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A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts

A high-strength, ribbed technology, applied in the field of high-performance carbon fiber composite structural parts manufacturing, can solve the problems of reduced production efficiency, increased production cost, and increased manufacturing cycle, achieving high manufacturing success rate, short production cycle, and low manufacturing cost. low effect

Active Publication Date: 2021-05-25
航天海鹰(镇江)特种材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0016] 4. The whole process requires 2-3 times of autoclave, and each time it needs to be heated to the corresponding curing temperature, the manufacturing cycle increases, the production cost increases, and the production efficiency decreases;
[0017] 5. If the parts enter the tank many times, the heat accumulation will cause the internal stress accumulation of the material, molecular chain breakage, material aging and other problems.

Method used

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  • A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts
  • A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts
  • A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts

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Experimental program
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Effect test

Embodiment 1

[0036] A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts, comprising the following steps:

[0037] Step 1: Mold making, through the method of mechanical manufacturing, process two sets of metal forming molds that are exactly the same size as the left and right sides of the composite material parts, such as figure 1 with 2 The left metal mold and the right metal mold shown and as image 3 A set of C-shaped metal forming molds that are completely consistent with the inner surface of the C-shaped web of the workpiece are shown, and corresponding drilling templates are equipped at the ends of the three sets of metal molds for drilling after curing;

[0038] Step 2: Lay a layer of rubber on the left and right metal forming molds respectively. After the first layer of rubber is paved, continue to pave two layers of carbon fiber prepreg or glass fiber prepreg on the rubber layer as a reinforcement layer;

[00...

Embodiment 2

[0043] A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts, comprising the following steps:

[0044] Step 1: Mold making, through the method of mechanical manufacturing, process two sets of metal forming molds that are exactly the same size as the left and right sides of the composite material parts, such as figure 1 with 2 The left metal mold and the right metal mold shown and as image 3 A set of C-shaped metal forming molds that are completely consistent with the inner surface of the C-shaped web of the workpiece are shown, and corresponding drilling templates are equipped at the ends of the three sets of metal molds for drilling after curing;

[0045] Step 2: Lay a layer of rubber on the left and right metal forming molds respectively. After the first layer of rubber is paved, continue to pave 10 layers of carbon fiber prepreg or glass fiber prepreg on the rubber layer as a reinforcement layer;

[0046]...

Embodiment 3

[0050] A method for high-strength soft tooling to realize co-curing of L-shaped ribs and C-shaped frame structure composite parts, comprising the following steps:

[0051] Step 1: Mold making, through the method of mechanical manufacturing, process two sets of metal forming molds that are exactly the same size as the left and right sides of the composite material parts, such as figure 1 with 2 The left metal mold and the right metal mold shown and as image 3 A set of C-shaped metal forming molds that are completely consistent with the inner surface of the C-shaped web of the workpiece are shown, and corresponding drilling templates are equipped at the ends of the three sets of metal molds for drilling after curing;

[0052] Step 2: Lay a layer of rubber on the left and right metal forming molds respectively. After the first layer of rubber is paved, continue to pave 5 layers of carbon fiber prepreg or glass fiber prepreg on the rubber layer as a reinforcement layer;

[0053...

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Abstract

The invention provides a method for co-curing L-shaped reinforcing ribs and C-shaped frame structure composite parts with high-strength soft tooling. The co-curing of C-frame composite structural parts with reinforced ribs ensures that key parameters such as profile, thickness, and L-shaped axis of the part meet the high-demand civil aviation manufacturing standards, and avoids material damage caused by multiple curing. 2. During the molding process, the pressure applied to the L-shaped vertical rib and the C frame is uniform and accurate, and the heating rate of each part of the part is kept consistent. The above two points prevent the part from appearing in the R angle area. Poor problem; 3. Combine the uncured preform of the L-shaped vertical rib and the C-shaped web through soft tooling, avoiding the internal stress generated by the combination after the components are cured, and solving the forced assembly under the original technology Out-of-tolerance profile and internal non-destructive defects caused by components.

Description

technical field [0001] The invention relates to the technical field of advanced composite material manufacturing, in particular to the manufacturing of high-performance carbon fiber composite structural parts in the aircraft, spacecraft and automobile industries. Background technique [0002] Resin-based carbon fiber composite materials have superior properties such as specific strength and specific stiffness, strong designability, good fatigue fracture resistance, corrosion resistance, and good dimensional stability. They are currently widely used in aviation, aerospace, transportation and other fields. High-performance structural materials. Among various carbon fiber composite molding processes, the autoclave process has uniform molding temperature and pressure, and has good adaptability to parts of different materials, shapes, sizes and structures. One of the main process methods of material components. [0003] The C-shaped frame structure with L-shaped ribs is a relat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/44B29C70/54
CPCB29C70/342B29C70/345B29C70/44B29C70/543
Inventor 马秀菊宋宏翔郭渊任嘉慧基亚成曹习飞黎玉钦华文龙任慧敏
Owner 航天海鹰(镇江)特种材料有限公司
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