基于四频差动激光陀螺/星敏感器的卫星定姿算法  

A Satellite Attitude Determination Algorithm Based on Four-Mode Differential Laser Gyro and Star Sensor

作　　者：臧强[1] 高晶敏[1] 杨鸿波[1] 关新[2] 陈守磊[2] 

机构地区：[1]北京信息科技大学电子信息与控制实验教学中心,北京100101 [2]北京控制工程研究所,北京100190

出　　处：《电光与控制》2016年第3期87-91,99,共6页Electronics Optics & Control

基　　金：北京市重点学科-检测技术与自动化装置学科建设(5111 523302);北京市属高等学校高层次人才引进与培养计划项目的青年拔尖人才培育计划(IT&TCD201304115)

摘　　要：为了得到更高分辨率的对地观测图像,就得获得比现阶段更高精度的卫星姿态,因此必须解决卫星高频抖动的测量与处理问题。四频差动激光陀螺具有测量卫星高频抖动和低频抖动的全频带测量能力。结合星敏感器测量精度高的优点,提出了四频差动激光陀螺与星敏感器的联合定姿方案。推导了联合定姿方案中的卡尔曼滤波模型,并使用该模型,对四频差动激光陀螺和星敏感器测量的数据进行融合滤波。仿真结果表明,该联合定姿方案实现了宽频带的卫星微振动测量,从而能获得更高精度的卫星姿态。In order to obtain higher resolution images of earth observation, we have to obtain more accurate satellite attitude, thus the measurement and processing of satellite high-frequency jitter must be solved. The four-mode differential laser gyro has the ability to measure the full-band jitter. Considering that the star sensors have the advantage of high measuring accuracy, we put forward a combined attitude determination program based on four-mode differential laser gyro and star sensor. The Kalman filter model of the combined attitude determination program was derived, which was then used for fusion filtering of four-mode differential laser gyro and star sensor measurement data. The simulation results show that the program achieves a broadband satellite micro-vibration measurement, and thus can obtain highly accurate satellite attitude.

关 键 词：四频差动激光陀螺 星敏感器 卫星姿态 高频抖动 卡尔曼滤波 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]