Co-curing process for the joining of composite structures

A composite material, composite material layer technology, applied in the field of assembled composite material structure, can solve the problems of composite material part limitation, high operation and maintenance cost, high initial construction cost, etc.

Active Publication Date: 2016-09-14
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Unfortunately, large autoclaves require high initial construction costs as well as high operating and

Method used

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  • Co-curing process for the joining of composite structures
  • Co-curing process for the joining of composite structures
  • Co-curing process for the joining of composite structures

Examples

Experimental program
Comparison scheme
Effect test

Embodiment approach

[0105] Clause 1. A method of manufacturing a composite component, said method comprising the steps of:

[0106] providing a first laminate and a second laminate formed from a first ply of composite material and a second ply of composite material, respectively, and having a corresponding first cured part and second cured part and corresponding first uncured part and second uncured part;

[0107] interleaving at least one of said first plies of composite material in said first uncured portion with said second plies of composite material in said second uncured portion to form an interfacial region; and

[0108] The interface region is cured to bond the first laminate to the second laminate and form a generalized composite component.

[0109] Clause 2. The method of clause 1, wherein the interleaving steps comprise:

[0110] At least one of the first plies of composite material in the first uncured portion is inserted between a pair of immediately adjacent second plies of compos...

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PUM

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Abstract

The invention relates to a co-curing process for the joining of composite structures. A method of fabricating a composite assembly (200) may include providing a first laminate (206) and a second laminate (216) respectively formed of first and second composite plies (204, 214), and having a respective first and second cured section (208, 218) and a respective first and second uncured section (210, 220). The method (200) may further include interleaving the first composite plies (204) in the first uncured section (210) with the second composite plies (214) in the second uncured section (220) to form an interfacial region (256). The method may additionally include curing the interfacial region (256) to join the first laminate (206) to the second laminate (216) and form a unitized composite assembly (200).

Description

technical field [0001] The present disclosure relates generally to composite fabrication, and more particularly to methods of assembling composite structures. Background technique [0002] Traditional methods of fabricating composite structures involve assembling cured composite parts using fasteners or adhesives. The use of fasteners requires special drilling equipment to create fastener holes in the composite parts to be joined. Additionally, the process of installing individual fasteners in the plurality of fastener holes is a time-consuming and labor-intensive process. Additionally, multiple fasteners in a structural assembly add weight, detracting from the performance capabilities of weight sensitive structures such as aircraft. [0003] Assembling a composite structure by using adhesives to bond composite parts together may limit the use of the structure to applications that do not need to carry major loads. Assembly techniques that rely on fasteners and / or adhesive...

Claims

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Application Information

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IPC IPC(8): B29C70/34B29C70/54B29L31/30
CPCB29C70/342B29C70/54B29L2031/3085B29C35/0266B29C66/71B29C65/14B29C65/18B29C65/5014B29C65/5021B29C65/505B29C66/112B29C66/12821B29C66/12822B29C66/12841B29C66/131B29C66/342B29C66/43B29C66/524B29C66/61B29C66/63B29C66/634B29C66/721B29C66/7212B29C66/72143B29C66/723B29C66/73752B29C66/73921B29C66/73941B29C66/81455B29C66/72141B64F5/10B64C3/20B64C5/02B29L2031/7172B64C3/26B29C65/02B29L2031/3076Y02T50/40B29C70/304B29K2277/10B29K2223/00B29K2305/00B29K2309/08B29K2307/04B29K2307/02B29K2309/02B29K2063/00B29K2027/12B29K2023/06B29K2067/00B29K2023/12B29K2069/00B29K2075/00B29K2271/00B29K2079/085B32B2605/18
Inventor K·D·洪费尔德K·M·纳尔逊
Owner THE BOEING CO
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