Temperature control method and system for spacecraft thermal vacuum test

Abstract

The invention relates to the field of ground surface heat tests of spacecrafts and discloses a thermal vacuum test temperature control method and system for a spacecraft. The method comprises the following steps: simultaneously aligning the center of the heating center of a heat source by two temperature measurement instruments for different measurement regions, and performing measurement to obtain two different average temperatures T1 and T2; taking the average temperature T1 of the small region as input quantity of an increment PID (Proportion Integration Differentiation) controller for PID control; taking the ratio T1 / T2 of the two average temperatures as additional feedback quantity, and linearly superposing the additional feedback quantity with a PID control result to obtain a power change value of the heat source; adjusting the output power of the heat source for a heat test according to the change value. According to the thermal vacuum test temperature control method and system, stable thermal vacuum test temperature and controllable overshoot of the spacecraft can be guaranteed, and the robustness and stability of the thermal vacuum test temperature control system are improved.

Description

technical field [0001] The invention relates to the field of spacecraft ground thermal tests, in particular to a temperature control method and system for spacecraft thermal vacuum 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] Due to aerodynamic heating, the surface temperature of the space-to-earth shuttle vehicle is extremely high when it re-enters. The high-temperature wind tunnel test can only assess the performance of the surface thermal p...

AI Technical Summary

Problems solved by technology

In the existing technology, the temperature control during the test is usually finely adjusted according to the change curve of the temperature measured on site, according to experience or a fixed pattern. Due to the complexity of the test environment, the adjustment range is difficult to match the actual demand, and overshoots will basically occur repeatedly

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

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