基于摄动原理的火箭弹落点实时预测

基于摄动原理，提出了以6自由度弹道方程解算的弹道为火箭弹基准弹道，求解参数扰动引起的落点偏差变化量的落点实时预测方法，并给出了详细解算步骤。将各种扰动系数的解算赋予地面火控计算机，降低了弹载计算机的解算复杂度和解算量。以122 mm火箭弹为例，选取一条基准弹道，分别对无扰动、仅存在初始扰动和全弹道存在随机扰动3种条件下的无控弹道进行了落点预测仿真实验和火箭弹落点预测飞行试验。研究结果表明：该方法在仿真实验和实际飞行试验中都具有较高的预测精度，横向偏差收敛速度较纵向偏差快，其波动幅度在全弹道上较纵向偏差小，而且纵向偏差预测在火箭弹降弧段才趋于收敛；采用该方法进行预测时每次解算时间为167 ns左 右，远小于弹载控制器2 ms的控制周期，实现了实时预测。

Real-time Impact Point Prediction of Rocket Projectile Based on Perturbation Theory

The 6-degrees of freedom trajectory equations for rocket projectiles are established, and a new real-time impact point prediction (IPP) approach is proposed based on perturbation theory. Assuming that the rocket projectile flies along the nominal trajectory without disturbance, the detailed calculation process of the dispersion in impact point is presented. The prediction coefficient is calculated using a fire control computer on the ground, and IPP is carried out using the rocket-borne computer during flight. As a result, the IPP process is simplified. Finally, the simulation and flight tests of 122 mm rockets is accomplished. The results show that its prediction precision is higher under any condition. At the same time, the results demonstrate that the time consumed to predict the impact point is about 167 ns, which is much less than the control cycle time of 2 ms.