基于双视场弹载星敏感器的姿态测量及误差分析  

Attitude determination of missile based on dual FOVS sensor

作　　者：刘朝山[1] 肖松[1] 马涛[1] 刘光斌[1] 

机构地区：[1]西安市第二炮兵工程学院,陕西西安710025

出　　处：《红外与激光工程》2007年第z2期540-543,共4页Infrared and Laser Engineering

摘　　要：姿态测量是导弹导航、制导系统的重要组成部分,为提高弹载星敏感器测量姿态的精度,提出了基于双视场星敏感器测量导弹姿态的方法。首先,由单个视场中的导航星求得每一个视轴的方位,然后通过双视轴矢量求得弹体在赤道惯性坐标系姿态,由发射点惯性系和赤道惯性系的关系,可得到导弹在发射点惯性系的姿态,并给出了具体数学表达式。最后,定量分析了双视场中星数目对姿态精度的影响,对合理采用姿态数据,提高测量精度有一定的指导意义。Attitude determination of missile is the key part of the guidance and control.To improve the measuring precision of attitude,the method based dual FOVs star sensor is proposed.First,each orientation of the dual FOVs bore sight is obtained by the position vectors of stars within a single FOV.Then,the two vectors of bore sight are used to determine the attitude in the celestial reference frame(CRF),the missile attitude in the launch inertial coordinate frame(LICF) is obtained by the relationship between CRF and LICF.At last,the relation between the measuring precision of attitude and the number of stars in FOV is analyzed;the result is useful to improve the measuring precision by filtering the data of attitude.

关 键 词：姿态测量 双视场弹载星敏感器 误差分析 

分 类 号：V448[航空宇航科学与技术—飞行器设计] U666.11[交通运输工程—船舶及航道工程]