Spaceflight vehicle structure with ultra-light weight, large expansion-contraction ratio and ultra-low temperature working environment

Abstract

The invention discloses an aerospace craft structure with an ultra-light, large-expansion-shrinkage-ratio and ultra-low-temperature working environment. The structure comprises multiple layers of inflatable expansion self-stiffening laminated film covers, a light structural plate, interlayer telescopic sleeve rods, telescopic sleeves, an organic fiber net and multiple sets of pressure control valves. The problem that mass application of extreme materials with temperature requirements on spacecrafts is limited due to mutual conflict among the mass, the size and the effect of heat-proof structures on the spacecrafts is solved. After being unfolded, the large ultralow-temperature heat-proof structure is shown as a multi-layer film cover structure; by utilizing a space unfolding structure anda self-stiffening principle, a pressure control valve group is controlled to inflate, maintain pressure and deflate according to a certain sequence, and is matched with local gravity and a telescopicsleeve rod to realize unfolding and shaping, so that a stable ultralow-temperature environment can be maintained for an extreme device with a temperature requirement in a medium-short term in a vacuumenvironment under the condition of no refrigeration equipment. The structure is large in expansion-contraction ratio, simple in modeling and extremely light in weight, the ultralow-temperature heat-proof performance can be guaranteed, and the pressure of a carrying system is reduced.

Description

technical field [0001] The invention relates to an ultra-low temperature heat-proof structure, which is an ultra-light space vehicle heat-proof structure with large expansion and contraction ratios that can provide short-term and medium-term stable ultra-low temperature in a vacuum environment. Background technique [0002] In current cutting-edge scientific research and application fields such as superconductivity and magnetic levitation, the use of related equipment and materials has high requirements on ambient temperature. The ambient temperature of superconducting components is required to be lower than the critical temperature of 77K for high-temperature superconductivity, and the temperature requirements are extreme. , There is a great demand for ultra-low temperature heat protection technology. Ultra-low temperature heat protection technology generally relies on methods such as vacuum insulation, heat shields to reduce radiation, and multi-layer insulation components...

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the defects of the existing ultra-low temperature heat-proof structure, such as large mass, small shape, and high cost, and provide a reliable temperature environment for components with extreme temperature requirements such as superconducting components on spacecraft, the patented ultra-light, large expansion and contraction ratio, The aerospace vehicle structure in the ultra-low temperature working environment takes advantage of the advantages of light weight and large expansion and contraction ratio of the space inflatable unfolded structure and the advantages of the external vacuum environment of the space vehicle. Thermal efficiency, can provide a large, light, medium and short-term ultra-low temperature experiment and working environment on the space vehicle

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