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

A mathematical model is conducted on flapping wing micro air vehicle. This Mathematical Model depends on some key unsteady aerodynamic mechanisms implemented using a Matlab code. A nonlinear longitudinal-axis dynamic model simulation of the vehicle is presented. The model under the assumption of ignoring the contribution from wing rotation is simplified. A direct average theory is introduced to change the nonlinear time-periodic system to the nonlinear time-invariant system and simulate the model. The linearized about a hover condition is then obtained used for stability analysis and design controller to control perturbations. Two types of control system design methodology are used. Full state feedback and linear quadratic regulator are designed on a linearized model. The controllers are attached to the nonlinear system. Simulation results demonstrate that the controllers can successfully stabilize the vehicle under perturbations around the hover condition

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