On Attitude Control Technology of Reentry Warhead Using Control Moment Gyroscopes

被引：0

作者：

Wu Zhong ^{[1
]}

Zhu Ting ^{[1
]}

Wei Kongming ^{[1
]}

机构：

[1] Beijing Univ Aeronaut & Astronaut, Sch Instrumentat Sci & Optoelect Engn, Beijing 100191, Peoples R China

来源：

PROCEEDINGS OF THE 29TH CHINESE CONTROL CONFERENCE | 2010年

关键词：

Reentry Warhead; Attitude Control; Control Moment Gyroscopes;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

In order to improve the ability of the mobile penetration, Single Gimbal Control Moment Gyroscopes (SGCMGs) are adopted instead of the control fins and vector thrusters to produce the torque for the attitude control of the reentry warhead. Under the assumption of indifferently static stability, attitude controller is designed for the warhead based on Lyapunov theory. And also, a pseudo-inverse steering law with null motions is used to generate the gimbal velocity commands for SGCMGs according to the desired torque from the attitude controller. Comparing with the strategies with fins or thrusters, the ablation of the actuators can be prevented and the aerodynamic shape can be preserved in this one since SGCMGs are mounted inside the warhead directly. Comparing with the moving mass or flywheels, SGCMGs can output torque large enough to meet the need of large-scope attitude reorientation and stabilization for the warhead. Simulation results of a certain warhead indicate that the control strategy with SGCMGs is feasible.

引用

页码：6139 / 6142

页数：4