摘要
以单框架控制力矩陀螺(SGCMG)为卫星动量交换机构,基于建立的姿态控制系统与SGCMG系统的动力学模型,设计零动量卫星的PD(比例微分)解耦姿态控制律。为逃避奇异,提出了一种改进的单框架控制力矩陀螺群(SGCMGs)奇异鲁棒伪逆操纵律算法。某航天器姿态控制仿真结果表明:改进算法可避免奇异,算法有效性得以验证。
The proportional and differential deeoupling control law of satellite attitude with zero momentum was designed based on the dynamic models of the attitude control system and single gimbal control moment gyro （SGCMG） when SGCMG was served as the momentum exchanging actuator in this paper. An improved singular robust pseudo-converse control law using the single gimbal control moment gyros （SGCMGs） was put forward to escape from the singular point. The simulation results of the attitude control for some spacecraft showed that the singular point could be escaped using the improved algorithm, and the effectiveness of the algorithm was approved.
出处
《上海航天》
2009年第2期1-8,26,共9页
Aerospace Shanghai
关键词
单框架控制力矩陀螺
奇异
鲁棒伪逆操纵律
姿态控制
Single gimbal control moment gyro
Singular point
Robust pseudo-converse control law
Attitude control
