Infrared radiation measurement device and method for low-temperature target in ground thermal testing

Abstract

The invention relates to an infrared radiation measurement device and method for a low-temperature target in ground thermal testing. The measurement device is composed of a measurement unit and a control cabinet. The measurement unit consists of a main equipment compartment body structure, an infrared optical window, a sealed inflation and deflation valve and joint, a sealed electric connector, temperature sensors, pressure sensors, heater pieces, a multi-layer thermal insulation assembly, a thermal control circuit, a bracket, an infrared thermal imaging instrument and an intra-cabin control system. The main equipment compartment body structure consists of a cabin body, a front cover, and a rear cover; the infrared optical window is installed on the front cover; the sealed electric connector and the sealed inflation and deflation valve and joint are installed on the rear cover; the infrared thermal imaging instrument is installed on the bracket inside the equipment cabin and is used for collecting target information; the heating pieces are pasted on the inner surface of the cabin; and the multiple temperature sensors and pressure sensors are arranged and the temperature inside thecabin is controlled by the thermal control circuit. The outer surface of the front cover is coated with the multi-layer thermal insulation assembly. The control system is used for providing power forequipment inside the cabin, carrying out environmental monitoring and data acquisition and sending the collected data to the control cabinet.

Description

technical field [0001] The invention provides an infrared radiation measurement device and method for a low-temperature target in a ground thermal test, belonging to the technical field of testing and low-temperature testing. Background technique [0002] Spacecraft thermal test (collectively referred to as thermal vacuum test and thermal balance test) is an important ground assessment that a spacecraft must undergo before launch. Spacecraft vacuum heat test in vacuum (vacuum degree 10 -3 Below Pa), cool and dark (environment temperature about 100K) environment, the surface temperature of the test piece can reach 150K ((-123°C)) or even lower, traditionally, the contact measurement means such as thermocouple or thermistor is used to monitor the test part surface temperature. In recent years, due to the remarkable advantages of not interfering with the movement of the test piece and being able to intuitively analyze the temperature field distribution on the surface of the s...

AI Technical Summary

Problems solved by technology

In previous test applications, the infrared thermal imaging camera was usually placed outside the vacuum tank, and the target in the simulated environment was measured through the infrared window, which was limited by factors such as thermal imaging camera noise, stray radiation in the measurement path, and low-temperature calibration capabilities. Low temperature targets below 40°C do not have measurement capabilities, and accurate measurement of low temperature targets below -40°C cannot be achieved

Insufficient low-temperature measurement capability of infrared thermal imaging equipment seriously restricts its further application in spacecraft thermal experiments

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