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Method and apparatus for manufacturing contoured composite structures and resulting structures

A composite structure and equipment technology, applied in the field of manufacturing composite parts, can solve problems such as high cost, increased floor space requirements, and long manufacturing process time

Active Publication Date: 2016-10-12
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These repetitive operations add cost, complicate processing, may increase floor space requirements, and may adversely affect manufacturing process time
[0004] Another disadvantage of known techniques for forming highly contoured composite structures with multiple legs involves the need to use a different set of tools to form each leg in a separate forming operation
Using a different tool set to form the legs of the structure can also result in higher costs and longer manufacturing process times

Method used

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  • Method and apparatus for manufacturing contoured composite structures and resulting structures
  • Method and apparatus for manufacturing contoured composite structures and resulting structures
  • Method and apparatus for manufacturing contoured composite structures and resulting structures

Examples

Experimental program
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Embodiment Construction

[0142] first reference Figure 1-3 , the barrel-shaped fuselage section 30 includes an outer skin 34 formed and fastened to the frame structure 32 . The frame structure 32 includes a plurality of longitudinally spaced barrel frames 32a and longitudinally extending stringers 32b passing through the barrel frames 32a. Each barrel frame 32a may comprise a curved or contoured composite member, which may be in the form of a plurality of curved frame sections 36 spliced ​​together using any suitable means, such as, but not limited to, spliced ​​panels (not shown). shown) and fasteners (not shown). In some applications, however, curved half-frame and full-frame sections (not shown) are also possible. It should be noted here that the curved frame sections 36 are merely illustrative of the various curved or contoured composite members that may be fabricated by the disclosed methods and apparatus.

[0143] Such as image 3 As best seen, each frame section 36 , hereinafter also somet...

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PUM

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Abstract

The contoured composite structure includes an axis of curvature and at least one curved leg (38). The structure is fabricated by laying down a flat stack (50) of pre-impregnated fiber layers (52), each having a non-zero fiber orientation relative to the axis of curvature, and At least one pre-impregnated fiber layer with zero degree fiber orientation is laid on. Laying the zero-degree layup includes laying down the prepreg tow lengths arranged end-to-end on at least a portion of the stack. The stack is formed as a web and curved legs.

Description

technical field [0001] The present invention relates generally to techniques for fabricating composite parts, and more particularly to methods of fabricating highly profiled, non-Cartesian composite structures using unidirectional prepreg composite tape and automated tape layup equipment. Background technique [0002] High profile multi-legged composite structures can be used in a variety of applications, such as in aircraft. Aircraft frames, spars, ribs, stringers, and similar structures may have multiple legs contoured along the length of the structure. One known technique for fabricating such structures involves hot drape forming / hot drape form flat composite charges / charges on multiple contoured tools / contoured tools, to form one or more curved legs in the structure. The charge usually comprises layers of unidirectional pre-impregnated fibers laid down according to a predetermined layer arrangement. Difficulties may be encountered, however, when attempting to hot-drap...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/20B29L31/00B29L31/30B29C70/44
CPCB29C70/38B29C70/44B29L2031/003B29L2031/3082Y10T428/24124Y10T428/24628Y10T156/14Y10T156/10Y10T428/24132Y10T156/1052B29C70/207G06F30/17B29C70/304B29C70/30B29C70/541B29C70/20B32B37/10
Inventor J·C·古兹曼D·A·麦克卡威尔J·L·思维听R·梅新格尔
Owner THE BOEING CO