Multi-layer heat insulation assembly system for improving heat insulation effect of spacecraft
A technology of multi-layer heat insulation components and heat insulation effects, which is applied in the fields of aerospace vehicle heat protection devices, aerospace safety/emergency devices, etc. Sufficient and other issues to achieve the effect of increasing heat insulation effect, reducing size requirements, and reducing weight requirements
Inactive Publication Date: 2020-11-06
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the existing technical solutions, to provide a multi-layer heat insulation component system for increasing the heat insulation effect of the spacecraft, and to solve the problem caused by the contact between the reflector screens in the existing spacecraft thermal control design. Insufficient heat insulation of multi-layer heat insulation components caused by heat conduction, and the addition of large structural parts such as structural sleeves to enhance the heat insulation effect of multi-layer heat insulation components leads to problems in thermal control design size and weight exceeding the limit
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[0051] The main structure of a large-scale camera of a certain type of satellite is installed on the top of the load cabin and directly exposed outside the cabin. It is required that the temperature fluctuation of the camera should not exceed ±1.5°C, and the maximum temperature difference should not exceed 1°C. 50mm. According to the characteristics of heat flow outside the satellite in all directions of the sun-synchronous orbit, the conventional way of covering 15 units of multi-layer heat insulation components outside the cabin is adopted. The maximum temperature fluctuation in a single orbital period exceeds 2 °C, and the maximum temperature difference with other areas not directly irradiated by the sun exceeds 2 °C. 2°C, simply increasing the number of multi-layer insulation components has no obvious effect on reducing the multi-layer equivalent radiation coefficient.
[0052] (1) According to the comprehensive consideration of thermal control design weight, size constrai...
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The invention relates to a multi-layer heat insulation assembly system for improving the heat insulation effect of a spacecraft. The multi-layer heat insulation assembly system comprises a first multi-layer heat insulation assembly and a second multi-layer heat insulation assembly. The first multi-layer heat insulation assembly and the second multi-layer heat insulation assembly wrap the outer surface of a heat-insulated spacecraft structure in sequence, and the first multi-layer heat insulation assembly is attached to the surface of the heat-insulated spacecraft structure. A certain gap is kept between the first multi-layer heat insulation assembly and the second multi-layer heat insulation assembly. The problems that in an existing spacecraft thermal control design, due to contact heat conduction between reflecting screens, heat insulation of the multi-layer heat insulation assemblies is insufficient, and in order to enhance the heat insulation effect of the multi-layer heat insulation assemblies, large structural parts such as a structural sleeve are additionally arranged, and the thermal control design size and weight exceed limits are solved.
Description
technical field [0001] The invention belongs to the field of thermal control of spacecraft, and relates to a multi-layer heat insulation component system for increasing the heat insulation effect of spacecraft. Background technique [0002] In the thermal control design of spacecraft, the heat insulation method of coating multi-layer heat insulation components is usually used to realize the insulation of the spacecraft or reduce the influence of external heat flow, so as to achieve a relatively stable temperature of the spacecraft. [0003] At present, the commonly used multi-layer heat insulation components in the thermal control of spacecraft are composed of high-reflectivity reflective screens and spacer layers; the installation method generally adopts a pair of Velcro fasteners respectively fixed on the structural parts and the multi-layer heat insulation components. The manner in which a tab cooperates with a pin secured to the structural member to define the multilayer...
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IPC IPC(8): B64G1/58
CPCB64G1/58
Inventor 殷亚州付伟纯杨琦韩东阳肖朋江利锋余雷张新伟
Owner BEIJING INST OF SPACECRAFT SYST ENG