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[1]李宏顺,张俭,谭建伟,等.固体火箭发动机喷管喉部瞬态热流的测量技术[J].武汉工程大学学报,2011,(12):94-98.
　LI Hong shun,ZHANG Jian,TAN Jian wei,et al.Measuring technique for transient heat flux at inner surface ofthroat insert of solid rocket motor nozzle[J].Journal of Wuhan Institute of Technology,2011,(12):94-98.
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《武汉工程大学学报》[ISSN:1674-2869/CN:42-1779/TQ]

卷:
期数:
2011年12期
页码:
94-98
栏目:
机电与信息工程
出版日期:
2011-12-30

文章信息/Info

Title:
Measuring technique for transient heat flux at inner surface of
throat insert of solid rocket motor nozzle
文章编号:
16742869(2011)12009405
作者:
李宏顺1; 2; 张俭1; 谭建伟1; 杜瑞兵1; 王刚1; 张海龙1
1.中国航天科工集团第六研究院41所，内蒙古 呼和浩特 010010；
2.武汉工程大学理学院，湖北 武汉 430074
Author(s):
LI Hongshun1; 2; ZHANG Jian1; TAN Jianwei1; DU Ruibing1; WANG Gang1; ZHANG Hailong1
1.The 41st Institute of the 6th Academy of CASIC,Huhhot 010010,China;
2.School of Science,Wuhan Institute of Technology,Wuhan 430074,China
关键词:
固体火箭发动机; 喷管; 传热; 测量
Keywords:
solid rocket motor; nozzle; heat transfer; measurement
分类号:
V435
DOI:
-
文献标志码:
AAdoi:10.3969/j.issn.16742869.2011.12.023
摘要:
改进了美国Nanmac公司的自更新快速响应热电偶，并将改进后的热电偶用于测量固体火箭发动机喷管喉衬内壁面上的瞬态温度和热流密度.测量是在一小型试验发动机上进行的，其喷管喉径为18 mm.分别采用黑火药、双基推进剂和复合推进剂进行了点火试验，试验结果表明本文的测量方法是可行的.
Abstract:
The “self renewing” fast response thermocouple developed by the Nanmac Corporation,USA,was improved,and employed to measure the transient temperature and heat flux density at the inner surface of the nozzle throat insert of a solid rocket motor.Measurements were conducted with a laboratory scale motor,whose inner diameter of throat insert was 18 mm.Ignition tests were conducted with black powder,double base propellant and composite propellant respectively.The experimental results show that the present measuring technique is feasible.

参考文献/References:

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