Data collection system for vacuum low-temperature environment

Abstract

The invention discloses a data collection system for a vacuum low-temperature environment. The data collection system comprises a vacuum container, a rotary table, a conductive sliding ring, a test piece, a temperature measurement sensor, a test piece measurement cable, a data collector, a rotary table movable disc, a comprehensive controller and an upper computer. The rotary table and the temperature measurement sensor are located inside the vacuum container, the comprehensive controller and the upper computer are located outside the vacuum container, the test piece is placed on the rotary table movable disc, the temperature measurement sensor adhering to the surface of the test piece is connected to the data collector through the test piece measurement cable, the data collector sends data to the comprehensive controller in an RS485 bus mode through the conductive sliding ring, and the comprehensive controller is in communication with the upper computer in a LAN mode. The data collection system is used for measuring the temperature of a rotary spacecraft test piece, and the gap in measurement for the temperature of a vacuum thermal test rotary test piece of a domestic spacecraft is filled.

Description

Technical field [0001] The invention relates to a ground test field of space environment simulation of a spacecraft, in particular to a data acquisition system used in a vacuum low-temperature environment, in particular to temperature measurement of a spacecraft specimen that needs to be rotated in a vacuum thermal test. Background technique [0002] The vacuum thermal test is one of the large-scale ground tests that must be carried out during the development of the spacecraft. In the vacuum thermal test, data collection, especially temperature data collection. If the temperature data is inaccurate, the conclusions made based on the test data may not be consistent with the actual conditions of the flight, and wrong decisions may be made based on such conclusions, which may eventually cause some components on the spacecraft to be overheated or It is too low to work properly. At present, the temperature measurement of spacecraft in the vacuum thermal test mainly has the following ...

AI Technical Summary

Problems solved by technology

The advantages of infrared camera temperature measurement are: the measurement process does not contact the surface to be measured, and does not destroy the temperature field distribution of the surface to be measured; the temperature resolution is high, the temperature measurement range is large, and the temperature field on the surface of the object can be displayed intuitively in different ways; The shortcomings of the camera temperature measurement system are: low accuracy and large measurement error

[0007] With the development of the spacecraft vacuum thermal test, in order to truly simulate the attitude of the spacecraft test piece or flight process, or to measure the thermal deformation, the test piece needs to rotate during the test process. The current thermocouple, platinum resistance, thermal The sensitive resistance temperature measurement system cannot meet the needs of such tests

Although infrared camera temperature measurement can be used to measure the temperature of rotating specimens, its measurement error is large and the accuracy is low, and it cannot meet the test requirements.

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