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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 measurement is an important part of missile guidance and guidance system. In order to improve the accuracy of the attitude measurement of the missile, the method of missile attitude measurement based on dual-field star sensor is proposed. Firstly, the azimuth of each visual axis is obtained from the navigation star in a single field of view, and then the attitude of the projectile in the equatorial inertial coordinate system is obtained from the binocular vector. The relationship between the inertial system of the launch point and the equatorial inertial system can be obtained Missile inertial system at the launch point attitude, and gives the specific mathematical expressions. Finally, the quantitative analysis of the influence of the number of stars in the dual-field on attitude accuracy is of guiding significance for the rational use of attitude data and improvement of measurement accuracy.