摘要
星敏感器是一种高精度的姿态测量仪器,本文在分析星敏感器姿态测量原理的基础上,利用序贯平差方法确定航天器姿态并予以实现。仿真结果表明,该算法能满足实时姿态确定的精度要求,且降低了数据存储量,节省了存储单元,具有较强的灵活性。
Star sensor is high precision attitude measurement equipment.This paper uses the iterative least square to calculate the attitude of spacecraft based on the fundamental theory of attitude measurement.Simulation result indicates this method is effective.It reduces the storage data,saves the storage cell and meets the request for accuracy of attitude determination.
出处
《现代测绘》
2009年第1期17-18,21,共3页
Modern Surveying and Mapping
关键词
星敏感器
姿态测量
序贯平差
Star Sensor
Attitude Measurement
Iterative least square
