一种改进的自适应滑模变结构导引律

An Improved Adaptive Sliding-mode Navigation Guidance Law With Variable Structure

为提高反坦克导弹对空中机动目标的命中精度,使其具备一定的低空防御能力,通过推导纵向平面内末制导段的弹目相对运动简化模型,并以零化弹目视线角速度为出发点,设计了一种改进自适应滑模变结构导引律,同时通过改进开关项系数,综合应用饱和函数,成功削弱了滑模变结构的抖振现象。仿真结果表明,在打击空中机动目标时,设计的导引律具有较高的命中精度,可以合理地分配末制导段导弹的法向过载,证明该文设计的导引律是有效的。

To make anti-tank missile （ATM）have the capability of low-altitude defense, and improve its hit accuracy to air maneuvering target, the simplified missile-target relative motion model of terminal guidance phase in longitudinal plane was derived. Based on the thread of annihilating the missile-target LOS angular-velocity, an improved adaptive sliding-mode variable- structure guidance law was designed. Meanwhile, the chattering phenomenon of variable structure was weaken by the integrated application of saturation function and improved variable switching term. Simulation results show that the guidance law has high accuracy at the time of attacking maneuvering air target, and the normal overload of guidance trajectory can be distributed reasonably by the guidance law. The results prove that the designed guidance-law is effective.