反坦克导弹带落角约束滑模导引律研究

Sliding Mode Guidance Law with Impact Angle Constraint for Antitank Missile

为增大反坦克导弹终端落角,提高战斗部的毁伤效能,基于终端滑模控制理论,及弹目相对运动模型,选取弹目相对速度偏角作为滑模面,同时引入落角约束项,结合快速幂次趋近律,推导出了一种带落角约束的滑模导引律。采用有限时间控制理论对导引律的稳定性和有限时间收敛特性进行了证明。最后基于弹道仿真,将该导引律与带落角约束的偏置比例导引律进行了对比仿真分析,结果表明该导引律能够满足制导精度和末端落角约束的要求,脱靶量更小,落角控制精度更高,鲁棒性更强。

To increase the sliding mode guidance law with terminal impa impact angle ct angle to enhance the damage efficiency of the warhead, a constraint based on terminal sliding mode control the missile-to-target motion model is proposed. The guidance law selects relative velocity deflection an ory gle and and impact angle constraint as the sliding mode surface, and combines with the fast power reaching law. The stability and finite-time convergent feature of the guidance law is proved with the finite-time control theory. Finally, the law is compared with bias proportional navigation guidance law with impact angle constraint based on trajectory simulation. Simulation results show that the designed guidance law can meet the requirement of guidance precision and terminal impact angel constraint, and has less miss distance, higher impact angle control accuracy, and stronger robustness.