火箭燃气射流温度分布的实验研究

推进技术 ›› 2003, Vol. 24 ›› Issue (2): 109-111.

火箭燃气射流温度分布的实验研究

徐强,李军,曹从咏

南京理工大学机械学院江苏南京 210094;南京理工大学机械学院江苏南京 210094;南京理工大学机械学院江苏南京 210094

发布日期:2021-08-15

Experimental study on temperature distribution in rocket exhausted flow field

Coll. of Mechanics, Nanjing Univ. of Science and Technology, Nanjing 210094, China;Coll. of Mechanics, Nanjing Univ. of Science and Technology, Nanjing 210094, China;Coll. of Mechanics, Nanjing Univ. of Science and Technology, Nanjing 210094, China

Published:2021-08-15

摘要/Abstract

摘要： 为了优化火箭发射承载设备的设计,使其避免燃气射流的热损坏。采用细丝热电偶测温的方法,实验研究了某型火箭固体发动机燃气射流的总温分布。结果表明,温度-时间历程曲线中存在若干相对稳定状态,对应于发动机的工作过程的不同阶段,得到了可能发生热损坏的温度分布区域。实验得到的温度分布与理论结构基本相符,与数值模拟存在一定差异。文中简要分析了细丝热电偶的测量误差。

关键词: 火箭排气;喷管气流;温度测量;热电偶;温度分布

Abstract: Temperature distribution of solid rocket exhausted plume was studied to optimize the loading equipment design and avoide the thermal damage. Fine wire thermocouples were used to measure the total temperature distribution of the rocket engine. There are several stages in temperature-time history corresponding to the work procedure of the rocket engine. Thermal damage zone was obtained. This distribution pattern is the same as theoretical structure, but it differs with numerical simulation result in some degree . The measurement error of fine wire thermocouples is discussed briefly.

Key words: Rocket exhaust;Nozzle flow;Temperature measurement;Thermocouple;Temperature distribution

徐强,李军,曹从咏. 火箭燃气射流温度分布的实验研究[J]. 推进技术, 2003, 24(2): 109-111.