宇航学报

宇航学报 ›› 2017, Vol. 38 ›› Issue (10): 1048-1056.doi: 10.3873/j.issn.1000-1328.2017.10.005

• 飞行器设计与力学 • 上一篇    下一篇

减阻增程弹道的射程估算与特性分析

凌王辉，鲜勇，郭玮林，李杰，张大巧   

  1. 火箭军工程大学七系，西安 710025
  • 收稿日期:2017-05-24 修回日期:2017-07-19 出版日期:2017-10-15 发布日期:2017-10-25

Range Estimation and Analysis for Extended Trajectory Based on Drag Reduction Design

LING Wang hui, XIAN Yong, GUO Wei lin, LI Jie, ZHANG Da qiao   

  1. 7th Department, Rocket Force University of Engineering, Xi’an 710025, China
  • Received:2017-05-24 Revised:2017-07-19 Online:2017-10-15 Published:2017-10-25

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摘要：

为实现弹道导弹射程的快速估算和减阻设计后弹道增程的定量分析，提出一种基于导弹基本参数的射程快速精确估算方法。通过建立减阻模型，仿真计算得到气动阻力系数表，并对速度计算公式进行逐项积分，利用高度近似值和气动系数拟合结果得到关机点状态量和射程的初步值，最终通过迭代计算得到满足精度要求的射程结果。仿真结果表明，经过高度和气动系数的迭代计算能有效快速得到满足精度的计算结果，通过减阻设计，导弹射程提高了162.36 km，增程的效果明显。

关键词: 减阻设计, 弹道增程, 射程快速估算, 气动拟合, 迭代计算

Abstract:

In order to realize the quantitative analysis of the trajectory and the evaluation of the extend range by using the drag reduction design, a fast and accurate estimation method is proposed based on the basic parameters of a missile. By establishing a drag reduction model, an aerodynamic drag coefficient table is calculated. Then the speed calculation formula is integrated item by item. The initial value of the state at the shutdown point and the range are obtained by the height approximation and the fitting aerodynamic coefficient. After the iteration, the result satisfies the accuracy requirements of the range. The simulation results show that the heuristic calculation of the height and the aerodynamic coefficients can effectively and quickly get the satisfying results. Under the drag reduction design, the final missile range is increased by 162.36 km and the extended-range effect is obvious.

Key words: Drag reduction design, Trajectory extension, Range rapid estimation, Aerodynamic coefficient fit, Iteration

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