NASA SBIR 2006 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 06-2 A2.04-8242
PHASE 1 CONTRACT NUMBER: NNX07CA39P
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.
1500 Bull Lea Road ,Suite 203
Lexington, KY 40511 - 0017
(859) 699-0441

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Patrick Hu
patrick.g.hu@advanceddynamics-usa.com
1500 Bull Lea Road ,Suite 203
Lexington, KY 40511 - 0017
(859) 699-0441

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 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 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.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
DoD components likely to have interests in the technology developed in this SBIR project are the US Air force, US Army and US Navy.Non-military potential applications represent a major sector from which sales opportunities can be pursued. Improvement of computational accuracy and efficiency is a common interest for wide range of aerospace applications and, thus is highly demanded. Therefore, 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 that we will aggressively pursue.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 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.

NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.

TECHNOLOGY TAXONOMY MAPPING
Ablatives
Airframe
Computational Materials
Controls-Structures Interaction (CSI)
Fundamental Propulsion Physics
Guidance, Navigation, and Control
Simulation Modeling Environment


Form Generated on 08-02-07 14:39