国防科技大学学报2017，Vol.39Issue(6)：6-11,6.DOI:10.11887/j.cn.201706002
导弹撞击角度与飞行时间两阶段控制制导律
Two-stage control guidance of missile impact angle and flight time
摘要
Abstract
The impact angle and the flight time were needed to be controlled simultaneously for a saturation attack.A two-stage guidance strategy with impact angle and flight time was proposed for impact angle and flight time control.In the first stage,the impact time high-precision control guidance law was derived by using a switching surface in pitch channel.The traditional proportional guidance law was used in yaw channel.Then in the second stage,the trajectory shaping optimal guidance with gravity compensation was used for impact angle control,which was an extension of explicit guidance in that gravity compensation was incorporated.The effectiveness of the impact angle and impact time two-stage guidance was validated by simulation.Simulation results show that the proposed two-stage control guidance with impact angle and flight time can achieve the simultaneous control of the impact angle and flight time.关键词
制导/撞击角度控制/飞行时间控制/重力补偿Key words
guidance/impact angle control/flight time control/gravity compensation分类
航空航天引用本文复制引用
李新三,汪立新,范小虎,丁邦平,薛亮,王明建..导弹撞击角度与飞行时间两阶段控制制导律[J].国防科技大学学报,2017,39(6):6-11,6.基金项目
国家自然科学基金资助项目(61503390) （61503390）
