Abstract A canard/tail rudder compound control method for missile is presented in this paper. The canard/tail rudder compound control system is designed based on the linearized small disturbance model of missile. The canard/tail rudder compound allocation strategy is proposed and optimized by the sequential quadratic programming method. The performance and overload capability of the control system are analyzed by simulation on Matlab/Simulink. The simulation results show that the compound control method can not only ensure the high dynamic and steady-state performance of the control system, but also ensure the maneuverability of the missile in high altitude, thus proving the algorithm in this paper to be reliable and effective.
Received: 30 January 2019
Published: 23 August 2019
2019, Vol. 2 
