摘要
对基于紫外敏感器的卫星自主导航方法进行了研究 ,给出了自主轨道确定的滤波算法。对基于紫外敏感器的导航在地球中低轨道、大椭圆轨道和同步轨道上的应用进行了数学仿真验证。仿真结果表明 ,导航误差主要取决于地心方向的测量误差 ,而地心距测量误差的影响要小得多。在已知卫星惯性姿态的条件下 ,仅以地心方向为观测量 ,滤波器同样能够收敛 ,并能获得较高的定轨精度。
The ultraviolet sensor based autonomous n av igation for spacecrafts is studied, and the orbit determination procedure are de tailed. When direction and distance of the earth center vector in inertial frame is input to the navigation filter, attitude information is required. The naviga tion scheme can operate over a large regime including geosynchronous orbit. The simulation results show that the navigation error is dominated by uncertainty of earth direction. Without range measurements, the navigation filter can also con verge to acceptable accuracy. <
出处
《航天控制》
CSCD
北大核心
2004年第3期35-39,共5页
Aerospace Control
关键词
自主导航
紫外敏感器
轨道确定
Autonomous navigation Ultraviolet sensor Orbi t determination
