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Method and apparatus for forming a composite fuselage structure

A composite structure and component technology, applied in the direction of fuselage, application, aircraft assembly, etc., can solve problems such as slow productivity

Pending Publication Date: 2021-06-18
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Additionally, traditional methods involving the use of autoclaves to cure fuselage barrel structures made of thermoset composites can be slower than desired with regard to production rate requirements
Meeting such productivity requirements may require a more significant than desired investment in capital, equipment, facility resources, or a combination thereof

Method used

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  • Method and apparatus for forming a composite fuselage structure
  • Method and apparatus for forming a composite fuselage structure
  • Method and apparatus for forming a composite fuselage structure

Examples

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Embodiment Construction

[0259] The example embodiments described below provide methods, apparatus, and systems for rapidly and efficiently manufacturing composite structures, such as fuselage barrel sections, at reduced cost and weight. In particular, the use of thermoplastic materials to manufacture composite structures, such as fuselage barrel sections, can help reduce overall manufacturing costs and production times.

[0260] Example embodiments describe methods, apparatus, and systems that eliminate the need for autoclaves for curing fuselage barrel structures. Using an autoclave can be more expensive than desired. Additionally, due to their size and complexity, autoclaves have thermal mass requirements that make using autoclaves more time-consuming and less efficient than would be required to fabricate fuselage barrel sections. Example embodiments described herein reduce the cost and time required to manufacture fuselage barrel sections by eliminating the need for autoclaves. For example, at l...

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PUM

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Abstract

A method and apparatus for forming a composite structure are disclosed. A stackup comprising a plurality of overbraided thermoplastic members and an overbraided thermoplastic skin is built. The stackup is placed between an inner tooling and an outer tooling. The inner tooling, the stackup, and the outer tooling are held in place together using a load constraint. The inner tooling, the stackup, the outer tooling, and the load constraint form a consolidation setup. The consolidation setup is heated to form the composite structure.

Description

technical field [0001] The present disclosure relates generally to composite manufacturing, and more particularly to methods and apparatus for fabricating composite fuselage structures by integrating fuselage skins and fuselage stringers comprised of clad braid materials. Background technique [0002] Composite materials can be used to manufacture different types of aircraft structures. Currently, many aircraft structures are formed using thermoset composite materials. However, the use of thermoset composite materials, such as thermoset resins, may be more challenging than desired when manufacturing aircraft structures of larger size and shape, such as fuselage barrel sections. Additionally, the processes involved in using thermoset composites for such structures can be more time-consuming and expensive than desired. [0003] For example, the process of manufacturing fuselage barrel sections using thermoset composite materials may involve more facility resources (eg, facil...

Claims

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Application Information

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IPC IPC(8): B64F5/10
CPCB64F5/10B64C2001/0072B29C35/0805B29C70/462B29C2035/0811B29C2043/3649B29D99/0014B29K2101/12B29L2031/3082B29C70/222B32B2305/184B29C70/342B29C70/345B29C70/446B29C70/549Y02T50/40B29C70/541
Inventor J·L·马尔考M·R·马特森
Owner THE BOEING CO