论文部分内容阅读
本文介绍了近年来我们研制和使用的一种利用热电偶测量火箭燃气流温度的方法。热电偶的材料为镍铬-镍铝或镍硅。测温上限达1300℃。传感器的时间常数不大于0.033秒。可以快速记录燃气流温度变化曲线。测量精度约为5％-6％。文章介绍了传感器的结构,记录仪器及其标定方法。对各种误差及其修正方法也进行了简要地讨论。
This article describes a method we have developed and used in recent years to measure the rocket gas flow temperature using thermocouples. The material of the thermocouple is nichrome-nickel aluminum or nickel-silicon. Temperature limit up to 1300 ℃. The time constant of the sensor is not more than 0.033 seconds. Can quickly record the gas flow temperature curve. Measurement accuracy of about 5% -6%. The article describes the structure of the sensor, recording instrument and calibration method. Various errors and their corrections are also briefly discussed.