攻击地面机动目标的一种击顶制导策略

A Guidance Law for Overhead Attacking Surface Maneuver Target

针对三维空间导弹和地面机动目标相对运动的非线性模型,将目标运动速度和机动加速度视为有界扰动,设计了一种击顶制导律策略。制导策略分为2部分:第1部分基于弹目视线倾角角速度和偏角角速度反馈,利用非线性系统输入输出线性化方法设计了接近制导律,保证导弹朝向目标运动;第2部分基于弹目视线倾角反馈,利用非线性系统输入输出线性化方法设计了击顶制导律。该制导律在保证弹目视线角速度趋零的同时还可保证视线倾角趋于-90°,从而实现对目标的垂直打击即击顶。从理论上分析了制导系统的稳定性和精度。数值仿真结果证实该制导律有效。

3-D relative motion model for missile and surface maneuver target was established. Target velocity and maneuver acceleration were all treated as bounded disturbance. Guidance law proposed in the paper contains two parts those are nonlinear approach guidance law and nonlinear overhead attack guidance law. The former guidance law was designed based on the feedback of the pitch and azimuth rate of missile-target line of sight using input-output linearization. The later guidance law was designed based on the feedback of missile-target＇s line of sight pitch using input-output linearization. Overhead attacking surface maneuver target was realized because the guidance law can guarantee the missile-target＇s line of sight pitch to reach negative ninety degree and missile-target＇s line of sight angle rate to reach zero simultaneously. Stability and precision of the guidance system were analyzed theoretically. Numerical simulation result shows the effectiveness of the guidance law.