中国空间科学技术

• • 上一篇    下一篇

非圆轨道卫星实现共面悬停的方法

闫野;朱亚文;   

  1. 国防科学技术大学航天与材料工程学院;
  • 发布日期:2010-04-25

Coplanar Hovering Method over Space Target on Non-circular Orbit

Yan Ye Zhu Yawen(College of Aerospace and Material Engineering,National University of Defense Technology,Changsha 410073)   

  • Online:2010-04-25
  • Supported by:
    国家863课题资助(2007AA704304)

被引次数

21

摘要： 通过矢量控制,使任务卫星始终在目标卫星的轨道平面内飞行,同时保证"任务卫星-目标卫星-地心"的夹角和两颗卫星间的相对距离保持不变,从而实现共面悬停飞行。重点进行了任务卫星悬停飞行的动力学理论分析,推导了悬停飞行过程中任务卫星相对于目标卫星的径向和切向加速度需求,给出了开环控制方案,对不同悬停任务的能量需求进行了对比分析,最后对悬停飞行过程进行了动力学仿真。

关键词: 共面悬停, 非圆轨道, 控制方法, 能量需求, 卫星

Abstract: The mission satellite is always forced to fly in the orbital plane of the target satellite by using vector control technique.At the same time,the angle of mission satellite to target satellite to geocenter,and the objective distance between two satellites will keep constant.So the coplanar hovering orbit was achieved.The dynamic theoretical analysis of the hovering orbit was conducted.Then the radial and tangential acceleration requirements during the hovering process were deduced,and the open loop orbit control strategy was proposed.After that the energy requirements of different hovering tasks were analyzed.The dynamic simulation of the hovering process was conducted to validate the theoretic results.