摘要
研究航天器自主导航的优化测试问题,针对我国的GEO轨道及施加小推力后的航天器自主导航的研究却很少。对GEO轨道航天器来说,若其不在我国测站测控范围内,则难以实现轨道测控。针对上述问题,提出采用地平仪和星敏感器的自主导航方案。同时,考虑众多的GEO轨道航天器采用高比冲电推进技术用于位置保持以及寿命末期离轨,还研究了在沿轨道速度方向连续小推力作用期间的自主导航问题。通过仿真,结果表明采用地平仪和星敏感器以及推广卡尔曼滤波的自主导航方法可以适用于GEO轨道航天器。
At present, most of GEO orbit spacecrafts use the method of ground - based monitoring to achieve orbit determination. As to our country, if the spacecraft is out of the monitoring and control scope of domestic stations, the orbit control of spacecraft is hard to achieve. In view of the above question, this article has proposed a method of autonomous navigation for GEO orbit spacecraft based on the horizon and star sensor. In addition, considering numerous GEO orbit spacecrafts using high specific impulse electric propulsion technology to hold position and to be deorbited at the end of life process, this paper has also studied the autonomous navigation problem in the condition that the track of continuous small thrust is along the speed direction. Through the simulation analysis, autonomous navigation method that based on the angle measurement and extended Calman filter can be applied to GEO orbit spacecraft.
出处
《计算机仿真》
CSCD
北大核心
2012年第12期85-89,共5页
Computer Simulation
