无陀螺偏置动量微纳卫星的姿态控制方案研究  

Attitude control scheme for momentum biased micro-nano satellite without gyroscope

作　　者：李明群[1,2] 雷拥军 蒋庆华[1] LI Mingqun;LEI Yongjun;JIANG Qinghua(Bejing Institute of Control Engineering,Beijing 100094,China;National Key Laboratory of Space Intelligent Control,Beijing 100094,China)

机构地区：[1]北京控制工程研究所,北京100094 [2]空间智能控制技术全国重点实验室,北京100094

出　　处：《先进小卫星技术（中英文）》2024年第4期14-20,共7页Advanced Small Satellite Technology

摘　　要：针对低成本微纳卫星的姿态控制问题进行了研究,提出了一种无陀螺条件下的偏置动量姿态控制方案,控制部件仅包含磁强计、磁力矩器和一个动量轮,配置精简。使用磁强计实现了卫星姿态确定,通过磁力矩器与动量轮的组合控制实现了三轴稳定的对地定向姿态控制,并具备了由任意初始姿态条件恢复至三轴稳定对地定向姿态的能力。仿真结果表明:姿态确定精度优于2°,姿态控制精度优于3°,姿态稳定度优于0.003(°)/s。A study was conducted on the attitude control problem of low-cost micro-nano satellites,and a bias momentum attitude control scheme was proposed under the condition of no gyroscope.The attitude control system included only one magnetometer,one magnetic torquer,and one momentum wheel,with a simple configuration.Only one magnetometer was used to determine the satellite′s attitude.By combining the magnetic torquer and the momentum wheel control,a three-axis stable Earth-oriented attitude control could be achieved,and it could recover from any initial attitude condition to a three-axis stable Earth-oriented attitude.The attitude determination accuracy is better than 2°,the attitude control accuracy is better than 3°,and the attitude stability is better than 0.003(°)/s.

关 键 词：微纳卫星 磁强计 磁力矩器 姿态控制 偏置动量 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]