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火箭技术

火箭发动机起动过程动力学研究

  • 陈艳霞 ,
  • 关世玺 ,
  • 唐家鹏
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  • 1 太原科技大学应用科学学院,太原 030024
    2 中北大学机电工程学院,太原 030051

陈艳霞(1977-),女,天津人,讲师,硕士,研究方向:火箭发动机过渡过程动力学。

收稿日期: 2009-11-25

  网络出版日期: 2025-05-28

The Research of Start Dynamics for Rocket Engine

  • CHEN Yanxia ,
  • GUAN Shixi ,
  • TANG Jiapeng
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  • 1 School of Applied Scienc, Taiyuan University of Science and Technology, Taiyuan 030024, China
    2 School of Mechaeronics Engineering, North University of China, Taiyuan 030051, China

Received date: 2009-11-25

  Online published: 2025-05-28

摘要

根据新一代液体火箭发动机特点,建立系统主要组件的动态数学模型。考虑推进剂的低温特性,对发动机的起动过程进行了仿真研究,计算方法采用龙格-库塔法。仿真结果表明数学模型合理,从而为判断系统能否稳定工作提供依据。同时也为发动机设计、改进和试验提供一定的指导意义。

本文引用格式

陈艳霞 , 关世玺 , 唐家鹏 . 火箭发动机起动过程动力学研究[J]. 弹箭与制导学报, 2010 , 30(5) : 131 -132,136 . DOI: 10.15892/j.cnki.djzdxb.2010.05.038

Abstract

According to the new-developed liquid rocket engine feature,the dynamic mathematic model of main system component was built.Considering low temperature characteristics of the propellant,the start process of the engine was researched.The method of characteristics and classical Runge-Kutta was adopted for system model.Result shows that the model is reasonable,and provides criterion for judging whether the system can work steadily,and can be a guide for design,improvement and experiment.

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参考文献

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JR Mason, R D Southwick. Large Liquid rocket engine transient performance simulation system[J]. N91-24340, 1989.
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张黎辉. 补燃循环液体火箭发动机系统的响应特性研究[J]. 航空动力学报, 1999. 14 (4): 546- 549.
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尘军. 液氢液氧高压补燃发动机系统和瞬变特性研究[D]. 航天科技集团11所, 2002.
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颜庆津. 数值分析[M]. 北京:北京航空航天大学出版社, 1999.
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