固体火箭发动机试验热电偶安装工艺分析

Assembly Plan Analysis of Thermocouple in Solid Rocket Motor Test

固体火箭发动机地面试验需测量发动机各部组件在工作过程中的温度数据,验证各部组件防热结构设计有效性。目前在固体火箭发动机地面试验中主要采用热电偶温度传感器进行温度参数测量,由于发动机各部组件外形尺寸各异,工作过程中温度范围跨度大(0~800℃),有强腐蚀、强电离的复杂环境,因此必须针对具体情况采用不同的温度传感器安装工艺。针对几种热电偶温度传感器表面测温的安装工艺,对比分析温度数据,总结不同安装工艺的适用条件,为今后固体火箭发动机地面试验热电偶温度传感器的使用提供参考。

Thermocouple is applied to measure temperature parameter in solid rocket motor test.Because motor components have some characteristics with different overall dimension,widely working temperatures,complex environment of strongly corrosion and strong-field ionization,it must apply special assembly plan in different condition.Though comparing with thermocouple assembly plans and analysing temperature data,the article summary applicable conditions of thermocouple assembly plans,provide reference of thermocouple applied in solid rocket motor test in future.