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弹箭与制导学报 >

2020 , Vol. 40 >Issue 3: 79 - 84

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2020.03.019

双脉冲发动机对火箭弹增程可行性分析

  • 苟秋雄 1 ,
  • 王伟 1 ,
  • 杨晓英 2 ,
  • 胡晓明 1
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  • 1 西安现代控制技术研究所, 西安 710065
  • 2 西安导引科技有限责任公司, 西安 710065

苟秋雄(1976-),男,陕西西安人,高级工程师,硕士,研究方向:制导火箭总体设计。

收稿日期: 2019-05-23

  网络出版日期: 2025-02-12

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Research on the Feasibility of Extending Rocket’s Range Using Dual-pulse Solid Rocket Motor

  • GOU Qiuxiong 1 ,
  • WANG Wei 1 ,
  • YANG Xiaoying 2 ,
  • HU Xiaoming 1
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  • 1 Xi’an Modern Control Technology Research Institute, Xi’an 710065, China
  • 2 Xi’an Guidance Technology Co. Ltd, Xi’an 710065, China

Received date: 2019-05-23

  Online published: 2025-02-12

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摘要

火箭弹的射程受传统固体火箭发动机技术发展的制约,在高能推进剂技术没有明显改善的情况下,进一步提高火箭弹的射程变得越来越困难。文中首先对影响火箭弹射程的主要因素进行了分析,对采用不同发动机技术在不同射程火箭弹的阻力系数、飞行速度和附加推力等影响因素进行逐一分析,并对采用双脉冲发动机技术的火箭弹增程能力进行仿真分析,仿真结果证明采用双脉冲发动机技术可以有效增加火箭弹的射程。

关键词： 双脉冲火箭发动机; 火箭弹; 射程; 弹道; 气动力

本文引用格式

苟秋雄 , 王伟 , 杨晓英 , 胡晓明 . 双脉冲发动机对火箭弹增程可行性分析[J]. 弹箭与制导学报, 2020 , 40(3) : 79 -84 . DOI: 10.15892/j.cnki.djzdxb.2020.03.019

Abstract

The range of rockets is constrained by the development of traditional solid rocket technology. In the absence of significant improvement in high-energy propellant technology, it has become increasingly difficult to further increase the range of rockets. This paper first analyzes the main factors affecting the range of rockets, and analyzes the resistance coefficient,speed and additional thrust factors of rockets with different solid rocket technology. Simulation results show that using dual-pulse rocket motor can effectively increase the range of the rocket.

Key words： dual pulse rocket motor; rocket; range; ballistic; aerodynamic force

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序
[1]
孙超, 张琳, 严聪, 等. 双脉冲固体火箭发动机概况[J]. 飞航导弹, 2013(8):72-77.

[2]
NAUMANN K W, STADLER L, TROUILLOT P, et al. Double-pulse solid rocket technology at Bayern-Chemie/Protac:AIAA 2006-4761[R]. Redston: AIAA Inc., 2006.

[3]
STADLER Ludwig, TROUILLOT P, RIENACKER C, et al. The dual pulse motor for LFK NG:AIAA 2006-4726[R]. Redston: AIAA Inc., 2006.

[4]
毕世龙, 陈延辉. 多脉冲发动机研究[J]. 飞航导弹, 2011(9):88-92.

[5]
张毅. 弹道导弹弹道学[M]. 长沙: 国防科技大学出版社, 1999:32-98.

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