卫星姿控多推力器高速率阻尼算法及验证  

High-Velocity Damping Algorithms and Validation for Multiple Jets of a Satellite

作　　者：袁彦红 王北超 范蕾懿 查理 范勇 梁巨平 李爽 Yuan Yanhong;Wang Beichao;Fan Leiyi;Zha Li;Fan Yong;Liang Juping;Li Shuang(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Shanghai Aerospace Control Engineering Institute,Shanghai 201109,China)

机构地区：[1]南京航空航天大学航天学院,南京211106 [2]上海航天控制技术研究所,上海201109

出　　处：《航天控制》2022年第5期15-21,共7页Aerospace Control

摘　　要：本文针对某小卫星姿轨控系统仅安装4台推力器,入轨后要求姿控系统在数秒内完成速率阻尼。由于该卫星三轴姿态控制相互耦合,一般速率阻尼算法难以达到控制需求。设计了卫星姿态角速度三轴解耦和三轴推力耦合速率阻尼两种算法。半物理实时仿真结果表明,两种算法均可以达到高速率阻尼的目的,而采用推力耦合算法能取得更好的控制效果。A small satellite only four thrusters are installed on the satellite,and the attitude control system is required to complete velocity damping within several seconds.General velocity damping methods are difficult to meet control requirements because three-axis attitude control is coupled with each other.Therefore,regarding the compound applied function of the attitude control thrusters in the three axes,two velocity-damping algorithms are studied for the attitude angular velocity of the satellite consisting of three-axis decoupling and thrust coupling methods.Semi-physical real-time simulation results show that the proposed two algorithms can achieve the purpose of high-velocity damping and the thrust coupling one achieves better control effect.

关 键 词：卫星姿态控制 高速率阻尼 姿态解耦算法 推力耦合算法 半物理仿真验证 

分 类 号：V448[航空宇航科学与技术—飞行器设计]