伪陀螺/星敏感器组合双体卫星姿控系统  

Pseudo-gyro/star tracker combination for dual-body satellite attitude control system

作　　者：刘海颖[1] 王惠南[1] 刘新文[1] 

机构地区：[1]南京航空航天大学自动化学院,江苏南京210016

出　　处：《系统工程与电子技术》2007年第9期1510-1513,共4页Systems Engineering and Electronics

基　　金：教育部博士点基金资助课题(20030287005)

摘　　要：针对双体卫星姿态控制系统,给出了"伪陀螺"概念,及其与星敏感器组合的姿态确定方法,其中伪陀螺是使用卫星内部传感器的测量以及卫星参数来进行动态模型的实时软计算,跟踪系统角动量进而得到角速度。首先建立了双体卫星模型,并设计了动量轮控制律,在此基础上根据星敏感器的测量信息,应用广义卡尔曼滤波器来估计姿态和角速率漂移误差,进而对伪陀螺和惯性陀螺进行校正。仿真结果表明本文的姿态确定方法,对双体卫星的姿态控制系统是非常有效的。The ‘Pseudo-gyro＇ concept and attitude determination using pseudo-gyro combined with star tracker are presented for the dual-body satellite attitude control system. Pseudo-gyro is a real-time soft calculation based on dynamic model using internal sensors and known satellite parameters, which tracks the system angular momentum so that angular rates are determined. First the dual-body satellite model is established and the control laws of reaction wheel are designed. Based on this the extended Kalman filter estimators with attitude sensor updated by star tracker are designed to provide error corrections for the pseudo-gyro and inertial gyro. The effectiveness of the proposed method is demonstrated through the simulation on the dual-body satellite.

关 键 词：双体卫星 伪陀螺 星敏感器 广义卡尔曼滤波 姿态控制 

分 类 号：U666.1[交通运输工程—船舶及航道工程]