Integrated Variable-Fidelity Tool Set for Modeling and Simulation of Aeroservothermoelasticity-Propulsion (ASTE-P) Effects for Aerospace Vehicles Ranging From Subsonic to Hypersonic Flight

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX08CA39C
Agency Tracking Number: 067285
Amount: $599,990.00
Phase: Phase II
Program: SBIR
Awards Year: 2008
Solicitation Year: 2006
Solicitation Topic Code: A2.04
Solicitation Number: N/A
Small Business Information
1500 Bull Lea Road, Suite 203, Lexington, KY, 40511-0017
DUNS: 790637867
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: Y
Principal Investigator
 Patrick Hu
 Principal Investigator
 (859) 699-0441
Business Contact
 Patrick Hu
Title: Business Official
Phone: (859) 699-0441
Research Institution
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.

* Information listed above is at the time of submission. *

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