Integration control of semi-strapdown coordinator stable tracking and missile body attitude

被引：0

作者：

Yi K. ^{[1
]}

Chen J. ^{[2
]}

Liang Z. ^{[1
]}

Ren Z. ^{[1
]}

Li Q. ^{[1
]}

机构：

[1] School of Automation Science and Electrical Engineering, Beihang University, Beijing

[2] College of Engineering, China Agricultural University, Beijing

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2016年 / 37卷 / 12期

基金：

中国国家自然科学基金;

关键词：

Attitude control; Backstepping control; Integration control; Semi-strapdown coordinator; Stable tracking;

D O I：

10.7527/S1000-6893.2016.0128

中图分类号：

学科分类号：

摘要：

The semi-strapdown coordinator is located on the missile body. Because of the existence of the parasitic loop, the control loop for stable tracking of the semi-strapdown coordinator is strongly coupled with the control loop of the missile body attitude. As a result, the stability and tracking performance of the coordinator are severely affected. In order to solve this problem, an integration control method is proposed. Control law is designed based on the backstepping theory. Stability and dynamic performance of the system can be ensured by choosing an appropriate feedback gain. The integrated control system is verified by simulations. Results show that the integration controller, which considers the coupling between the coordinator stable tracking loop and the missile attitude loop, can not only ensure the dynamic performance of the missile attitude control system, but also improve the stable tracking performance of the coordinator and prevent the high-speed target from escaping from the field of view of the missile seeker. © 2016, Press of Chinese Journal of Aeronautics. All right reserved.

引用

页码：3752 / 3763

页数：11