Design of autopilot for blended controlled missiles via state-dependent Riccati equation

A missile autopilot is designed via the state-dependent Riccati equation (SDRE) approach for an interceptor with blended lateral thrust and aerodynamic force. A nonlinear dynamic model describing pitch and yaw motion of the blended missile is transformed into a linear-like structure with state-dependent coefficient (SDC) matrices by an extended linearization. Based on this linear-like structure, an SDRE feedback controller is designed to steer the missile to track an acceleration commands. Since the lateral thrust provided by some pulse thrusters is considered as a discrete-time variable, the nonlinear tolerance of the feedback system is analyzed whenever the control cannot be implemented ideally. Some sufficient conditions are given to guarantee that the closed system is locally asymptotically stable. Simulation results vitrify the proposed control strategy.