Aeroservothermoelastic Modeling for a Hypersonic Wave Rider Vehicle

Period of Performance: 08/01/2005 - 05/01/2006


Phase 1 STTR

Recipient Firm

Stirling Dynamics Incorporated
4030 Lake Washington Blvd NE, Suite 205
Kirkland, WA 98033
Firm POC
Principal Investigator

Research Institution

University of Utah
75 S 2000 E
Salt Lake City, UT 84112
Institution POC


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.