State-of-the-art, Multi-Fidelity Modeling and Simulation (M&S) Tool for Nonlinear Aeroelasticity

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$600,000.00
Award Year:
2011
Program:
SBIR
Phase:
Phase II
Contract:
NNX11CB66C
Award Id:
n/a
Agency Tracking Number:
095442
Solicitation Year:
2009
Solicitation Topic Code:
A2.04
Solicitation Number:
n/a
Small Business Information
KY, Lexington, KY, 40511-1628
Hubzone Owned:
N
Minority Owned:
Y
Woman Owned:
N
Duns:
790637867
Principal Investigator:
Patrick Hu
Principal Investigator
(859) 859-0441
patrick.g.hu@gmail.com
Business Contact:
Patrick Hu
President
(859) 699-0441
patrick.g.hu@gmail.com
Research Institute:
Stub




Abstract
Research is proposed for the development of a state-of-the-art computational aeroelastic tool. This tool will include various levels of fidelity and the ability to perform computational uncertainty quantification for data-driven risk analysis and certification. A number of novel reduced-order in time methods will be implemented into the code allowing for efficient and accurate aeroelastic simulation which will enable both the exploration of complex physics, point design and fast generation of "training data" for reduced order spatial aeroelastic models. The various levels of fidelity available in the code for aeroelastic modeling will range from CFD-based (both grid-based and a novel particle-based method) simulation to reduced-order aeroelastic models based upon Volterra series representations and Proper Orthogonal Decomposition (POD). The application of the proposed innovations spans the range of flight, from high-speed transport vehicles, to small-scale, flapping Micro-Air vehicles. Anticipated results include 1) the further validation and implementation of the proposed novel time-reduced order models into the existing ASTE-P solver framework (which already includes the various level fidelity mentioned above), 2) application of the proposed work to large-scale simulation and comparison with experiment, and 3) advancement of the state of knowledge for nonlinear problems in aeroelasticity in both the subsonic, low Reynolds number regime and transonic high Reynolds number regime.

* information listed above is at the time of submission.

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