地磁传感器在自旋导弹惯测组合中的应用研究  

Magnetic Sensor Application in IMU of Spinning Missile

作　　者：楼朝飞[1] 张锐[1] 

机构地区：[1]中国航天科工集团公司第二研究院第二总体设计部,北京100854

出　　处：《航天控制》2008年第2期41-46,54,共7页Aerospace Control

摘　　要：为了提高自旋导弹控制的性能,采用自旋导弹的惯测组合来扩充实时测量导弹在飞行过程中运动状态的能力。由于目前速率陀螺的量程和精度都不能满足测量自旋导弹大旋转速度的需求,因此在惯测组合中用地磁场传感器代替速率陀螺来测量绕弹体纵轴的角速度。本文主要利用地磁场传感器组合对自旋导弹滚转角、滚转周期的确定原理及工程可实现性进行研究,给出了采用敏感轴分别在弹体坐标系Oy1和Oz1方向的2个地磁场传感器实现自旋角速度测量的结构设计,分析了产生奇异的条件和地磁场传感器惯测组合的可行性,推导了利用地磁场传感器实现滚动角和滚动周期测量的计算公式和计算流程,对所研究的结果通过了实物试验验证。To improve the performances of the controller, inertial measurement unit （IMU） of spinning missile is adopted, which measures the motion state during missile flight. The rate gyro can not be used to measure the spinning rate because of its narrower range and lower precision. So the magnetic sensor is a- dopted in the IMU. The thesis focuses on how to determine the roll angle and the roll period with the magnetic sensor. The construction design is brought forward. The condition of singularity and the feasibility of magnetic IMU are analyzed. At last the model for computing the roll angle and the roll period is proposed. Its validity is proved by simulation.

关 键 词：自旋导弹 惯测组合 地磁传感器 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]