Atmospheric reentry spacecraft outsole heat shield molding tool

Abstract

The invention relates to an atmospheric reentry spacecraft outsole heat shield molding tool, which comprising a lower die (6), a middle die (4), an upper die (1), an observation window (2), a vacuum pipeline (3), a glue injection pipeline (7) , a tray (10), a lifting ring (9), a pressing plate (8), and a pressing frame (12); in the height direction, the tool is divided into three layers: the upperdie (1), the middle die (4), and the lower die (6); the middle die (4) and the lower die (6) are used for holding a spacecraft outsole heat shield (11); the mounting surface between the middle die (4) and the lower die (6) is located in the middle of the height direction of the tray (10); and the upper die (1) serves as an upper cover and forms a closed cavity with the middle die (4) and the lower die (6)after assembled. According to the atmospheric reentry spacecraft outsole heat shield molding tool, the problem that the large-scale heat-resistant bottom layer of the return type spacecraft cannot directly implement the vacuum impregnation, drying and solidification processes are solved.

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...

AI Technical Summary

Problems solved by technology

[0013] The technical problem to be solved by the present invention is: in order to overcome the problem that the heat-proof bottom layer of the returnable spaceship cannot be directly subjected to vacuum impregnation, drying, and curing processes, a tool for forming the heat-proof layer of the large bottom of the returnable spaceship is provided.

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