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Nonlinear Aeroelastic Analysis of Composite Wing at a Hale Flight Vehicle

Besharatlou, Mohammad | 2018

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 51266 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Dehghani Firouz-Abadi, Roholla
  7. Abstract:
  8. The purpose of this study is aeroelastic stability analysis and nonlinear aeroelastic vibration of composite wing with nonlinear 1D beam model. Wing’s structure modelled as thin-walled composite single box beam in linear and nonlinear conditions. Thin-walled composite box beam developed by classical lamination theory and structural nonlinearity is von karman strain. Unsteady aerodynamic of wing modelled with modified strip theory. Aeroelastic equations of wing obtained from modal expansion (assumed mode) and Hamilton’s Principle. In order to stability analysis of wing, the linear aeroelastic equations in state space must be calculated and so with eigenvalue analysis instability speed will be obtained. Stability analysis use the theodorsen and peters et al aerodynamic models with swept effect. Time response of wing will be obtained with linear and nonlinear structure and peters et al aerodynamic with using Rang-Kutta numerical solution. Verification of linear structure is based on Librescu (54) and aerodynamic models verification is based on clean goland’s wing. Finally, linear and nonlinear time response of wing at subflutter,flutter and post flutter is studied. Also, LCO at near flutter speed checked
  9. Keywords:
  10. Composite Beam ; Unsteady Aerodynamic ; Stability Analysis ; Hamilton's Principle ; Von Karman Theory ; Assumed Modes Method

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