Missile Autopilot Design Based on State Dependent Riccati Equation

In this paper a control approach is presented for flight control system of a rigid body missile using both state dependent Riccati equation (SDRE) method and fast output sampling (FOS) technique. The dynamics and kinematics for missile attitude stable problem are of typical nonlinear character. SDRE technique has been well applied to this kind of highly nonlinear control problems. But in practice the system states needed in the SDRE method are sometimes difficult to obtain. FOS method, which makes use of only the output samples, is combined with SDRE to accommodate the incomplete system state information. Thus, the control approach is more practical and easy to implement. The method and its stabilization are examined under numerical simulations and the results show that the proposed method produces excellent results and multi-model robust stabilization is achieved.