基于雷达测量数据的弹箭扰动源最优估计

为精确计算舰载武器的飞行状态参数,以弹体纵向运动过程为研究对象,推导了包含误差干扰源在内的纵向扰动运动学方程,利用"系数冻结法"及拉普拉斯变换得到解析解,拟合出弹体被动段纵向运动的气动参数公式,采用三坐标雷达测量量作为系统量测方程,从而对气动参数误差干扰源进行最优估计。计算结果表明:该算法可以使俯仰操纵力矩系数导数误差的精度稳定在±0.007(°)~(-1)范围内,阻力系数误差的精度趋于±0.025之间;升力系数误差基本稳定在±0.12之间;俯仰力矩系数对攻角的导数偏差精度稳定在±0.011(°)~(-1)之间;俯仰阻尼力矩系数误差的精度收敛于±0.009(°)~(-1)之间,且算法收敛速度快,可为重构高精度的弹道参数提供支撑。

Optimal estimation of missile disturbance source based on radar measurement data

In order to calculate the flight state parameters of shipborne weapons accurately, the equations of longitudinal perturbation kinematics with error disturbance source are deduced based on the longitudinal motion process of the missile. The "coefficient freezing method" and the Laplace transform are used to analyze the motion equation solution. The aerodynamic parameter formula of the longitudinal motion during passive phase is fitted out, and the measurements of the coordinate radar are used as the system measurement equation to optimally estimate the aerodynamic parameter error source. Experiment results show that: the algorithm can stabilize the error of the steering torque coefficient to within±0.007 (°)-1, and the accuracy of the resistance coefficient tends to be within±0.025; the lift coefficient error is basically stable to within±0.12; the accuracy of the torque coefficient is within±0.011(°)-1; the accuracy of the torque coefficient of the pitching damping converges to within±0.009 (°)-1, and the convergence speed of the algorithm is fast. The proposed algorithm can provide technical references for the reconstruction of high-precision trajectory parameters.