摘要
针对以单框架控制力矩陀螺(SGCMG)为执行机构的卫星,提出分步设计控制律和操纵律来实现欠驱动姿态控制。用两个SGCMG进行三轴控制时,将控制系统分解为控制律设计和操纵律设计两部分,来实现角速度稳定和姿态角稳定。通过卫星姿态动力学方程和运动学方程,分别设计状态反馈控制器和反步法控制器;再进行SGCMG的操纵律设计。结合所设计的控制律和操纵律,能够实现基于SGCMG的欠驱动卫星姿态控制,数学仿真验证了该算法的有效性。
The paper deals with the attitude control of a rigid under-actuated satellite by containing the controlling law and steering law which use back-stepping control with a single gimbal control-moment-gyroscope(SGCMG).The mission contains two parts as the controlling law and the angle velocity steering law of SGCMGs.The controlling law includes angle constringency and angle velocity constringency.Firstly,the state equations are established.A discontinuous state feedback controller and a back-stepping controller are designed separately to stabilize the angle and angle velocity of the satellite.The steering law of SGCMGs is designed lastly.The attitude control is achieved by combining the three laws.Finally the availability of the proposed method is verified by a numerical simulation.
作者
刘美师
吴敬玉
王文妍
杨盛庆
谢任远
LIU Meishi;WU Jingyu;WANG Wenyan;YANG Shengqing;XIE Renyuan(Shanghai Aerospace Control Technology Institute,Shanghai 201109,China)
出处
《上海航天》
CSCD
2018年第1期48-53,共6页
Aerospace Shanghai
基金
上海青年科技启明星计划(17QB1401400)
关键词
欠驱动
姿态控制
单框架控制力矩陀螺(SGCMG)
微分方程
反步法
状态反馈
控制律
操纵律
under-actuation
attitude control
single gimbal control-moment-gyroscope(SGCMG)
differential equation
back-stepping
state feedback
controlling law
steering law
