基于MEMS/北斗的火箭弹弹道参数测量方法

摘要

The trajectory of the rocket projectile can be calculated using the BD system measurement,while the inertial parameters can be solved through MIMU.The date fusion based on the unscented kalman filter (UKF) is carried out to deal with the parameters from the BD system and MIMU,with the purpose of increasing accuracy.This paper introduces the measurement method of trajectory parameter,and designs the unscented kalman filter,and the six-degree-of-freedom simulation data of a certain guided rocket is used to validate the integrated navigation scheme.The simulation results show that the MIMU/BD integrated measurement method based on UKF can effectively measure the trajectory parameters of rocket projectile,and the data fusion through the UKF filter can eliminate the data divergence produced by using the inertial navigation alone.Meanwhile,the measurement accuracy is completely satisfied towards the navigation requirement of guided rocket projectile.All these provide the theoretical support for the application of micro inertial devices in the projectile.%利用北斗定位系统计算弹道轨迹,利用MEMS惯性测量单元解算弹道惯性参数,并通过无迹卡尔曼滤波器(UKF)对两者的数据进行数据融合,以提高弹道参数测量的精度.分析了各弹道参数的测量方法,设计了无迹卡尔曼滤波器,并利用某型制导火箭弹的六自由度仿真数据对组合导航算法进行验证.仿真结果分析表明:基于UKF的MEMS/北斗组合测量方案能够有效地对火箭弹的弹道参数进行测量,且通过UKF滤波器进行数据融合能够消除纯惯导测量时数据发散等问题,精度达到制导火箭弹导航要求.对微惯性器件上弹应用提供了一定的理论支持.