喷管喉衬结构瞬态温度测量及导热反问题方法应用

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1253-1258.

喷管喉衬结构瞬态温度测量及导热反问题方法应用

孙　娜,马新建,陈　悦,娄德全,牛　禄,唐奇志

上海航天动力技术研究所，上海 201109;上海航天动力技术研究所，上海 201109;上海航天动力技术研究所，上海 201109;上海航天动力技术研究所，上海 201109;上海航天动力技术研究所，上海 201109;上海航天动力技术研究所，上海 201109

发布日期:2021-08-15
作者简介:孙　娜(1983—)，女，硕士，工程师，研究领域为火箭发动机设计及仿真。
基金资助:
上海市自然科学基金(14ZR1440000)；上海市科委优秀技术带头人计划(BXD1423700)。

Transient Temperature Measurement of Nozzle Throat Insert and Application of Inverse Heat Conduction Problem Method

Shanghai Space Propulsion Technology Research Institute，Shanghai 201109，China;Shanghai Space Propulsion Technology Research Institute，Shanghai 201109，China;Shanghai Space Propulsion Technology Research Institute，Shanghai 201109，China;Shanghai Space Propulsion Technology Research Institute，Shanghai 201109，China;Shanghai Space Propulsion Technology Research Institute，Shanghai 201109，China;Shanghai Space Propulsion Technology Research Institute，Shanghai 201109，China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得实时可靠的固体火箭发动机喉衬结构瞬态温度，采用内埋快响应烧蚀热电偶对发动机喉衬结构瞬态温度进行测量，并应用导热反问题方法(Beck序列函数法)计算其喉部内壁面温度和热流密度。采用的试验方案有效避免了传感器探头与喉衬内壁面烧蚀速率不同而干扰流场或中途烧毁等现象发生。试验结果显示越靠近内壁面的测量点温度峰值越高，测点温度瞬态变化与发动机工作状态同步性越好。计算结果显示，计算的平均误差为5.6%，最大误差为7.9%，其内壁温度最高出现在发动机工作结束时，热流密度在0.1s内迅速上升，而后又迅速下降，最大值约为30MW/m2。在发动机停止工作2s后，喉衬开始向外界传热。

关键词: 固体火箭发动机；喉衬；温度测量；导热反问题方法

Abstract: In order to obtain the reasonable temperature of the nozzle throat insert in the SRM，the embedded fast-response Eroding thermocouple is used to measure the transient temperature of the nozzle throat insert structure. And the inverse heat conduction problem method (Beck’s sequence function method) is also applied to calculate the temperature and the heat flux of the throat internal surface. In this experiment，both the disturbed flow field caused by the different erosion rate between the thermocouple and the throat internal surface and the burning phenomenon of the thermocouple are avoided. The experimental results show that when the measured point is closer to the internal surface，the temperature is higher，and the synchronism to the state of the motor is better. The numerical results show that the average error is around 5.6%，and the maximum error is 7.9%. In addition，the internal surface temperature reaches its maximum at the end of the working. The heat flux increases rapidly within 0.1s and decreases at the rest of time. The maximum of heat flux is about 30MW/m2. The throat insert begin to transfer heat to the environment within 2s after the SRM stops working.

Key words: Solid rocket motor；Throat insert；Temperature measurement；Inverse heat conduction problem method

孙　娜,马新建,陈　悦,娄德全,牛　禄,唐奇志. 喷管喉衬结构瞬态温度测量及导热反问题方法应用[J]. 推进技术, 2014, 35(9): 1253-1258.

SUN Na,MA Xin-jian,CHEN Yue,LOU De-quan,NIU Lu,TANG Qi-zhi. Transient Temperature Measurement of Nozzle Throat Insert and Application of Inverse Heat Conduction Problem Method[J]. Journal of Propulsion Technology, 2014, 35(9): 1253-1258.

参考文献

[1] 翁中杰,孙传铮,孙南生,等.小型固体火箭发动机喷管内壁表面瞬态温度的测量[J].推进技术,1984,5(1): 51-55.
[2] 杨飒,李江,王文彬.C/C喉衬烧蚀性能的实验研究[J].固体火箭技术,2009,32(3): 284-287.
[3] 黄一忱.火箭发动机喷管喉部和扩散段的温度测量和传热计算[J].飞航导弹,1986,(SI): 63-71.
[4] Nanigian J,Nanigian D.A Unique Thermocouple to Measure the Temperatures of Squibs,Igniters,Propellants and Rocket Nozzles[J].Proc of SPIE,2006,6222(3): 1-6.
[5] 何洪庆,王思民.固体发动机喷管烧蚀和温度场测量[J].固体火箭技术,1993,(3): 31-36.
[6] 李宏顺,张俭.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,(33): 94-98.
[7] Beck J V,Blackwell B,St Clair C R.Inverse Heat Conduction-Ill Posed Problem[M].New York:Wiley-Interscience,1985: 218-243.
[8] Beck J V.User’s Manual for Conta-Program for Calculating Surface Heat Fluxes from Transient Teperatures Inside solids[R].SAND 83-7134.
[9] Ott L J,Hedrick R A.ORINC: A One Dimensional Implicit Approach to the Inverse Heat Conduction Problem[R].NTIS Reprot ORNL/NUREG-23,1977.
[10] Reinhard H J,Hao D N.Sequential Approximation to Nonlinear Inverse Heat Conduction Problems[J].Mathematical and Computer Modelling,1994,20(10/11): 189-200.
[11] Blackwell B.User’s Manual for the Sandia One-Dimensional Direct and Inverse Thermal(SODDIT) Code[R].Sandia National Laboratories Internal Report of Div,7537,1983.
[12] France D M,Chiang T.Analytic Solution to Inverse Heat Conduction Problem with Periodicity[J].Journal of Heat Transfer,1980,102: 579-581.
[13] 杨冬,陈听宽.导热反问题方法在计算瞬态传热过程中的应用[J].核动力工程,1997,(6).
[14] 张中礼,李明海.计算外壁热响应的非线性瞬态导热反问题方法[J].航天器环境工程,2009,(2).
[15] 陶文铨.数值传热学[M].西安:西安交通大学出版社,2001.(编辑:张荣莉)收稿日期:2013-09-20；修订日期:2013-11-11。基金项目:上海市自然科学基金(14ZR1440000)；上海市科委优秀技术带头人计划(BXD1423700)。作者简介:孙娜(1983—),女,硕士,工程师,研究领域为火箭发动机设计及仿真。E-mail:38141109@qq.com