High and low temperature box for spacecraft structure stability test

Abstract

The invention provides a high and low temperature box for a spacecraft structure stability test. The high and low temperature box comprises a box body and a temperature control host arranged outside the box body, the box body comprises a temperature control cabin and observation cabins connected to the two ends of the temperature control cabin; a temperature control plate is arranged in the temperature control cabin; the temperature control board is connected with the temperature control host through a temperature control medium pipeline and is used for adjusting the temperature in the temperature control cabin; and a transparent observation window is arranged on the observation cabin. The box is simple in structure and convenient to operate, the transparent observation window is arranged on the observation cabin, and when the device is used, the pose monitoring device is placed outside the box body, so that the high-temperature and low-temperature poses of a detected product in the box body can be monitored; and by connecting different numbers of lengthened cabins between the observation cabin and the temperature control cabin, the length of the box body of the test box can be adjusted, so that the box body can accommodate tested products with different lengths and sizes.

Description

technical field [0001] The application relates to the technical field of spacecraft professional testing, in particular to a high-low temperature chamber used for spacecraft structural stability tests. Background technique [0002] When the spacecraft is in orbit, it is in a complex environment of alternating cold and heat. When the spacecraft is in orbit, the temperature on the side facing the sun is as high as 180°C, and on the side facing away from the sun is minus 180°C. When developing a spacecraft on the ground, it is necessary to simulate a high and low temperature environment to verify whether the spacecraft structure is deformed. [0003] At present, the commonly used method is to locally heat the spacecraft through the heating plate under normal pressure conditions in the laboratory, heat different positions to a certain temperature according to different test matrices, and use position and attitude monitoring equipment to monitor the structure during the heating o...

AI Technical Summary

Problems solved by technology

At the same time, the position and attitude monitoring equipment is packaged in a protective tank with a glass window, and the monitoring equipment and the protective tank are placed in a low-temperature vacuum container to monitor the structural deformation of the spacecraft. "(Optical Technology, 201339(4)), this method is more complicated, and it is not easy to operate the pose monitoring equipment

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