Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering

In the present work an aero-elastic model is presented for the aero-elastic analysis and optimization of composite plate like wings with different geometry. A Finite Element Model is developed to predict the performance of plate wings. A divergence analysis is carried out using the finite element model combined with the vortex lattice method for aerodynamic load calculations. The flutter analysis is carried out using the finite element model combined with the doublet lattice method. The aerodynamic model is coupled to the structural model using the shape (interpolation) functions of the finite element model. It is assumed that the proposed mapping is more consistent, and hence is expected to produce more accurate results as compared to other methods using simple interpolation methods. Static condensation is used to express the finite elements{u2019} in-plane degrees of freedom in terms of the bending ones, hence reducing the number of the elements{u2019} degrees of freedom per node to three. A MATLAB code is developed to implement the proposed model using three-node triangular plate finite elements

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