areas:
Aircraft Engines; Airframe
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A2.07-9416 (SBIR 06-2)
Miniature High Force, Long Stroke Linear Shape Memory Alloy Actuators
MIGA Motor Company
HubZone: No
Women Owned: No
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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Shape Memory Alloys (SMAs) are metal alloys (of Nickel-Titanium, for example) that can change their 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 attributable 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 large strokes in highly compact, lightweight packages. Our current commercially available electric linear actuators provide 1/2" of stroke with 4.5 pounds of output force. We propose to develop several high force variants of our DM designs, allowing up to 32 lbf (high cycle count) or 48 lbf (hundreds of cycles) 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, protected or over-molded precision chemically-etched stainless-steel stages, and various load-sharing techniques have enabled these powerful actuators to finally become a reality.
Technology Areas:
Aircraft Engines; Attitude Determination and Control; Biomedical and Life Support; Cooling; Electromagnetic Thrusters; Electrostatic Thrusters; Erectable; Guidance, Navigation, and Control; Human-Robotic Interfaces; Integrated Robotic Concepts and Systems; Kinematic-Deployable; Manipulation; Mobility; Multifunctional/Smart Materials; Perception/Sensing; Pilot Support Systems; Portable Life Support; Substrate Transfer Technology; Teleoperation; Tools
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A2.09-8306 (SBIR 06-2)
Multidisciplinary Optimization Object Library
M4 Engineering, Inc.
HubZone: No
Women Owned: Yes
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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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 was 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". In Phase II we extend this to the problems of design space exploration, uncertainty quantification, and analysis/test correlation, and demonstrate the approach on a set of MDAO problems.
Technology Areas:
Simulation Modeling Environment; Software Tools for Distributed Analysis and Simulation
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A2.09-9065 (SBIR 06-2)
Multi-Disciplinary Multi-Fidelity Design Environment
Phoenix Integration
HubZone: No
Women Owned: No
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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To meet the design challenges of tomorrow, NASA and industry require advancements in the state-of-the-art for physics-based design and analysis frameworks. In particular, NASA needs the ability to make more use of physics-based models earlier in the design process. This will allow engineers to more accurately capture the complex coupling between engineering disciplines and to more accurately simulate the complex behavior of novel design configurations. Key technical barriers include long execution times, model and data complexity, and geometry management. In the Phase II project, Phoenix Integration will expand on the successful Phase I prototypes to develop new technologies and user interfaces that will help overcome these barriers. This project will focus on (1) the development of a flexible capability for implementing Multi-Disciplinary Analysis and Optimization (MDAO) strategies (such as multi-fidelity) in ModelCenter, (2) the creation of a flexible geometry visualization and monitoring capability for high-fidelity system models, and (3) the extension of Phoenix Integration's "Plug-In" infrastructure to better support a wide range of high-fidelity analysis and geometry management tools (CAD/CAE tools, meshing tools, mesh morphing tools). These technologies will combine with other NASA funded technologies to create a robust physics-based design and analysis framework for designing next generation air vehicles.
Technology Areas:
Simulation Modeling Environment; Software Development Environments; Software Tools for Distributed Analysis and Simulation
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A2.10-8181 (SBIR 06-2)
Optimized Cellular Core for Rotorcraft
Patz Materials & Technologies
HubZone: No
Women Owned: No
Minority Owned: No
Center: GRC
Proposal Abstract/Firm Contact
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Patz Materials and Technologies has developed, produced and tested, as part of the Phase-I SBIR, a new form of composite cellular core material, named Interply Core, this new product is a major step forward in composite core technology. The Interply Core was physically tested to have twice the compressive strength compared to the same density aramid paper and glass fabric core presently available to the aerospace industry. In addition, the new core material has the ability be utilized without any change in the composite aerospace structures manufacturing processes. The Phase II project will be to develop the production equipment to make significant quantities of Interply Core and then build and test different material iterations to quantify all parameters of Interply Core's abilities.
At the end of phase II the rotorcraft, as well as other aerospace industries, will have a new material to significantly lower weight without changing platform production methodologies.
Technology Areas:
Airframe; Composites
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A2.10-8983 (SBIR 06-2)
Next Generation Modeling Technology for High Speed Rotorcraft
Continuum Dynamics, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: NSSC
Proposal Abstract/Firm Contact
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Development of a new generation of high speed rotorcraft has been hampered by both an absence of strong predictive methods for rotors operating at very high advance ratio and a dearth of relevant test data. Phase I initiated work on these challenges with rotor tests and development of enhanced analyses for high speed flight. Phase I testing produced useful data on model scale autorotating rotors at advance ratios up to 1.7, thereby supporting analysis development and laying the groundwork for further Phase II testing. Enhanced yawed flow models for comprehensive rotorcraft analyses were also investigated and an enhanced lifting surface blade/wake model was developed and validated for improved modeling in this regime. Additionally, Phase I studied CFD grid generation and flow analysis methods for improved modeling of reversed and strong spanwise flows. Phase II will see further high advance ratio rotor tests, up to 2.5, and CFD analysis supporting the development of new validated models suitable for extreme yawed flow. These new models will be incorporated into CDI's commercial rotorcraft aerodynamics software for immediate use in rotorcraft design and flight simulation codes. A hierarchy of models will be developed supporting applications ranging from high resolution CFD to real-time simulation.
Technology Areas:
Software Tools for Distributed Analysis and Simulation
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A2.10-9691 (SBIR 06-2)
A Post-Processing System for Physics Based Derived Rotorcraft Computational Aero-Acoustics Simulations
JMSI, Inc. dba Intelligent Light
HubZone: No
Women Owned: Yes
Minority Owned: No
Center: LaRC
Proposal Abstract/Firm Contact
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Intelligent Light, the makers of the FIELDVIEW CFD post-processing software, in response to NASA SBIR Phase 2 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.
Technology Areas:
Software Tools for Distributed Analysis and Simulation
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A3.01-8158 (SBIR 06-2)
Computational Appliance for Rapid Prediction of Aircraft Trajectories
Optimal Synthesis, Inc.
HubZone: No
Women Owned: No
Minority Owned: No
Center: NSSC
Proposal Abstract/Firm Contact
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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 algorithms, the success of these systems will depend strongly on the ability to rapidly generate trajectory predictions. By combining algorithmic improvements and high-performance computing hardware, Phase I research demonstrated significantly accelerated prediction of high-fidelity aircraft trajectories using the NASA-FACET software.
Phase II research will build on the Phase I feasibility demonstration results to develop a full-scale computational appliance for rapid prediction of aircraft trajectories (CARPAT). The proposed architecture will combine the trajectory and airspace modeling capabilities of the FACET software with commercial, off-the-shelf high-performance computing technology. High-speed trajectory predictions and iterative computation of traffic flow management algorithms will be demonstrated under realistic traffic scenarios. The trajectory prediction appliance will commercialized during the Phase III work.
Technology Areas:
Computer System Architectures; Guidance, Navigation, and Control; On-Board Computing and Data Management; Pilot Support Systems; Software Tools for Distributed Analysis and Simulation
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A3.01-8855 (SBIR 06-2)
ACES Model Composition and Development Toolkit to Support NGATS Concepts
Intelligent Automation, Inc.
HubZone: No
Women Owned: Yes
Minority Owned: No
Center: NSSC
Proposal Abstract/Firm Contact
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Building on recent advances in formal agent specification, protocol composition, model composers, and visualization capabilities provided by development environments such as eclipse, the key innovation in this effort is the development of an agent model composition toolkit that will enable NASA ACES users to design and compose agents, activities, and models to meet specific design requirements. From a users perspective the front end of the toolkit will be very similar in spirit to a Simulink<SUP>REG</SUP> or a Matrix-X<SUP>REG</SUP> where users can drag and drop from a library of models, interconnect the inputs and outputs of these models, and run a simulation. In addition to composing 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 in other languages such as Matlab<SUP>REG</SUP>. Integral to the Phase II effort will enhancements to the ACES-X, TAP architecture to enable plug-n-play of detailed 4-D trajectories in the terminal area, the development of a Command and Control framework for ACES-X and the development of a library of C2 models to enhance the capabilities of the ACES-X TAP.
Technology Areas:
Computer System Architectures; Guidance, Navigation, and Control; On-Board Computing and Data Management; Simulation Modeling Environment
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