The invention relates to the technical field of spacecraft attitude control, in particular to a load attitude determination method and device based on an included angle monitoring star sensor, and the method comprises the following steps: obtaining a position between a reference mirror coordinate system and a star sensor measurement coordinate system, a position between a central prism coordinate system and the reference mirror coordinate system, and a position between the central prism coordinate system and the star sensor measurement coordinate system; the angle conversion relation between a central prism coordinate system and a star sensor monitoring coordinate system is determined; obtaining an angle conversion relation between a central prism coordinate system and a star sensor monitoring coordinate system and an angle conversion relation between a star sensor measuring coordinate system and a J2000 coordinate system in an on-orbit stage; and determining an angle conversion relation between a central prism coordinate system and a J2000 coordinate system in an in-orbit stage by combining a corresponding relation between a star sensor measurement coordinate system and a star sensor monitoring coordinate system. According to the invention, high-precision load pointing can be obtained.
本发明涉及航天器姿态控制技术领域,特别涉及一种基于夹角监测星敏感器的载荷姿态确定方法及装置,其中方法包括:获取在地阶段的基准镜坐标系与星敏感器测量坐标系之间、中央棱镜坐标系与基准镜坐标系之间,以及中央棱镜坐标系与星敏感器监测坐标系之间的角度转换关系;获取在轨阶段的中央棱镜坐标系与星敏感器监测坐标系之间,以及星敏感器测量坐标系与J2000坐标系之间的角度转换关系;结合星敏感器测量坐标系与星敏感器监测坐标系之间的对应关系,确定在轨阶段中央棱镜坐标系与J2000坐标系之间的角度转换关系。本发明能够获得高精度载荷指向。
Load attitude determination method and device based on included angle monitoring star sensor
基于夹角监测星敏感器的载荷姿态确定方法及装置
2024-04-02
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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