An improved installation for control moment gyros and its applications on reconfiguration and singular escape

被引：14
|
作者：
Zhang Jingrui [1 ]
Jin Jin [2 ]
Liu Zaozhen [1 ]
机构：
[1] Beijing Inst Technol, Sch Aerosp Engn, Minist Educ, Key Lab Dynam & Control Flight Vehicle, Beijing 100081, Peoples R China
[2] Tsinghua Univ, Sch Aerosp, Beijing 100083, Peoples R China
来源：
ACTA ASTRONAUTICA | 2013年 / 85卷
关键词：
Control moment gyros; Failure; Singularity avoidance steering law; Reconfiguration; VIBRATION ISOLATION PLATFORM; ATTITUDE-CONTROL; SMALL SATELLITES; DESIGN;
D O I：
10.1016/j.actaastro.2012.12.014
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A cluster of control moment gyros (CMGs) is widely used as the actuator of attitude control for modern satellite. However, to use CMGs will induce some accessional problems, like the singularity and the failure of them. In this paper, a rotator for the support bracket of each control moment gyro (CMG) is adopted and its application on reconfiguration and singular escape is discussed. The first step puts forward a novel reconfiguration scheme for the CMGs and applied on a satellite, which can adjust the installation angles of the remaining CMGs and make the CMGs remain axial symmetry. Then the characteristic of the output torque is studied in the process of reconfiguration of the CMGs. Based on this characteristic, a special steering law of the CMGs is designed to counteract the disturbance from the reconfiguration. The feasibility of singularity avoidance via the reconfiguration is also discussed by calculating the derivative of the singularity measurement to the installation angle. A singularity avoidance steering law is proposed based on the above calculation. (C) 2013 IAA. Published by Elsevier Ltd. All rights reserved.
引用
收藏
页码：93 / 99
页数：7
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