유도탄의 유도명령 추종을 위한 혼합제어기 설계: 공력 및 추력벡터제어

Abstract

This paper is concerned with a control allocation strategy using the dynamic inversion and the pseudo inverse control which generates the nominal control input trajectories. In addition, an autopilot design method is proposed by using time-varying control technique which is missile with aerodynamic fin and thrust 7 time-varying version of the pole placement of linear time-invariant system for an agile vectoring control. The control allocation proposed in this paper is capable of extracting the maximum performance by combining each control effector, aerodynamic fm and thrust vectoring control. The adopted time-varying control technique for the autopilot design enhances the robustness of the tracking performance for a reference command. The main results are validated through the nonlinear simulations with aerodynamic data.