Two-stage control guidance of missile impact angle and flight time

被引：2

作者：

Li X. ^{[1
,2
]}

Wang L. ^{[1
]}

Fan X. ^{[2
]}

Ding B. ^{[2
]}

Xue L. ^{[1
]}

Wang M. ^{[2
]}

机构：

[1] Department of Control Engineering, Rocket Engineering University, Xi'an

[2] Rocket Force Sergeant School, Qingzhou

来源：

Wang, Lixin (281167393@qq.com) | 2017年 / National University of Defense Technology卷 / 39期

关键词：

Flight time control; Gravity compensation; Guidance; Impact angle control;

D O I：

10.11887/j.cn.201706002

中图分类号：

学科分类号：

摘要：

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. © 2017, NUDT Press. All right reserved.

引用

页码：6 / 11

页数：5

共 16 条

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