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Computational Fluid Dynamics-Based Aeroservoelastic Analysis with Hyper-X ApplicationsA finite element computational fluids dynamics-based aeroservoelastic analysis methodology is presented in this paper, in which both structural and fluids discretization are achieved by the finite element method, and their interaction is modeled by the transpiration boundary condition technique. In the fluids discipline either inviscid or viscous flow may be accounted for, usually employing unstructured grids.Adescription of a novel viscous flow solver employing unstructured grids is given in detail. Provisions are made for digital as well as analog controllers. These new aeroservoelastic analysis techniques are next applied for the solution of a number of example problems including the novel Hyper-X launch vehicle. Experimental and actual flight test data are also compared with analysis results that signify to the efficacy and accuracy of the newly developed solution procedures.
Document ID
20070034896
Acquisition Source
Armstrong Flight Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Gupta, K. K.
(NASA Dryden Flight Research Center Edwards, CA, United States)
Bach, C.
(Analytical Services and Materials, Inc. Edwards, CA, United States)
Date Acquired
August 24, 2013
Publication Date
July 1, 2007
Publication Information
Publication: AIAA Journal
Volume: 45
Issue: 7
Subject Category
Launch Vehicles And Launch Operations
Report/Patent Number
Paper 884
Meeting Information
Meeting: AIAA Aerospace Science Conference and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 5, 2004
End Date: January 9, 2004
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other

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