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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。
The solid rocket engine ground test needs to measure the temperature data of the various components of the engine during the working process to verify the effectiveness of the design of the thermal protection structure of each component. At present, the temperature parameters are mainly measured by the thermocouple temperature sensor in the ground test of the solid rocket motor. Since the dimensions of the various components of the engine are different, the temperature range in the working process is wide (0-800 ° C.), and there is a strong corrosion and strong ionization complex Environment, so you must use different temperature sensor installation process for specific situations. According to the installation process of temperature measurement on several thermocouple temperature sensors, the temperature data are compared and analyzed, the applicable conditions of different installation processes are summarized, and the reference of the thermocouple temperature sensor for solid rocket motor ground test is provided.