Spacecraft thermal vacuum testing temperature control method

Abstract

The invention relates to the field of spacecraft ground thermal tests and discloses a spacecraft thermal vacuum testing temperature control method. The method comprises the steps of measuring the position of a laser heating center with two thermodetectors with different measurement ranges at the same time to obtain average temperature T1 and average temperature T2 within two measurement ranges; taking the specific value T1 / T2 of the two average temperatures as the setting parameter of a proportion and integral time coefficient in a PID controller, conducting real-time online setting on the proportion and integral time coefficient according to the change of T1 / T2, and obtaining the change value of current heating power through the PID controller by means of the set coefficient; adjusting laser output power according to the change value. By the adoption of the method, under the condition that the overshoot of controlled temperature is reduced greatly, controlled temperature adjusting time is not increased, and the robustness and stability of a spacecraft thermal testing temperature control system are improved.

Description

technical field [0001] The invention relates to the field of spacecraft ground heat tests, in particular to the field of temperature control for spacecraft vacuum heat tests. Background technique [0002] The spacecraft thermal vacuum test is a test to verify various performances and functions of the spacecraft under specified vacuum and thermal cycle conditions. It is one of the important tests in the multi-environmental simulation tests in the development stage of the spacecraft. The main purpose of the test is to expose the spacecraft’s material and manufacturing process defects under vacuum and thermal cycle conditions, and eliminate early failures, thereby greatly improving the reliability of the spacecraft’s in-orbit operation. [0003] The spacecraft thermal vacuum test is to simulate the harsh conditions such as vacuum, low temperature, and solar radiation that the spacecraft is subjected to when working in the space environment on the ground. Generally, it is carr...

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Problems solved by technology

[0004] In the spacecraft thermal vacuum test, in addition to simulating the vacuum condition, there is also a need to control the temperature of the components on the spacecraft. When the control method is improper or the control parameters are selected unreasonably, the spacecraft will be over-tested and under-tested.

Excessive testing may damage certain instruments and equipment on the spacecraft or shorten the working life, and under-testing may result in certain instruments and equipment on the spacecraft not being properly tested

Especially due to the extremely slow heat dissipation in the vacuum environment of the thermal test, when the temperature control is performed, when the temperature curve overshoots, it is difficult to reduce the overshoot, which can easily lead to overtesting.

Moreover, due to the high cost and long cycle of spacecraft thermal vacuum tests, it is generally difficult to debug the temperature control system online before the test, so higher requirements are put forward for the robustness and adaptability of the temperature control system

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