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Method of manufacturing a fuselage barrel made of monolithic composite material

A composite, monolithic technology used in airframes, airframe frames, chemical instruments and methods to solve problems such as damage to curing bags

Active Publication Date: 2016-11-23
ALENIA AERMACCHI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method overcomes the problems of the previous method, but in the known method it can only be used for sandwich structures, and there is still a risk of withdrawing the IML mandrel from the barrel before curing, because the extraction operation is performed in a limited gap, so May damage curing bag

Method used

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  • Method of manufacturing a fuselage barrel made of monolithic composite material
  • Method of manufacturing a fuselage barrel made of monolithic composite material
  • Method of manufacturing a fuselage barrel made of monolithic composite material

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Embodiment Construction

[0024] first reference figure 1 and figure 2 , reference numeral 10 generally designates a collapsible inner mandrel (or auxiliary mandrel), the outer surface of which is defined by a set of mandrel sectors 11 radially shrinkable with respect to the central horizontal axis x back. The mandrel sectors are operable in a radial direction to assume a radially extended position in which the mandrel sectors are juxtaposed circumferentially so as to collectively define a circumferentially continuous outer surface in which On the continuous outer surface is placed the pre-impregnated fiber strip to be cured for the manufacture of the fuselage body. In the example shown in the figures, the outer surface of the mandrel is almost cylindrical to manufacture the main body or middle section of the fuselage of the aircraft. However, the method is equally applicable to the manufacture of tapered fuselage barrels (or fuselage bodies), eg frusto-conical, the barrels being placed along the f...

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Abstract

A vacuum bag (18) is placed around the inner forming surface (IML) of an inner mandrel provided with radially retractable sectors (11a, 11b) with parallel longitudinal slots (17). Composite material stringers (30) are positioned in said slots (17). In each stringer is placed a respective elongated inner support (31) covered by an impermeable tubular bag (32). A skin of composite material (37) is laminated around said stringers (30), said coating supports (31, 32) and said inner forming surface (IML). Outer curing tools (50, 51) are closed around said skin (37), defining the outer forming surface (OML) of said fuselage barrel, where the outer surface of said skin (37) meets said outer forming surface. An annular gap (G) of predetermined radial width is left between the surfaces (OML). applying a vacuum to the space enclosed between the vacuum bag (18) and the outer tooling (50, 51 ) to increase the diameter of the uncured cylinder and release the cylinder from the inner mandrel (10) And bringing the outer surface of the skin (37) into contact with the inner surface (OML) of the outer tool (50, 51).

Description

technical field [0001] The invention relates to a method of manufacturing a fuselage tube of composite material, the fuselage tube being reinforced by stringers. More specifically, the present invention relates to the manufacture of composite materials in a single-piece fuselage barrel comprising: an overall tubular, cylindrical or frusto-conical skin and on the inner surface of the barrel A protruding series of longitudinal stringers. Background technique [0002] The prior art includes several methods of manufacturing a complete composite fuselage barrel. In general, some processes require curing the barrel around an inner mandrel or inner forming tool, which provides the inner forming surface of the barrel (the so-called "inner molding line" (IML) or "inner molding surface"). In other cases, the curing operation takes place in a hollow forming tool that provides the outer forming surface of the barrel ("outer molding line" (IML) or "outer molding surface"). [0003] A ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/32B29C70/44B29C33/48B64C1/06
CPCB64F5/10B64F5/50B29C33/485B29C70/32B29C70/446B64C1/068B29L2031/3082B64C2001/0072Y02T50/40B32B37/0046B32B37/1018B32B2309/68B32B2605/18
Inventor 萨巴托·因塞拉 因帕拉托彼得兰托尼奥·切雷塔
Owner ALENIA AERMACCHI