一种星光折射卫星自主导航系统方案设计  

A Scheme Design of Satellite Autonomous Navigation System Based on Stellar Refraction

作　　者：宁晓琳[1,2,3] 王龙华[1,2,3] 白鑫贝[1,2,3] 房建成[1,2,3] 

机构地区：[1]惯性技术重点实验室,北京100191 [2]新型惯性仪表与导航系统技术国防重点学科实验室,北京100191 [3]北京航空航天大学仪器科学与光电工程学院,北京100191

出　　处：《宇航学报》2012年第11期1601-1610,共10页Journal of Astronautics

基　　金：国家自然科学基金(60874095);北京市优秀博士学位论文指导教师科技项目(YB20091000601)

摘　　要：利用星光折射间接敏感地平的卫星自主导航方案具有导航精度高、自主性强的特点,是一种极具应用潜力的自主导航方案。在基于星光折射的自主导航方案中,折射星的准确识别与折射角的精确获取是实现高精度导航的基础。提出了一种基于双星敏感器,利用连续高度星图模拟与匹配技术实现高精度折射星识别和折射角获取的方法,并在此基础上设计了一种新颖的基于星光折射的卫星自主导航系统方案。同时,为了验证该方案的可行性,设计了相关的折射星仿真程序,以轨道高度为686km的对地观测卫星为例进行计算机仿真验证,结果表明在星敏感器精度为3″时,该导航系统平均位置误差约为145m,最大位置误差不超过400m。Satellite navigation based on stellar refraction has a great potential in application for its high accuracy and independence. Identification of refracted star and determination of refraction angle are the basis for high accuracy navigation. A new method for refracted star identification and refraction angle determination through star pattern simulation and recognition using two star sensors is proposed. Accordingly, a novel satellite autonomous navigation scheme based on stellar refraction is designed. To verify the feasibility of the proposed scheme, a simulation program of refracted star is presented, and an earth-pointing three-axis stabilized satellite with orbit altitude of 686km is used as an example in this paper for computer simulation. The results show that the accuracy of the proposed navigation scheme is better than 200m when the accuracy of star sensor is 3＂.

关 键 词：卫星自主导航 星光折射 星图识别 星图模拟 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]