大气层外主动防御三维自适应滑模制导律

针对提高弹道导弹中段突防成功概率问题,提出了主动防御滑模自适应制导律。首先,推导出目标、拦截导弹和防御导弹的三维相对运动方程。其次,基于三角拦截制导策略,利用Lyapunov稳定性理论设计了主动防御滑模自适应制导律(active defense adaptive sliding mode guidance law,AD-ASMG)。该制导律能同时达到两个制导目标:防御导弹处在目标和拦截导弹视线上,保持三点共线;零化防御导弹对拦截导弹的视线转率。最后,针对开关式轨控发动机推力大小不可调节的问题,考虑了发动机动态特性,设计了精确的脉冲宽度调制(pulse width modulation,PWM)控制方法,获得可变的等效力,适应制导指令变化的要求。六自由度仿真结果表明了该制导律的有效性。

Active defense exo-atmospheric adaptive sliding mode guidance law in three dimensions

The problem of ballistic missile middle course penetration is investigated, and a guidance law named active defense adaptive sliding mode guidance law (AD-ASMG) is proposed. First, the three dimensional relative motion equations of the three bodies-target, the intecepting missile the and defending missile are derived. Second, using the Lyapunov stablility theory, the guidance law is derived based on the triangle intecepting guidance strategy. Using the guaidace law two objectives can be achieved simultaneously, which are keeping the defending missile on the line connecting the target to the intercepting missile and nullifying the defending missile’s line-of-sight rate to the intercepting missile. Finally, considering the fact that the thurster can only output the constant force, a pulse width modulation (PWM) controling method which accounts the dynamics of the thruster, is designed to get the variable equivalent force required by the guidance law whose output guidance command is variable. Simulation results show the high performance of the guidance law.