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航天器的姿态控制误差是客观存在的,由于中继终端跟踪能力有限,在某些情况下,姿态误差会导致跟踪中断,从而造成测控资源的浪费并影响正常执行任务。针对姿态控制误差影响中继跟踪的问题,通过对简化姿态旋转矩阵求导,推导出姿态误差与中继终端框架角和角速度的转换关系,得到引入姿态误差的中继终端跟踪预报模型。利用该模型对某航天器中继跟踪情况进行仿真计算,表明:考虑姿态误差情况下,中继跟踪弧段比无扰动情况要短一些,跟踪时间减少的时段发生在天线方位轴与航天器到中继星连线的夹角较小的时候。
Spacecraft attitude control error is objective. Due to the limited tracking ability of relay terminal, in some cases, attitude error will cause tracking interruption, resulting in the waste of monitoring and control resources and affecting the normal execution of tasks. Aiming at the problem that attitude control error affects the tracking of relay, the conversion relation between attitude error and frame angle and angular velocity of relay terminal is deduced by deriving simplified attitude rotation matrix, and the tracking terminal model of relay terminal with attitude error is obtained. The model is used to simulate the tracking of a spacecraft. It shows that under the condition of attitude error, the tracking arc is shorter than the undisturbed one, and the time when the tracking time decreases is between the antenna azimuth and spacecraft arrival When the angle of the relay star connection is small.