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针对火箭发动机地面静式试验中燃气温度测量的特殊要求,设计出了一种基于钨铼热电偶的测温方法.根据发动机点火试验中工作时间短、压强小、温度高等特性,分别从热电偶丝的选型、绝缘材料、耐高温材料、热电偶的保护和传感器的安装方式等方面设计温度传感器,并利用信号调理器和数据采集卡对燃气温度进行采集和显示.经过多次点火试验表明,该温度传感器具有很好的抗高压和抗高温特性,能够满足点火试验的要求.
Aiming at the special requirements of gas temperature measurement in rocket engine ground static test, a temperature measurement method based on tungsten rhenium thermocouple was designed.According to the characteristics of short working time, low pressure and high temperature in engine ignition test, The selection of wire, insulation materials, high temperature materials, the protection of thermocouples and the installation of the sensor design temperature sensors, and the use of signal conditioner and data acquisition card on the gas temperature collection and display. After several ignition tests showed that , The temperature sensor has good resistance to high pressure and high temperature characteristics, to meet the ignition test requirements.