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膏体推进剂火箭发动机点火特性
Ignition Characteristics of Pasty Propellant Rocket Engine
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中文摘要:
      为研究膏体推进剂火箭发动机点火工作特性,推导了膏体推进剂燃面变化模型和各阶段燃面方程,编制了发动机点火特性参数计算程序,计算了不同输运管道孔径以及膏体推进剂初始堆积量下瞬态燃烧室压力。设计了膏体推进剂火箭发动机热试车试验系统,成功进行了点火试验,分析了膏体推进剂火箭发动机点火工作过程中四个阶段的特性。结果表明: 燃烧室平均压强的计算结果与试验数据吻合较好,计算误差小于5.7%,该计算程序适用于膏体推进剂火箭发动机点火特性参数计算;膏体推进剂初始堆积量增加一倍,初始压力峰值平均增加42.8%;输运管道孔径减小60%,初始燃烧时间平均减小66.5%,余药燃烧时间平均下降26.1%。发动机点火试验时,减小膏体推进剂初始堆积量,可降低燃烧室初始压力峰、增大稳定燃烧时间,另外减小输运管道孔径,可明显增大发动机稳定燃烧时间。
中文关键词: 膏体推进剂  燃面模型  火箭发动机  点火特性
英文摘要:
      In order to study the ignition operating characteristics of the pasty propellant rocket engine, the burning surface change model of pasty propellant was built, and regression equations of pasty propellant were deduced in each stage. The calculating procedure was programmed and the transient pressure of combustion chamber under different transport pipeline diameter and pasty propellant initial accumulation was calculated. Also, the ignition tests were carried out successfully based on a pasty propellant rocket launch test system, and the ignition characteristics of the rocket engine in each working stage were analyzed. Results show that the data calculated by the procedure are in good agreement with the experimental and the maximum absolute error are 5.7%. When the pasty propellant initial accumulation doubled, the initial pressure peak increases by 42.8%. Under the same condition, as the diameter of the pipeline decreases by 60%, the initial combustion time and residual combustion time decrease by an average of 66.5% and 26.1%. The initial pressure peak can be decreased and stable burning time can be increased by reducing the initial packing quantity of pasty propellant, in addition, the stable burning time can be increased apparently by reducing the diameter of transport pipeline.
英文关键词: pasty propellant  regression model  rocket engine  ignition characteristics
DOI:10.11943/j.issn.1006-9941.2017.12.009
投稿日期:2017-03-27
最后修改日期:2017-06-28
网络出版日期:2017-12-27
书版出版日期:2018-01-29
基金项目:国家自然科学基金资助(51606098)
引用文献:叶小兵,陈雄,单新有,周长省,秦振杨,等.膏体推进剂火箭发动机点火特性[J].含能材料,2017,25(12):1025~1030
作者单位E-mail
叶小兵 南京理工大学 机械工程学院,江苏 南京 210094 yexbchina@163.com,chenxiong@njust.edu.cn 
陈雄 南京理工大学 机械工程学院,江苏 南京 210094 chenxiong@njust.edu.cn 
单新有 南京理工大学 机械工程学院,江苏 南京 210094  
周长省 南京理工大学 机械工程学院,江苏 南京 210094  
秦振杨 南京理工大学 机械工程学院,江苏 南京 210094  
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