Spacecraft thermal test reference point thermal response test system

Abstract

The invention discloses a spacecraft thermal test reference point thermal response test system. The system comprises a control unit, a first information exchange unit, a data acquisition unit and a branching unit, the control unit is used as a main control unit, the selection, heating and temperature collection of reference points are controlled in a communication connection mode, and the first information exchange unit is used as an information exchange medium between the control unit and the data collection unit; the connection between a field acquisition device and each reference point in a vacuum container is established through the branching unit, the branching unit receives a to-be-measured reference point selection electric signal, selects one to-be-measured reference point and performs heating operation, and then the data acquisition module receives a temperature data acquisition electric signal and acquires temperature data. Acquired temperature data is converted by the first information exchange unit and then is transmitted to the control unit for storage; the correctness of the matching relation between the reference point platinum resistor and the thermocouple compensation end is effectively verified, and the vacuum thermal test of the spacecraft is ensured to be smoothly carried out.

Description

technical field [0001] The present disclosure generally relates to the technical field of spacecraft and aircraft ground tests, and in particular relates to a thermal response test system for reference points of spacecraft thermal tests. Background technique [0002] The thermocouple temperature measurement system is the most widely used in the temperature measurement of the spacecraft vacuum thermal test, which generally uses a single-wire system to lead the thermocouple wires out of the vacuum container, that is, each group of temperature measurement points adopts the method of common lead wires, and each The negative poles of the group of thermocouples are connected together to a common reference point and then to the measuring instrument. [0003] At present, the vacuum heat test adopts the method of setting a common reference point in the vacuum container. The built-in temperature reference point device is generally a copper cylinder, and a hole is opened in the middle ...

AI Technical Summary

Problems solved by technology

At present, the reference point device is in a normal temperature environment before the test is started, and there is no way to change its temperature, which makes it impossible to verify: the correctness of the matching relationship between the reference point platinum resistance and the thermocouple compensation terminal

Among them, the correctness of the welding relationship of the thermocouple compensation end, such as the reverse connection of the reference point platinum resistance or the reverse welding of the thermocouple compensation end, may lead to a large number of thermocouple temperature measurement data errors

Therefore, we propose a spacecraft thermal test reference point thermal response test system to solve the above-mentioned problem that the temperature of the reference point cannot be adjusted, and it is impossible to verify the correctness of the matching relationship between the reference point platinum resistor and the thermocouple compensation terminal.

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