Control System Design For A 2-DOF Aircraft Attitude Simulator

The 2-DOF aircraft attitude simulator, which belongs to complicated control system in control filed. Besides its own nonlinear characteristics, there are many factors involved in control of the 2-DOF aircraft attitude model, such as intricate aerodynamics characteristics, influence of flight attitude and so on, which reflects the commonly seen multi-variables, multi-input multi-output, nonlinearity, system uncertainties, couplings, time-varying parameters, and natural instability properties, etc. Specific to these phenomena, a deep analysis of the experimental system was established in this dissertation: a nonlinear model for the 2-DOF aircraft attitude system was developed on the basis of Euler-Lagrange Equation, after which, an effective controller was designed in accordance with the existing problems in practical systems. And simulations were conducted to verify the designed controller.Firstly, a thorough analysis of the entire system, including the mechanical structures, the electrical system, and the control programs was pre was established. Then a multi-input multi-output nonlinear dynamical model was developed according to Euler-Lagrange Equation based on dynamic principles. The uncertain parameters of the system were determined by identification algorithms via practical experiments.Furthermore, to handle the nonlinear system model, we design a robust state-feedback controller on the basis of nonlinear system control theory and the design method of reference tracking control systems and simulation results were presented to validate the model.Finally, design a multi-cell state-feedback controller with ￥H performance index to deal with the multi working points, variable-parameters, and the existed uncertainties and disturbances.And simulation verifies the effectiveness of the controller.