在轨组装卫星自适应姿态控制  

Adaptive Attitude Control for On-Orbit Assembled Satellites

作　　者：钱晓莱 王瀚霆 王小琰 郭禹辰 赵亚涛 QIAN Xiaolai;WANG Hanting;WANG Xiaoyan;GUO Yuchen;ZHAO Yatao(Shanghai Aerospace Space Technology Company Limited,Shanghai 201109,China;Shanghai Institute of Satellite Engineering,Shanghai 201109,China;General Department of Communication and Navigation Satellites,China Academy of Space Technology,Beijing 100098,China;School of Astronautics,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]上海航天空间技术有限公司,上海201109 [2]上海卫星工程研究所,上海201109 [3]中国空间技术研究院通信与导航卫星总体部,北京100098 [4]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《空间控制技术与应用》2023年第6期47-57,共11页Aerospace Control and Application

基　　金：上海航天科技创新基金资助项目(SAST2020-023)。

摘　　要：结合在轨组装卫星姿态敏感器冗余配置和质量参数未知的特点,为了抑制敏感器测量误差和参数不确定性干扰对组装卫星的姿态影响,首先建立陀螺/GPS/星敏多传感器联邦滤波算法,利用残差卡方检验方法实现敏感器故障的检测、隔离和重构,提高姿态确定精度和结果可靠性.在此基础上,通过参数辨识算法估计组装卫星质量参数,提出自适应固定时间滑模控制算法,提高滑模控制在未知干扰下的控制精度,降低参数选取范围改善系统颤振.最后通过数值仿真验证了本文算法的有效性,组装卫星姿态精度小于0.0002°,姿态稳定度小于0.0003(°)/s,表明所提算法实现了组装卫星的高精高稳姿态控制.Combining the characteristics of redundant configuration of attitude sensors and unknown inertia parameters of the on-orbit assembled satellites,in order to suppress the influence of sensor measurement errors and parameter uncertainty disturbance on satellite attitude,firstly a gyroscope/GPS/star sensor multi-sensor federal filtering algorithm is established and the residual chi-square test method is used to achieve the detection,isolation and reconstruction of sensor faults,by which the attitude determination precision and result reliability are improved.On this basis,the parameter identification algorithm is used to estimate the assembly satellite inertia parameters,and the adaptive fixed-time sliding mode control algorithm is proposed to improve the control precision of the sliding mode control under unknown disturbance and reduce the parameter selection range to attenuate the chattering phenomenon.Finally,the algorithm effectiveness is verified by numerical simulation,and the attitude precision and attitude stability of the assembled satellite are within 0.0002°and 0.0003(°)/s,respectively,indicating that the proposed algorithm can achieve high precision and high stability attitude control of the assembled satellites.

关 键 词：自适应固定时间滑模控制 联邦滤波 在轨组装卫星 

分 类 号：V44[航空宇航科学与技术—飞行器设计]