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针对大椭圆轨道卫星在轨运行中特殊光照条件导致的能源供给、热控设计等工程研制难点,兼顾光照时间和遥感任务,提出将基于太阳矢量与地面物点矢量的日地观测坐标系作为卫星姿态控制的基准坐标系。研究了相应的卫星姿态运动学,针对日地观测坐标系的角速度矢量在物理层面难以写出解析表达式的问题,提出一种解析计算方法,给出了算法流程,推导了日地观测坐标系相对惯性坐标系的角速度矢量在惯性坐标系中的计算公式。与数值差分法的仿真对比结果表明:该解析算法正确可行,其曲线特性和计算精度优于数值差分法。研究对卫星研制具有理论意义和应用价值。
In view of the difficulties of engineering such as energy supply and thermal control design due to special lighting conditions in on-orbit of large-elliptical orbit satellite, taking into consideration the illumination time and remote sensing tasks, the paper proposes that the solar-earth observation coordinate system based on solar vector and ground object point vector be used as satellite The coordinate system of attitude control. The corresponding satellite attitude kinematics is studied. In order to solve the problem that the angular velocity vector of the observational coordinate system in Japan and Earth can not be easily expressed in the physical level, an analytical method is proposed and the algorithm flow is given. The Calculation Formula of Angular Velocity Vector of Relative Inertial Coordinate System in Inertial Coordinate System. Compared with the numerical difference method, the simulation results show that this method is correct and feasible, and its curve characteristics and accuracy are better than the numerical method. Research on satellite development has theoretical significance and application value.