本文讨论利用线性二次导引法(LQG)来设计拦截器加速度分布曲线,该拦截器用于对付加速飞来的威胁目标。假设拦截器所使用的固体推进剂点燃以后便不间断地燃烧,但其药柱采取分段装配方案,以便在弹道的不同阶段产生不同的加速度。仿真结果表明,当采用增强式比例导引(APN)作为一种导引规律时,所产生的加速度分布曲线在很大程度上取决于预测拦截点的误差向量。本文介绍的导引法与其它最优控制规律之间的主要差别是:LQG法在大部分寻的时间内采用纯调节器模式(无末端约束)。由于没有末端约束,过去从未把纯调节器模式作为一种可行的引导方法。然而,如果寻的时间很长,那就有助于在寻的的大部分时间内采用纯调节器模式,而只在较后时间内采取末端约束。这样可以降低对总的转向速度的要求,并可产生均匀的加速度分布曲线,从而简化了固体燃料发动机的设计。 This article discusses the design of an interceptor acceleration profile using the linear quadratic guidance method (LQG), which is designed to deal with the threat of accelerating flying targets. It is assumed that the solid propellant used in the interceptor ignites without interruption, but its pellets adopt a segmented assembly scheme to produce different accelerations at different stages of trajectory. The simulation results show that the acceleration distribution curve generated by enhanced proportional guidance (APN) as a guiding law depends largely on the error vector of the predicted interception point. The main difference between the guidance method introduced in this paper and the other optimal control laws is that the LQG method uses the pure regulator mode (without end constraints) for most of the time sought. Since there was no end constraint, pure regulator mode was never used as a viable guide. However, looking for a long time helps to use the pure regulator mode for the majority of the time it is sought, but only for the end constraints at a later time. This reduces the overall steering speed requirement and produces a uniform acceleration profile that simplifies the design of the solid fuel engine.