Study Of Measurement Technique Of Total Temperature Probe Using Thermocouple In High-Enthalpy/High-Speed Airflow

It is a difficult problem for total-temperature measurement of high-enthalpy/ high-speed flow in test study and hypersonic flow calibration. It depends on test data. It deserves thorough study for test techniques of total-temperature measurement of high-enthalpy/high-speed flow (including symbolic logic matrix, measurement method and precision), especially in study of action of high-enthalpy to aircrafts.The total-temperature measurement of gas can adopts disrobed thermocouple probe and total-temperature thermocouple probe. The total-temperature thermocouple probe mainly consists of stagnation room, thermocouple wire and insulating ceramics pipe of two orifices etc. It has the advantages of simple structure, easy fabrication, high recovery coefficient, short response time and spot temperature measurement etc. It is more suitablefor total-temperature measurement of high-enthalpy/high-speed flow.This thesis gives domestic and overseas study actuality of total-temperaturemeasurement. Total-temperature thermocouple probe was fabricated and used in different conditions of high-enthalpy/high-speed flow. According to the character of high temperature and large load of high-enthalpy wind tunnel and jet flow of solid rocket engine, its total temperature was measured through reasonable design of structure, choice of material, welding technique and crafty assemblage etc. The test data was proved believable and has small error through calibration of different methods. The direct measurement of total temperature of high-enthalpy flow was achieved through special shielded structure especially at disturbance environment of super electromagnetic field.