Aeroservothermoelastic Modeling for a Hypersonic Wave Rider Vehicle

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$99,999.00
Award Year:
2005
Program:
STTR
Phase:
Phase I
Contract:
FA9550-05-C-0143
Award Id:
73419
Agency Tracking Number:
F054-027-0042
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
4030 Lake Washington Blvd NE, Suite 205, Kirkland, WA, 98033
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
883221723
Principal Investigator:
Robert Stirling
President
(425) 827-7476
rstirling@stirling-dynamics.com
Business Contact:
Dennis Messenger
Business Development Manager
(425) 827-7476
dmessenger@stirling-dynamics.com
Research Institute:
THE UNIV. OF UTAH
Patrick G Hu
201 South President's Circle, Room 201
Salt Lake City, UT, 84112
(801) 585-1547
Nonprofit college or university
Abstract
Development of an innovative analysis and software modeling capability is proposed for aeroservothermoelastic evaluation of air-breathing hypersonic wave rider vehicles. The interface of the airframe dynamic vibration modes with highly nonlinear hypersonic flows is modeled using a particle-based material point method (MPM) in an integrated dynamic fluid-structure environment. MPM is essentially a mesh-free method, which avoids dealing with time-varying mesh distortions and boundary variations due to static and dynamic structural deformations, thus being significantly more robust and computationally efficient than other numerical methods and algorithms, such as the finite element method that is currently favored for fluid-structure interaction simulations. Performance is further enhanced by nonlinear model reduction, massive parallelization, in-situ residual monitoring and computational steering. Inclusion of the flight control system gives a complete integrated aeroservothermoelastic capability covering all flight regimes, and accounting for the aeroelastic effects of dynamic shock/structure interactions and TPS/ablation, as well as real gas effects. The FCS will be represented in full nonlinear detail, and model linearization is also proposed to enable the application of conventional FCS design procedures. Phase I is aimed at establishing basic feasibility and an initial capability. Phase II will extend the research into more detailed developments, leading to a full capability.

* information listed above is at the time of submission.

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