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

Abstract

The invention relates to a space material passive experiment sample supporting structure, a sample module and a test box. The sample supporting structure comprises a supporting plate and a crimping device, wherein the crimping device is detachably connected to the supporting plate and is used for crimping and fixing a sample material on the supporting plate. The space material passive experiment sample supporting structure provides effective support for an experiment sample material, the space experiment material is subjected to modular treatment, and in-orbit experiment testing can be carriedout on the material in extremely harsh environments such as space atomic oxygen denudation, space high and low temperature alternation, space high-energy particle radiation, microgravity, ultrahigh vacuum, space debris / micrometeoroid impact and the like. Meanwhile, ground laboratory installation, water removal, gas removal, dust removal treatment, in-orbit disassembly and replacement and disassembly operation after returning to the ground are facilitated; and the aerospace characteristic requirements of compact structure, small size, light weight and reliable mechanical property in the rocketlaunching ascending stage are met.

Description

technical field [0001] The invention relates to the technical field related to aerospace material exposure experiments, specifically to the interdisciplinary research fields of space material science and space physics science, and specifically to a sample support structure, sample module and test box for passive experiment of space materials. Background technique [0002] After investigation, it was found that famous foreign aerospace agencies such as NASA, Russian Aerospace Agency (RSA), European Space Agency (ESA), Japan Aeronautics and Space Agency (JAXA), etc., conduct material exposure tests based on the International Space Station (ISS). As well as the development of the sample experiment module, according to different test purposes and requirements, a variety of material on-orbit test devices are designed for material systems such as metallic materials, inorganic non-metallic materials, polymer materials, and composite materials. There is no related work on the develo...

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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