真空热试验温度参考点热响应测试系统设计与实现

Design and implementation of temperature reference equipment thermal response test system in vacuum thermal test

摘要:

在航天器真空热试验的温度测量中应用最广泛的是热电偶测温系统,温度参考点是热电偶测温系统的重要组成部分,对温度测试数据的准确性和航天器产品的安全有很大影响。为了在热试验开机前对参考点铂电阻与热点偶补偿端匹配关系的正确性进行验证,设计了一种可用于真空热试验的热电偶测温参考点热响应测试系统。该系统由加热器以及控制箱组成,可通过LAN网络与上位控制计算机连接实现热响应远程测试。文章通过对参考点装置的热分析以及热响应测试原理分析,给出了系统的硬件结构以及软件设计方案,并在多项航天器真空热试验中投入使用,提高了航天器真空热试验热电偶测温系统的可靠性。

Abstract:

In the spacecraft vacuum thermal test temperature measurement is the most widely used thermocouple temperature measurement system. The temperature reference point is an important part of the thermocouple temperature measurement system, and it has a great impact on the accuracy of the temperature test data and the safety of the spacecraft products. In order to verify the correctness of the matching relationship between the platinum resistance and the compensation point of the hot spot before the start of the thermal test, a thermocouple temperature reference test system for thermal test was designed. The system consists of a heater and a control box, which can be connected to a host computer via a LAN network for thermal response remote testing. In this paper, the thermal analysis of the reference point device and the thermal response test principle analysis, given the system hardware structure and software design, and in a number of spacecraft vacuum thermal test put into use, improve the spacecraft vacuum thermal test thermocouple Reliability of temperature measurement system.