基于星敏感器的最小二乘估计自主定轨方法  

Least-squares Estimation Autonomous Orbit Determination Method Based on Star Sensor

作　　者：李言俊[1] 王信峰[1] 王彦荣[2] 

机构地区：[1]西北工业大学航天学院,西安710072 [2]西安卫星测控中心,西安710043

出　　处：《系统仿真学报》2008年第21期6006-6008,共3页Journal of System Simulation

基　　金：国家自然科学基金(60575013)

摘　　要：基于星敏感器的航天器自主定轨,不同于基于GPS和跟踪与数据中继卫星系统的自主定轨,它是采用星敏感器对背景恒星的观测资料进行定轨。使用第一类无奇点根数状态微分方程,利用星敏感器视场中的多个恒星以及底片坐标,计算视场中心天球坐标的最优估计值,从而建立条件方程,采用最小二乘估计快速确定航天器的轨道。这种方法可以彻底摆脱航天器定轨对地面测控设备的依赖,实现真正的自主定轨。该方法的实现大大降低了航天任务的成本,同时,可缓解地面测控资源的紧张和冲突问题。It＇s different from the autonomous orbit determination based on GPS or TDRSS, the observation of the background stars in the visual field of star sensor is used in autonomous orbit determination based on star sensor. This method uses the differential equation of the first class zero-singular points root state as well as several stars in the visual field of star sensor and negative coordinate to calculate the optimal coordinate estimation of the central celestial sphere, establishes condition equation, and rapidly determines spacecraft orbit according to least-squares estimation. It enables spacecraft orbit determination independent of ground TT＆C equipments and really realizes autonomous orbit determination. It can substantially reduce the cost of space mission, and simultaneously mitigate the tension of ground TT ＆C resource.

关 键 词：自主定轨 星敏感器 最小二乘 最优估计 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计] V412.4