Carbon fiber composite mold surface forming property screening method

Abstract

The invention discloses a carbon fiber composite mold surface forming property screening method. The method comprises the specific steps that firstly, a numerical control machine tool is adopted for machining a forming surface on a female die; secondly, die prepreg is adopted to be laid on the surface of the female die in the first step, and after the prepreg is laid, according to the curing system of the die prepreg resin system, curing forming of a composite die in a hot pressing tank or oven can be finished; thirdly, the composite die is separated out of the female die, and is subjected tocold and hot circulation treatment, and point cloud information of the product profile is obtained, and is transmitted to a numerical control grinding and polishing machining system; fourthly, a high-spot material is removed, and after the profile precision is converge to the die profile precision threshold, a polishing device is adopted for carrying out circular polishing according to the profilefinal precision needs; and fifthly, a three-dimensional measuring method is adopted for carrying out comprehensive evaluation on the forming surface property. The comprehensive evaluation of the surface property after profile precision is improved through the grinding and polishing machining means of the carbon fiber composite die is achieved.

Description

technical field [0001] The invention belongs to the structural forming technology of carbon fiber reinforced resin matrix composite material, and is applied to the research and development of composite material antenna reflector structure products for spacecraft. Background technique [0002] The space-borne large-aperture composite antenna reflector is a typical carbon fiber-skinned honeycomb sandwich structure, which has the characteristics of light weight, high precision, and high thermal stability. Accuracy is also gradually improved. [0003] The molding of resin-based carbon fiber composite antenna reflector mainly refers to the carbon-skinned honeycomb sandwich structure. Two carbon fiber skins are glued and solidified with the end face of the honeycomb core through a molding die under high temperature and high pressure conditions to form a stable structure. At the same time, through the design of a special The mechanical interface is connected with the feed source a...

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Problems solved by technology

[0005] However, at present, the surface accuracy of carbon fiber forming molds is mainly obtained by turning over the master mold. The limit accuracy that can be achieved by direct molding is about 0.05mm RMS, which still cannot meet the development needs of large-caliber high-precision composite antenna reflectors. Therefore, it is necessary to directly Grinding and polishing on the basis of forming accuracy to further improve the accuracy

The surface state of co

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