机动再入体的带落角约束扩展比例导引律设计

Terminal guidance law with angular constraint design for maneuvering reentry body

传统的各种制导律都是以获得最小脱靶量为最终目标,没有考虑到导弹击中目标时刻的末端落角。为了保证非自旋再入体完成精确打击目标的任务,针对非自旋再入体垂直打击目标的制导问题,设计了一种带落角约束的扩展比例导引律。仿真研究表明,所设计的末制导律能够保证非自旋再入体命中目标时的脱靶量和末端落角都能满足要求,可以为开展近空间非自旋再入体制导问题的研究提供测试平台。

In the traditional literatures,the aim of guidance law design was to obtain the minimum miss distance as the ultimate goal,without considering the limits from missile terminal angle when the missile hits the target.In order to ensure a nonspinning reentry body to complete the precise attacking task,we design one extended proportional navigation guidance law with terminal angle constraint for nonspinning reentry body vertical attack.Simulation research shows that above terminal guidance laws can ensure the nonspinning warhead to attack a target with required miss distance and required terminal angle,and provides a feasible test platform of nonspinning reentry body guidance system.