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Aeroelastic stability consideration of supersonic flight vehicle using nonlinear aerodynamic response surfaces

Fathi Jegarkandi, M ; Sharif University of Technology | 2009

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  1. Type of Document: Article
  2. DOI: 10.1016/j.jfluidstructs.2009.04.006
  3. Publisher: 2009
  4. Abstract:
  5. Aeroelastic stability of a flexible supersonic flight vehicle is considered using nonlinear dynamics, nonlinear aerodynamics, and a linear structural model. Response surfaces including global multivariate orthogonal modeling functions are invoked to derive applied nonlinear aerodynamic coefficients. A modified Gram-Schmidt method is utilized to orthogonalize the produced polynomial multivariate functions, selected and ranked by predicted squared error metric. Local variation of angle-of-attack and side-slip angle is applied to the analytical model. Identification of nonlinear aerodynamic coefficients of the flight vehicle is conducted employing a CFD code and the required analytical model for simulation purposes is constructed. The method is used to determine the aeroelastic instability and response of a selected flight vehicle. © 2009 Elsevier Ltd. All rights reserved
  6. Keywords:
  7. Aeroelastic instabilities ; Aeroelastic stability ; Aeroelasticity ; Analytical model ; Angle-of-attack ; CFD codes ; Flight vehicles ; Generalized coordinates ; Gram-schmidt ; Linear structural model ; Local variations ; Modeling functions ; Multivariate function ; Non-linear aerodynamics ; Non-linear dynamics ; Response surface ; Sideslip angles ; Simulation code ; Squared errors ; Supersonic flights ; Elastic waves ; Elasticity ; Flight dynamics ; Gas dynamics ; Model structures ; Stability ; Surface properties ; Vehicles ; Simulators
  8. Source: Journal of Fluids and Structures ; Volume 25, Issue 6 , 2009 , Pages 1079-1101 ; 08899746 (ISSN)
  9. URL: https://www.sciencedirect.com/science/article/abs/pii/S0889974609000504