Case studies on U-state space control system design for aircraft dynamic model

In this study, U-state space design approach is used to develop a control system of linearized F-16 aircraft dynamic model. The related F-16 model is converted from the original nonlinear dynamics by Taylor series around the trimmed equilibrium. The linearized model is discretised by zero order hold. The desired closed loop matrix Ad is optimally designed by LQR (linear quadratic regulator). Then the controller output can be obtained by solve the related equations. In case study, a flight condition is selected to determine the trimmed equilibrium. The numerical simulation results show the performance of the proposed approach.