Temperature measurement system and method with floating reference end arranged in vacuum chamber

Abstract

The invention provides a temperature measurement system and method with a floating reference end arranged in a vacuum chamber. The system comprises a thermocouple (1) and an isothermal block (2), wherein the reference end of the thermocouple (1) is placed in the isothermal block (2), the isothermal block (2) is placed in the vacuum chamber (9), the measuring end of the thermocouple (1) and a platinum resistor (3) for measuring the temperature of the isothermal block (2) are respectively connected with a data collector (6) positioned outside the vacuum chamber (9) through an internal and external adapter cable (4) and a penetrating cabin connector (5) of the vacuum chamber (9); and the data collector (6) transmits the temperature data of the measuring end of the thermocouple and the temperature data of the platinum resistor (3) to a computer (7). According to the method provided by the invention, the problem of reference end temperature compensation when a thermocouple wire cannot directly penetrate out of the vacuum chamber through a hollow tube is solved, and temperature data during a spacecraft thermal test can be accurately obtained.

Description

technical field [0001] The invention relates to the technical field of spacecraft environment simulation, in particular to a temperature measurement system and method of a floating reference terminal built in a vacuum chamber. Background technique [0002] When a spacecraft uses a high-thrust engine to ignite, the average temperature is above 1000°C, which will cause large radiation heat transfer to the surface and internal equipment of the spacecraft, which will easily damage the structure or equipment of the spacecraft due to high temperature. A high-temperature heat shield is installed at the engine for corresponding protection measures. [0003] In order to obtain more accurate thermal boundary conditions of the high-temperature heat shield and determine the influence of the heat shield on the temperature of the engine throat, the high-temperature heat shield needs to participate in the thermal test of the engine program stage. During the hot test run, since the tempera...

AI Technical Summary

Problems solved by technology

[0004] However, the above-mentioned thermocouples are armored structures, and the thermocouple wires cannot pass directly out of the vacuum chamber through the hollow tube. Therefore, it is necessary to set a floating reference terminal inside the vacuum chamber for temperature compensation of the reference terminal of the thermocouple temperature measurement circuit, and the temperature measurement system is complicated. , unable to accurately obtain the temperature data during the thermal test of the spacecraft

Images