摘要
研究了利用惯性导航系统与星敏感器进行组合定姿的方法。首先,分析惯导系统和星敏感器的误差源,选取惯导系统误差作为组合系统的状态,获得系统状态方程。然后,利用惯导系统输出的飞行器位置、速度和姿态等信息来构造恒星矢量等效观测值,将其与星敏感器实际观测到的恒星矢量相减作为量测,构造出量测方程。最后,利用卡尔曼滤波技术,设计惯性/星敏感器组合定姿算法。仿真结果表明,基于惯性/星敏感器的组合定姿方法达到了6角秒的定姿精度,非常适用于空间飞行器的高精度定姿。
The method of integrated attitude determination based on inertial navigation system and star sensor is researched in this paper. Firstly, the error sources of inertial navigation system （INS） and star sensor are analyzed, and the errors of INS are chosen as states of the integrated system, thus system state equations are obtained. Secondly, the position, velocity and attitude information of the aerocraft from INS are used to construct the equivalent observation of the star vector. The difference between the equiva- lent observation and the actual star vector observed by star sensor is chosen as the measurement, and then the measurement equation is constructed. Thus the algorithm of integrated attitude determination is designed by Kalman filtering technology. Simulation results show that, the method of integrated attitude determination based on INS / star sensor has high precision of attitude determination of 6 angle second, it is very fit for the precise attitude determination of space aerocraft.
出处
《航空兵器》
2007年第3期15-19,24,共6页
Aero Weaponry
关键词
惯性导航系统
星敏感器
组合定姿
卡尔曼滤波
inertial navigation system
star sensor
integrated attitude determination
Kalman filter
作者简介
杨波（1980-），男，江苏滨海人，博士研究生，研究方向是导航、制导与控制。
