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A carbon fiber/high toughness epoxy composite material grid rib forming method

A technology of grid rib and composite material, which is applied in the field of carbon fiber/high-toughness epoxy composite grid rib forming, can solve problems such as damage to grid rib strength, buckling at the nodes of grid rib, etc. , to achieve high molding efficiency, avoid pores, and the number of roots is stable and reliable.

Active Publication Date: 2017-07-28
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] After using hot-melt prepreg instead of traditional solution method prepreg, during the molding process of the carbon fiber composite grid reinforcement structure, due to factors such as low resin content and poor resin fluidity, the thickness of the cross node of the ribs is higher than that used. The thickness of the joints is more prominent when the solution method prepregs the wire, especially when the cross-section of the ribs is large, which will cause the thickness of the ribs prepared by the hot-melt method to be inconsistent with the thickness of other places, so that the grid The buckling of the joints of the ribs is serious, which greatly damages the strength of the grid ribs

Method used

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  • A carbon fiber/high toughness epoxy composite material grid rib forming method
  • A carbon fiber/high toughness epoxy composite material grid rib forming method
  • A carbon fiber/high toughness epoxy composite material grid rib forming method

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Embodiment

[0051] (1) The schematic diagram of the structure of the grid ribs to be formed is prepared as follows figure 1 As shown, its forming mold is as figure 2 As shown, the mold size is 440mm×440mm, the depth of the ribs is 20mm, the width is 10mm, and the vertical and horizontal ribs are equally spaced with 4 bars each. The distance between adjacent ribs and the edge of the mold to the side of the rib near the edge The same width is 80mm;

[0052] (2) According to the three-dimensional digital model of the grid ribs to be formed, the quantity and size of the prepreg blocks required for the grid ribs to be formed are accurately calculated for laying the A-type prepreg blocks of the transverse ribs Length 450mm, width 440mm, type B prepreg block length 80mm, width 440mm, for laying longitudinal ribs C type prepreg block length 450mm, width 440mm, D type prepreg block length 80mm, width 440mm, and Precise cutting with automatic cutting equipment;

[0053] (3) Preparation of tend...

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Abstract

The invention relates to a carbon fiber / high tenacity epoxy composite material grid fillet molding method, and belongs to the technical field of grid ribbing structure composite material molding. The cross section of a grid fillet prepared with the molding method is large, the common depth-to-width ratio is 1-3, the depth ranges from 15 mm to 20 mm, and the carbon fiber / high tenacity epoxy composite material grid fillet molding method In particular, the invention relates to a T800 carbon fiber / epoxy hot melting method prepreg grid fillet skin class structure molding method. The carbon fiber / high tenacity epoxy hot melting pre-soaking silk material system which is low in flue containing amount and high in filter size content is adopted in the method, large-section size fillet molding technical researches are developed, adaptation improvements are carried out on the pre-soaking silk paving process, the glue absorbing curving process, the skin interface interlayer bonding process and the like are achieved, and application to grid fillet standard structure pieces is achieved.

Description

technical field [0001] The invention relates to a method for forming grid ribs of carbon fiber / high-toughness epoxy composite material. The grid ribs prepared by the forming method have a large cross-section, generally have an aspect ratio of 1-3, and a depth of 15-20mm, belonging to the network The technical field of composite material molding with grid reinforcement structure, especially relates to a T800 carbon fiber / epoxy hot melt method prepreg grid rib skin structure molding method. Background technique [0002] Compared with aluminum alloy, carbon fiber composite materials have the characteristics of light weight and high strength, and the amount of carbon fiber composite materials is increasing day by day. Carbon fiber composite grid rib structure is used in aerospace and other fields due to its advantages of high structural load-bearing efficiency, good designability, and low sensitivity to local initial defects. [0003] The existing carbon fiber composite grid re...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/44B29C70/54
CPCB29C70/44B29C70/54
Inventor 张建宝郑红飞孙文文赵文宇肖利川
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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