Method for machining multi-layer thermal insulation material retainer
A multi-layer thermal insulation material and fixing device technology, which is applied in the direction of thermal insulation protection of pipes, heat exchange equipment, thermal insulation, etc. Effects of stability, weight reduction, high bending ductility
Active Publication Date: 2017-01-04
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
For some satellites, there is no change in the fairing during launch, and the outer surface of the star is affected by aerodynamic scour, and aerodynamic heating will cause the temperature of the outer surface of the satellite to exceed 200°C for a short time, coupled with the impact of vibration during launch, use The multi-layer heat insulation material pasted with silicone rubber, due to the short-term temperature rise and the existence of the vibration environment of the whole star, the performance of the silicone rubber decreases
In addition, for some spacecraft in non-Earth orbit, they will encounter extremely high or low temperature environments in orbit, even exceeding the operating temperature range of silicone rubber. The operating temperature range of silicone rubber is -100 to +150°C. It may cause the pasted velcro or pin to fall off, which will cause all or part of the multi-layer to fail and fail to meet the thermal control requirements.
[0004] In addition, during the development of spacecraft, the weight control is relatively strict. Some spacecraft need to use multi-layer heat insulation materials to build a relatively closed space to ensure the temperature of the equipment. Aluminum alloys are generally used to make multi-layer heat insulation materials on spacecraft. The supporting device cannot effectively reduce the weight
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[0025] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0026] The invention provides a method for processing a multi-layer heat insulating material fixing device. The multi-layer heat insulating material fixing device comprises: a top ring 1, a long bamboo strip 2, a small bamboo circle 3, a short bamboo strip 4, and a large bamboo circle 5, such as figure 1 shown. Eight long bamboo strips 2 are evenly distributed along the warp direction and fixed on the top ring 1, the small bamboo circle 3 and the large bamboo circle 5 are fixed on the long bamboo strips 2 along the latitude direction, and eight short bamboo strips are fixed on the large bamboo circle 5 along the warp direction And the small bamboo circle 3.
[0027] The processing steps of the multi-layer insulation material fixture are as follows:
[0028] Step 1: Make a forming mold according to the size of the multi-layer heat insulation material fixi...
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The invention discloses a method for machining a multi-layer thermal insulation material retainer. The method utilizes moso bamboos to produce long bamboo strips, short bamboo strips, a large bamboo ring and a small bamboo ring, which are fixedly assembled on a machined top ring, and after high-temperature heat treatment and punching, the multi-layer thermal insulation material retainer is produced. The method can ensure that when temperature is overlow or overhigh, the multi-layer thermal insulation material retainer can prevent a multi-layer thermal insulation material from failing due to separation, and moreover, the requirement on weight can be effectively decreased.
Description
technical field [0001] The invention relates to the technical field of spacecraft thermal control, in particular to a method for processing a multi-layer heat insulating material fixing device. Background technique [0002] On spacecraft, multi-layer heat insulation materials are widely used, and the fixing methods of multi-layer heat insulation materials are generally fixed by Velcro or polyimide pins, and both Velcro and pins are pasted with silicone rubber. The structural member of the layer or the outer surface of the equipment. [0003] Generally, the outer surface of the spacecraft has a fairing to protect the thermal control material on the outer surface of the entire star from the influence of aerodynamic scour. For some satellites, there is no change in the fairing during launch, and the outer surface of the star is affected by aerodynamic scour, and aerodynamic heating will cause the temperature of the outer surface of the satellite to exceed 200°C for a short tim...
Claims
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IPC IPC(8): F16L59/02
CPCF16L59/029
Inventor 任红艳刘庆志
Owner BEIJING INST OF SPACECRAFT SYST ENG