一种脱靶量最小的最优末制导指令设计

A DESIGN OF OPTIMAL TERMINAL GUIDANCE COMMAND WITH MINIMIZING MISS DISTANCE

给出了一种中远程战术导弹的捷联复合制导系统最优末制导指令设计。基于最优控制理论的二次型性能指标,将弹体-自动驾驶仪惯性计为高阶受控对象,导出了最优制导指令的解析表达式,并对剩余飞行时间进行了研宽。数字仿真结果表明,所作分析与设计是有效的。

In this paper, a strapdown combined terminal guidance system for the medium-range missile is studied. An optimal guidance command is designed. When both missilebody and autopilot are considerd as high-order controlled process, an analytic expression of guidance command is derived from optimal control theory. The time-to-go is also discussed. Finally, digital simulations show that the schemes can work effectively.