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Hood heat shield forming tool for returnable spacecraft

A return-type spacecraft and molding tooling technology, which is applied to household components, household appliances, other household appliances, etc., can solve the problem that the heat-proof hood layer of the return-type spacecraft cannot be directly subjected to vacuum impregnation, drying, and curing processes. Avoid the degradation of thermal protection performance, avoid excessive stress, and improve the effect of resin impregnation quality

Active Publication Date: 2019-07-02
BEIJING SATELLITE MFG FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] The technical problem to be solved by the present invention is: in order to overcome the problem that the heat-proof hood layer of the reversible spacecraft cannot be directly subjected to vacuum impregnation, drying, and curing processes, and to provide a heat-resistant layer forming tool for the reversible spacecraft hood

Method used

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  • Hood heat shield forming tool for returnable spacecraft
  • Hood heat shield forming tool for returnable spacecraft
  • Hood heat shield forming tool for returnable spacecraft

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Embodiment Construction

[0048] Such as Figure 1 to Figure 6 As shown, a returnable spacecraft hood heat-proof layer forming tooling includes a lower mold 11, a middle mold 10, an upper mold 1, an observation window 2, a vacuum gauge 3, a placeholder 4, a vacuum pipeline 5, and a glue injection pipeline 13 , Tray 9, hoisting ring 7, pressing plate 14, pressing frame 6 and guide wheel 12.

[0049] Along the height direction, the tooling is divided into three layers, the upper mold 1, the middle mold 10, and the lower mold 11; The installation surface is in the middle of the height direction of the inner tray 9; the upper mold 1 is used as the upper cover, and after assembly, forms a closed cavity together with the middle mold 10 and the lower mold 11; Install the gasket.

[0050] The lower mold 11 is located at the bottom of the tooling and has a concave mold structure. The distance between the inner wall and the heat-proof layer 8 of the spacecraft hood is 20mm; the lowest part of the inner cavity ...

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Abstract

The invention relates to a hood heat shield forming tool for a returnable spacecraft. The hood heat shield forming tool is characterized by comprising a lower die, a middle die, an upper die, an observation window, a vacuum meter, a space occupying lining, a vacuum pipeline, a glue injection pipeline, a tray, a hoisting ring, a compression plate and a compression frame. Along the height direction,the tool is divided into three layers, namely the upper die, the middle die and the lower die. The middle die and the lower die are used for containing a hood head shield of the spacecraft, and a mounting surface between the middle die and the lower die is positioned at the middle position of the tray in the height direction. The upper die is used as an upper cover, and the upper die, the middledie and the lower die form a closed chamber body together after being assembled. The space occupying lining is in screwed connection with the upper die, and a sealing gasket is arranged at a screw position.

Description

technical field [0001] The invention relates to a molding tool, which belongs to the field of molding of fiber-reinforced low-density thermal protection materials. Background technique [0002] Due to the need to experience high heat flow erosion during the reentry flight, the outer surface of the returnable spacecraft must have a reliable, erosion-resistant thermal protection system to protect the equipment and personnel inside the spacecraft. With the continuous development of deep space exploration projects, the return of the spacecraft at the second space flight speed to the reentry heat flow environment puts forward the structural strength, structural stability, large-scale integral molding, lightweight structure, and molding quality control of the surface ablation layer of the thermal protection system. Due to higher requirements, the thermal protection materials of traditional returnable spacecraft cannot meet their needs. [0003] Large-size curved long-fiber needle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/44B29C70/46B29C70/54B29C33/00B29L31/30
CPCB29C33/00B29C70/443B29C70/46B29C70/54B29L2031/3097
Inventor 孙天峰黎昱张明张玉生张璇郑建虎张鹏飞关鑫宫顼梁龙杨海涛尉世厚梁凯王冬陶积柏
Owner BEIJING SATELLITE MFG FACTORY
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