Space material passive experiment sample installation structure, sample module and test box

Abstract

The invention relates to a sample installation structure, a sample module and a test box for a passive experiment of space materials. There is a chamfer at the upper end of the pressing edge near the exposure hole; the lower cover is detachably installed on the lower end of the upper cover, and an installation space for installing sample materials is formed between the lower cover and the pressing edge. The installation structure of the material passive experiment sample of the present invention provides effective support for the experimental sample material, and modularizes the space experiment material, which can realize the material in space atomic oxygen denudation, space high and low temperature alternation, space high-energy particle radiation, microgravity, ultra- Conduct on-orbit experiments in extremely harsh environments such as high vacuum, space debris / micrometeoroid impacts, etc. A sample material is set between each upper cover and lower cover to become a separate module. If some material modules have problems or fail, it will not affect other material modules to continue the experiment.

Description

technical field [0001] The invention relates to the related technical field of aerospace material exposure experiments, in particular to the interdisciplinary research field of space material science and space physical science, and in particular to a sample installation structure, a sample module and a test box for a passive experiment of space materials. Background technique [0002] After investigation, it was found that well-known foreign aerospace agencies such as NASA, Russian Aeronautics and Space Administration (RSA), European Space Agency (ESA), Japan Aeronautics and Space Administration (JAXA), etc., conduct material exposure tests based on the International Space Station (ISS). As well as the development of sample experimental modules, according to different test purposes and requirements, various types of material on-orbit test devices have been designed for material systems such as metal materials, inorganic non-metallic materials, polymer materials and composite ...

AI Technical Summary

Problems solved by technology

[0006] (2) Effect of pressure difference

[0007] The effect of pressure difference is usually within 1×10 -2 Pa~1×10 -5 Occurs in the vacuum range of Pa. When there is a sealed structure in the spacecraft, the internal and external differences of the sealed structure will increase, resulting in structural deformation or damage

[0008] (3) Effect of vacuum outlet

Released gases can re-condense on colder components, contaminating optics, sensors, and thermal control coatings with optically selective properties, resulting in reduced optical performance, increased solar absorption, and elevated temperatures

[0010] (4) Effect of radiation heat transfer

The cold and dark environment can easily lead to the stretching performance of the retractable mechanism on the spacecraft, and affect the performance of some organic materials, leading to the aging and embrittlement of materials, etc.

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