### 基于锥形运动的制导火箭速度控制导引律设计

1. 南京理工大学 能源与动力工程学院, 江苏 南京 210094
• 收稿日期:2013-05-22 修回日期:2013-09-28 出版日期:2014-04-25 发布日期:2013-10-28
• 通讯作者: 孙瑞胜，Tel.：025-84315193 E-mail：srscom@163.com E-mail:srscom@163.com
• 作者简介:刘鹏云男，博士研究生。主要研究方向：火箭弹制导控制系统设计。Tel：025-84315193 E-mail：liupengyun802@163.com；孙瑞胜男，博士，副教授，博士生导师。主要研究方向：火箭弹总体设计。Tel：025-84315193 E-mail：srscom@163.com
• 基金资助:

国家自然科学基金（11176012）；航空科学基金（20110159001）

### A Coning Motion-based Guidance Law for Guided Rocket with Velocity Control

LIU Pengyun, SUN Ruisheng, LI Weiming, MING Chao

1. School of Energy and Power Engineering, Nanjing Institute of Technology, Nanjing 210094, China
• Received:2013-05-22 Revised:2013-09-28 Online:2014-04-25 Published:2013-10-28
• Supported by:

National Natural Science Foundation of China (11176012);Aeronautical Science Foundation of China (20110159001)

Abstract:

This paper develops a novel coning motion-based guidance method for a missile with impact velocity control. First, an ideal trajectory of a virtual target is designed based on the requirement of impact velocity, and the problem of velocity control for the missile is transformed into that of tracking the virtual target. Then, the locomotion models of the guided rocket and the virtual target are formulated. Furthermore, the information of the relative position and velocity between the rocket and the virtual target is used for the formula derivation of the coning motion-based guidance law. Based on the theory of dynamic inversion, the guidance parameters and commands are designed. Finally, the new guidance method is evaluated using a simulation of the typical terminal guidance for a guided rocket with velocity control. Simulation results demonstrate that the proposed guidance law has a good performance and can be applied to the guidance of missiles with impact velocity control in different impact angle constraints, which provides some significant reference for the technology of velocity control.