Development of the Hale Aircraft's Aeroelastic Model with Very Flexible Wings

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Borhanpanah, Mohammad Reza | 2022

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Type of Document: Ph.D. Dissertation
Language: Farsi
Document No: 55027 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Dehghani Firouzabadi, Roohallah
Abstract:
In this study, a nonlinear aeroelastic model for an aircraft with fully flexible wings is obtained. This aeroelastic model is based on system identification and is created using the beam model for the structure and the three-dimensional panel method for aerodynamic analysis. The model intended for the structure is a nonlinear beam with exact geometry with initial deformation and rigid motion. The model intended for aerodynamics is an unsteady three-dimensional panel method for the airplane’s body, wings, and tail. The desired aeroelasticity model is a reduced-order model based on system identification using the time-domain/frequency-domain aerodynamic response under forced vibrations in the form of structural modes. In this study, numerical results of linear elastic trim condition analysis, elastic aircraft’s trim with nonlinear structure, linear stability analysis around the nonlinear trim condition, and full aircraft aeroelastic parametric study are presented.
Keywords:
Aeroelasticity ; Aeroelastic Instability ; Flexible Aircraft ; Three Dimentional Panel ; Nonlinear Trim ; Exact Geometry Beam ; Flexible Wing

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