High-temperature-resistant carbon fiber composite material cylinder bearing layer and preparation process thereof

Abstract

The invention provides a high-temperature-resistant carbon fiber composite material cylinder bearing layer and a preparation process thereof, relates to the technical field of composite materials, and is mainly used in the field of spaceflight as an external bearing layer of missiles and spaceflight launchers. According to the high-temperature-resistant carbon fiber composite material cylinder bearing layer, bismaleimide resin with a glass transition temperature of 260 DEG C is used as a matrix material and T800 carbon fiber is used as a reinforcement material to prepare unidirectional prepreg as a raw material, and an autoclave molding process is adopted to prepare the high-temperature-resistant conical carbon fiber composite material cylinder bearing layer; according to the preparation process, a male mold is adopted as a mold to prepare a pressure equalizing plate, and then the bearing layer is prepared in the manner that the male mold is matched with the pressure equalizing plate; according to the bearing layer, the unidirectional prepreg is laid between a male mold forming surface and the pressure equalizing plate in a belt-laying-like manner, and the laying manner is an orthogonal symmetric laying manner, so that the directivity of fibers and the surface quality of the cylinder bearing layer are ensured; and the high-temperature-resistant carbon fiber composite material cylinder bearing layer prepared by the method meets the use requirements, and the product quality is high.

Description

technical field [0001] The invention relates to the technical field of composite materials, in particular to a bearing layer of a high-temperature-resistant carbon fiber composite material cylinder and a preparation process thereof. Background technique [0002] Carbon fiber composite materials have excellent mechanical properties, high specific strength and specific stiffness, good weight reduction effect, and are increasingly widely used in the aerospace field. The use of carbon fiber composite materials to replace aerospace products, such as the outer cover of rocket system products, the shell of missile system products, etc., can make the corresponding system products have more excellent functions and improve the overall performance. At present, most of the load-bearing layer structures of cylinders used in aerospace products are made of metal, which are required to be resistant to high temperatures, and the maximum operating temperature is required to reach above 250°C....

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Problems solved by technology

[0003] The purpose of the present invention is to provide a high-temperature-resistant carbon fiber composite material cylinder load-bearing layer and its preparation process, so as to solve the problem that the appearance quality of the composite material cylinder load-bearing layer in the prior art is not high, cannot meet the use requirements of temperature, and has deformation during use technical issues

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