一种微纳卫星的姿态安全控制方案  

An Attitude Safety Control Scheme for Micro-Nano Satellites

作　　者：李明群[1,2] 雷拥军 蒋庆华[1] LI Mingqun;LEI Yongjun;JIANG Qinghua(Beijing 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：《航天控制》2024年第4期16-21,共6页Aerospace Control

摘　　要：针对微纳卫星在低冗余度下实现姿态安全控制的问题进行了研究,提出一种占用资源少的姿态安全控制方案,当诊断信息不完备时尽可能切除所有潜在故障源,仅用磁强计和磁力矩器实现卫星姿态控制系统的重构。所提方案可以在卫星任意初始姿态条件下完成角速度阻尼,并可控制卫星机动至对日定向姿态,确保帆板充电效率,从而延长故障条件下的卫星寿命。数学仿真表明,在陀螺、星敏感器、动量轮和推力器等主要控制部件均不使用的条件下,所提方案仍可完成稳定的单轴对日定向安全姿态控制,姿态确定精度优于2°,对日定向精度优于5°,极大地提高了卫星在轨安全运行的能力。A study is conducted on the problem of achieving attitude safety control under low redundancy in micro-nano satellite.A resource efficient attitude safety control scheme is proposed,which aims to cut off all potential fault sources as much as possible when diagnostic information is not in complete.Only magnetometer and magnetic torquer are used to reconstruct the satellite attitude control system.The proposed scheme can realize angular velocity damping under any initial attitude condition of the satellite,and can control the satellite maneuvering to the sun oriented attitude,which ensures the efficiency of the solar array charging and thus extends the satellite’s lifespan under fault conditions.Mathematical simulation shows that even when the main control components such as gyroscopes,star sensors and momentum wheels are not available,the proposed scheme can still achieve stable single axis safe attitude control towards the sun,which achieves attitude determination precision by better than 2 degrees and the sun orientation precision by better than 5 degrees that greatly improves the satellite’s safety operation ability in orbit.

关 键 词：微纳卫星 磁强计 磁力矩器 姿态安全控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]