火箭外弹道特征点修正解算方法研究

秦华伟; 王华

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火箭外弹道特征点修正解算方法研究

机械与动力工程 | 更新时间：2026-09-14

- 火箭外弹道特征点修正解算方法研究
- Study on the Correction Calculated Method Based on the Exterior Projectile Trajectory Feature Point
- 中北大学学报（自然科学版） 2013年34卷第4期页码：386-392
- 作者机构：
  
  1. 中北大学机电工程学院
  2. 北京航空航天大学宇航学院
- 作者简介：
- 基金信息：
  
  总装预研项目
- DOI：
  中图分类号：
- 纸质出版：2013
- 稿件说明：
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秦华伟, 王华. 火箭外弹道特征点修正解算方法研究[J]. 中北大学学报（自然科学版）, 2013,34(4):386-392.

秦华伟, 王华. Study on the Correction Calculated Method Based on the Exterior Projectile Trajectory Feature Point[J]. 2013, 34(4): 386-392.
秦华伟, 王华. 火箭外弹道特征点修正解算方法研究[J]. 中北大学学报（自然科学版）, 2013,34(4):386-392. DOI：

秦华伟, 王华. Study on the Correction Calculated Method Based on the Exterior Projectile Trajectory Feature Point[J]. 2013, 34(4): 386-392. DOI：

摘要

采用二自由度的质点弹道微分方程组

对火箭弹弹道特性以及弹道诸元的求解方法进行了研究.在合理选择适用于二维弹道修正的火箭弹弹道运动模型的基础上

利用插值解析法求解弹道诸元的数据后

提出了针对火箭外弹道特征点修正解算的方法

并对射程修正量和方位修正量进行了仿真计算.仿真计算结果表明:当修正处于弹道升弧段

射角小于等于45°和大于等于50°时

射程横向修正量出现相反情况

降弧段修正所产生的横向修正量无此关系.这说明处在升弧段的修正所产生的射程横向修正量与修正时的初始弹道倾角有关.这也为以后执行机构对火箭弹的运动轨迹进行一次或多次修正提供了理论计算参考依据.

Abstract

The rocket trajectory characteristics and the solving methods based on firing data of projectile were researched based on 2-freedom-degree differential equations about ballistic particle.Based on the reasonable selection of rocket's trajectory model suited in two-dimensional trajectory correction

when resolving the data of external trajectory characteristic point using the analytical method of interpolation

a method for solving trajectory data was presented

and the corrections of range and azimuth correction were simulated and calculated.The simulation results show that

when the correction is carried on in the ballistic rise department

lateral correction appear on the contrary between angle of fire is less than or equal to 45° and that more than or equal to 50°.But there is no such relationship in the ballistic degressive department.This shows that the lateral correction of range in the rise department is in connection with the initial trajectory angle.This method provides one kind of theory evidence to the actuator correcting the rocket trajectory for one or more times.

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references

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