基于卡尔曼滤波算法的弹箭飞行姿态测试方法

The Test Method of Missiles' Flight Attitude Based on the Kalman Filter Algorithm

提出了一种基于磁强计和陀螺的弹箭飞行姿态测试方法,利用地磁测量、陀螺测量和卡尔曼滤波器来解算姿态角的算法。通过软件分析和处理结果表明:卡尔曼滤波器算法比较适用于高动态短近程的小型飞行体的姿态测量。

This paper presents a test method of missile＇ flight attitude based on magnetometer and gyroscope, which is a algorithm to resolve the attitude angles based on the geomagnetic measurements, the gyro measurement and the Kalman filter. It shows that the algorithm of Kalman filter is suitable for applying to the attitude measurement of the high dynamic and short-range small flight relatively according to the software analysis and processing results.