基于最小二乘的航天器天文导航定姿算法研究  

Research on attitude algorithm for spacecraft celestial navigation based on the least squares method

作　　者：王易南 闫杰[1] 温琦[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《电子设计工程》2015年第5期58-60,共3页Electronic Design Engineering

基　　金：国家自然科学基金(90816027);航空基金(20135853037);航天支撑基金(2013HTXGD;2014HTXGD)

摘　　要：星敏感器是目前精度最高的姿态测量仪器之一,具有自主性和稳定性,是航天器主要的定姿设备。研究采用最小二乘法对星敏感器的测量信息进行处理得到航天器姿态信息,通过数字仿真证明姿态精度可以达到角秒级,为某工程型号应用提供理论依据。Star sensor is one of the highest precision attitude measurement instruments at present, which has the autonomy and stability. It＇s the main spacecraft attitude determination device. Dealing with star sensor measurement information using the least squares method to process spacecraft attitude is researched. The digital simulation shows that the attitude accuracy can reach to arcsecond level. It provides a theoretical basis for the application of certain project types.

关 键 词：星光定姿 天文导航 最小二乘 数字仿真 

分 类 号：TN96[电子电信—信号与信息处理]