摘要
根据弹道修正弹阻力板的展开控制对于射程偏差预测要求的实时性,提出基于摄动原理的射程偏差预测算法.为解决阻力板修正能力在线计算数据量大的问题,提出在弹载计算机上装定阻力板修正能力表格的方法,给出发射前计算修正能力表格的过程和飞行中使用修正能力表格的步骤,提出阻力板展开时机的优化判断条件,并采用该方法对某型弹道修正火箭弹射程修正控制进行仿真试验和飞行试验.仿真试验结果表明,当目标射程为33 565.4m时,经修正后火箭弹的射程偏差能控制在20m以内;飞行试验结果表明,弹道修正火箭弹的射程偏差实测为24m,射程精度得到明显提高.
In order to control the drag brakes effectively a real-time impact point prediction algo-rithm based on perturbation theory is presented in this paper.Normally,calculating the correction ability of drag brakes is time-consuming.To save the calculation time the drag brakes correction ability figure is uploaded onto the rocket-borne computer before rockets are fired.Then the proce-dures for calculating the figure and for using the figure are presented.With this method the drag brakes correction ability can be calculated in time.The deployment order of drag brakes is formed by comparing the impact point prediction value with the correction ability value.In order to prove the truth of this control method,simulation and flight test are carried out based on the 122 mm one dimensional traj ectory correction rocket proj ectile.Simulation results show that the corrected distance from the impact point to target is less than 20 m and the flight test results show that when the firing range is 33565.4 m the distance from actual impact point to target is 24 m,and the range density can be improved apparently with this method.
出处
《军械工程学院学报》
2014年第4期19-25,共7页
Journal of Ordnance Engineering College
基金
军队科研计划项目
关键词
摄动原理
射程偏差预测
弹道修正弹
阻力板
perturbation theory
range prediction errors
one dimensional traj ectory correction pro-j ectile
drag brakes
