SDRE CONTROL OF THE CONTROL ACTUATION SYSTEM OF A GUIDED MISSILE

Abstract This article illustrates the design and analysis of a nonlinear State-Dependent Riccati Equation (SDRE) controller on a control actuation system (CAS) of an aerodynamically controlled guided missile. The system consists of a DC-motor, the transmission mechanism, a control actuation surface (fin), and a position feedback device. The overall system has to satisfy the desired performance requirements in the presence of the nonlinear modeling characteristics: aerodynamic loading and backlash in the transmission mechanism, both of which are unknown to the controller. Moreover, there are uncertainties in DC-motor parameters and supplied power. The use of a state-dependent (nonquadratic) performance functional is strongly emphasized for control design purposes to show how the integration of mathematical synthesis and engineering objectives can be achieved. A series of numerical simulations are carried out to evaluate the effectiveness and robustness of the proposed nonlinear SDRE controller.