一种惯性测量装置火箭橇试验误差分离方法

Method to separate errors based on rocket sled test of inertial measurement unit

惯性测量装置火箭橇试验可以提供大过载环境,为标定加速度计高阶误差项系数提供必要条件。为了利用位置外测信息准确辨识加速度计高阶误差项系数,提出一种针对火箭橇试验的惯性测量装置误差模型参数辨识方法。在给出加速度计高阶误差模型后,该方法通过建立惯性测量装置位置遥测误差和误差模型参数间的线性函数关系构建位置环境函数,之后利用最小二乘法估计出误差系数数值。仿真结果表明,该方法在辨识加速度计高阶误差项参数上具有很高的精度;应用该方法对一次火箭橇试验数据进行误差分离后,通过对解算结果进行显著性分析,证明了辨识出的高阶误差项系数的有效性。

The rocket sled test of inertial measurement unit（IMU） can provide strong incentive for accelerometer which is necessary when identifying the parameters in high level error model. Aiming at using the location measurement information when separating the coefficients of the high level error model of IMU in rocket sled test, a parameter identification method was designed. With the accelerometer model, a location environment function was built through establishing the linear equation between the location measure error from the IMU and the parameters in the error model. Then by using the least square method, the values of errors were obtained. The simulation shows that this method is of high accuracy when identifying the parameters of high-level error model. The significance analysis on the parameters identified from a rocket sled test shows the effectiveness of high-level error coefficients.