过载指令约束下的导弹导引律设计

基于平面内的目标-导弹相对运动方程，采用指令滤波backstepping方法设计了一种过载指令约束下的平面导引律，同时考虑了导弹自动驾驶仪的二阶动态特性。依据制导系统主要状态变量响应特性要求将制导系统分为两个子系统。采用指令滤波backstepping方法基于零化视线角速率原则和目标-导弹相对速度小于一个负常数的原则分别对两个子系统进行导引律设计。指令滤波backstepping方法不仅能够有效地处理过载指令饱和约束而且克服了传统backstepping方法中“项数爆炸”的缺陷。在过载指令饱和且导弹自动驾驶仪存在较大滞后的情况下，针对视线方向施加控制和不施加控制两种情况进行了仿真，结果表明设计的导引律在拦截大机动目标时具有优良的性能。

Design of Missile Guidance Law Subject to Acceleration Command Constraint

Based on target-missile relative motion equation in plane, a two-dimensional guidance law subject to acceleration command constraint is designed using command filtered backstepping approach, and the second-order dynamics characteristics of missile autopilot is considered. The guidance system is divided into two sub-systems in the light of stability requirement of the main states. Then the command filtered backstepping approach is used to design the guidance laws for two sub-systems based on the principles of zeroing line-of-sight(LOS) angular rate and letting the relative velocity between missile and target be less than a negative constant, respectively. The command filtered backstepping approach can not only address saturation constraint on acceleration command but also overcome the deficiency of “explosion of terms” in the conventional backstepping method. Finally, the simulations are performed for controlling and non-controlling along LOS in the case of acceleration command saturation and missile autopilot with big lag. The results show that the guidance law has excellent performance for intercepting a highly maneuvering target.