前言 1977年,曾计划为AIM-9型近程空一空导弹(AAM)研究一种利用最佳控制论来实现的制导规律。在瞄准误差相对小和目标维持高度机动水平的状态中,与比例导引相比较,制导规律对导弹性能有些小改进。根据线性二次高斯理论,这个制导规律展开为 A_(MC)=3(S_R/t_(go)~2+V_R/t_(go)) (1) 式中A_(MC)是三分量导弹指令加速度矢量,S_R是三分量相对位置矢量,V_R是三分量相对速度矢量,以及t_(go)是飞行时间过程,给定为 Preface In 1977, there was a plan to study a guidance law using optimal control theory for the AIM-9 short-range surface-to-air missile. In a state where the aiming error is relatively small and the target maintains a high maneuver level, the guidance law improves the missile performance slightly compared to proportional guidance. According to the linear quadratic Gaussian theory, the guidance law is A_ (MC) = 3 (S_R / t_ (go) ~ 2 + V_R / t_go) (1) where A_ (MC) is the three-component missile command acceleration Vector, S_R is a three-component relative position vector, V_R is a three-component relative velocity vector, and t_ (go) is the time-of-flight process given as