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Closed structure consisting of composite material

A closed structure, composite material technology, applied in aircraft parts, household components, household appliances, etc., can solve problems such as difficulty in designing Ω-shaped sections of longitudinal beams

Inactive Publication Date: 2012-02-08
AIRBUS OPERATIONS SL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These circumstances make it difficult to design the Ω-shaped section of the longitudinal beam while satisfying the aforementioned conditions

Method used

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  • Closed structure consisting of composite material
  • Closed structure consisting of composite material
  • Closed structure consisting of composite material

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Embodiment Construction

[0016] The invention disclosed below relates to a component 11 of an aircraft fuselage made of composite material as a single integral piece. figure 1 The part 11 is shown in the process of being demolded from the clamp 13 according to the demolding direction 35 .

[0017] Part 11 is generally frusto-conical or tubular, formed by an outer skin 21 and a plurality of omega-shaped longitudinal beams 23 within the outer skin. The clamp 13 includes a slot 15 similar in shape to the longitudinal beam 23 .

[0018] The process of manufacturing component 11 by using composite material (such as carbon fiber composite material CFC (Carbon Fiber Composite)) mainly includes: the first step, the Ω-shaped longitudinal rib 23 is arranged in the groove 15 in an "uncured" state; In the second step, the composite material is laminated on the jig to form the skin 21; in the third step, the part 11 is consolidated in a high-pressure vessel;

[0019] In order to demould the part 11 it must first...

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Abstract

The invention relates to a closed structure (11) consisting of a tubular composite material comprising a skin (21) and a plurality of longitudinal omega-shaped reinforcing stringers (23), such as a fuselage structure of an aircraft, wherein said structure is produced as a single piece on a male tool (13) consisting of a material having a higher contraction coefficient than that of the composite material, and is demoulded in a pre-determined direction. In said structure: a) the outer surface (31) of the skin (21) forms an angle = 0 with the demoulding direction (35); and b) each of the longitudinal stringers (23) has a trace (41) following a demoulding direction and a cross-section which maintains the height (Ho), the head length (Lho) and the length between the feet (Lfo) of the stringer constant along the trace (41).

Description

technical field [0001] The invention relates to a closed structure made of composite material as a single integral piece, for example part of an aircraft fuselage, the reinforcing beams of which have an omega-shaped cross-section. Background technique [0002] Patent application WO 2008 / 092971 discloses a closed structure of composite material for an aircraft fuselage formed on a male jig, capable of being separated from the aircraft fuselage in a defined direction. The structure is formed by an integral outer skin and omega-shaped internal longitudinal stiffeners integrated in the panels and reinforced with high pressure vessels. The male fixture consists of a housing for positioning the unhardened longitudinal beams to which the outer skin is bonded. The male fixture is made of aluminum, a material with a greater coefficient of contraction than composite materials, so that when the structure is removed from a high-pressure vessel When it comes out to cool, a gap develops ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C33/44B64C1/00B29C70/44B29L31/30
CPCB29C33/44B29C70/446B29L2031/3082B64C1/068B64C2001/0072Y02T50/40
Inventor 卡洛斯·迪阿兹坎加弗恩安德兹
Owner AIRBUS OPERATIONS SL
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