摘要
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。
The control system of relay terminal usually imports attitude compensation because of the objective existence of attitude errors. Tracking will be interrupted when attitude error exceeds the capability of the relay terminal. Therefore, it is necessary to obtain the relationship between attitude error and pointing error of relay terminal and to model the relay tracking forecast in view of attitude errors. Tracking forecast results got with the proposed method show that the tracking time considering attitude error is shorter and this will always occur when the cross angle be- tween the azimuth axis and relay satellite is smaller.
出处
《飞行器测控学报》
2012年第4期11-14,共4页
Journal of Spacecraft TT&C Technology
