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Aeroelastic Analysis of a Trimmed Generic Hypersonic VehicleThe aeroelastic equations of motion governing a hypersonic vehicle in free flight are derived. The equations of motion for a translating and rotating flexible body using Lagrange's equations in terms of quasi-coordinates are presented. These equations are simplified for the case of a vehicle with pitch and plunge rigid body degrees of freedom and small elastic displacements. The displacements are approximated by a truncated series of the unrestrained mode shapes, which are obtained using equivalent plate theory. Subsequently, the nonlinear equations of motion are linearized about the trim state, which is obtained using a rigid body trim model and steady hypersonic aerodynamics. The appropriate flutter derivatives are calculated from piston theory. Results describing mode shapes, trim behavior, and aeroelastic stability of a generic hypersonic vehicle are presented.
Document ID
19990052704
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Nydick, I.
(California Univ. Los Angeles, CA United States)
Friedmann, P. P.
(California Univ. Los Angeles, CA United States)
Date Acquired
August 19, 2013
Publication Date
June 1, 1999
Publication Information
Publication: CEAS/AIAA/ICASE/NASA Langley International Forum on Aeroelasticity and Structural Dynamics 1999
Issue: Pt. 2
Subject Category
Aircraft Design, Testing And Performance
Funding Number(s)
CONTRACT_GRANT: NCC2-374
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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