Flight Controller Design for Intercepting Missiles with Multiple TVC Systems and DCS

In this paper, we propose a highly maneuverable autopilot system based on multiple Thrust Vector Control (TVC) mechanisms and Divert Control System (DCS). The strategy of the cooperation of multiple TVC mechanisms and DCS is discussed. Moreover, the decision and control part in missiles: guidance law (GL) and autopilot is presented. The GL is designed with dynamic sliding mode control (DSMC) to eliminate the chattering phenomenon caused by sliding mode control (SMC) and to minimize the distance between the missile and the target without the estimation of interception time. The autopilot controller based on quaternion representation is designed using backstepping control technique to execute the attitude command. The stability of the integrated guidance/autopilot (G/A) system is analyzed by Lyapunov stability theory. In addition, we advocate a wingless missile to reduce the nonlinear effect from the aerodynamics as much as possible. Extensive simulations including aerodynamic model are finally demonstrated to verify the validity of the proposed integrated G/A systems of missiles incorporating the highly maneuverable inputs.