| 1. | In the stage of the sun and the moon in sight , azimuth of the sun , the earth and the moon in the spacecraft body coordinate system is simulated . combining the simulated azimuth with the ephemeris of the sun and the moon , the state equation and observation equation are modeled . the initial orbital parameters calculated by least square method are used in orbit state equation to predict spacecraft state and to realize autonomous navigation
在日月可见阶段,模拟日、地、月敏感器测量信息,即日、地、月在航天器本体坐标系下的方位信息,结合日月星历,建立状态方程及观测方程,通过最小二乘法得到历元时刻的轨道状态初始值,将其代入轨道状态方程进行自主导航。 |
