摘要
在简单介绍火箭药温精确测量必要性和可能性的基础上,针对火箭热传导的特点,其发动机传热现象可用17个参量来表征,其中包括12个无量纲参量和5个基本量纲,并对无量纲参量进行了分析和分类。在缩小尺寸模型和火箭发动机原型之间特征温度以及经历时间完全对应(相似比例为1)的前提下,设计了1/5缩小尺寸模型。将初始温度相同(2 0℃)的原型与缩小尺寸模型置入温度为4 8℃的恒温环境下12 80min ,试验周期内,模型与实物特征温度之间最大偏差不大于1℃.试验结果表明该设计方案满足工程需要。
The necessity and possibility of measuring the propellant temperature of rockets accurately were introduced briefly. According to the transfer characteristic of rockets, seventeen parameters were used to describe the transfer of rockets including twelve nondimensional parameters and five basic parameters. The nondimensional parameters are analyzed and classified. A 1/5 size model was discussed in this paper, which keeps the same temperature as the rocket’s at the same time. The rocket and the small size model having the initial temperature (20℃) are both placed under the same environment keeping 48℃. The experiment lasts for as long as 1280 min and the difference between the characteristic temperature of rocket and the model’s is not more then 1℃. The experimental result shows that the design meets the demand of engineering.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2005年第3期405-408,共4页
Acta Armamentarii
关键词
化工测量技术与仪器仪表
火箭
药温
测量
measurement and instrument for chemical engineering
rocket
propellant temperature
measurement
