PANEL ASSEMBLY FOR AN AIRCRAFT FUSELAGE

Title:

PANEL ASSEMBLY FOR AN AIRCRAFT FUSELAGE

Document Type and Number:

WIPO Patent Application WO/2010/037964

Kind Code:

A3

Abstract:

The invention relates to a panel assembly for an aircraft fuselage, in which a first panel (10) and a second panel (20) respectively have a first end portion (11) and a second end portion (21) overlapping one another and connected to one another. The aim of the invention is particularly to limit the impact of the aerodynamic flow on the edge (25) of said second end portion (21) without impairing the mechanical aspect of the first panel (10). The aim is achieved by using a level difference (30) extending from said first end portion (11) opposite which the edge (25) of the second end portion (21) is located, the inner surface (14) of the first panel (10) having no level difference.

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Inventors:

CASTANET MARC-ANTOINE (FR)

Application Number:

PCT/FR2009/051847

Publication Date:

September 02, 2010

Filing Date:

September 29, 2009

Export Citation:

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Assignee:

AIRBUS OPERATIONS SAS (FR)
CASTANET MARC-ANTOINE (FR)

International Classes:

B64C1/12; B64C1/06; B64C3/26; F16B5/00

Domestic Patent References:

WO1994001277A1	1994-01-20
WO2007071905A1	2007-06-28

Foreign References:

EP1504888A1	2005-02-09
US2225779A	1940-12-24
US2228779A	1941-01-14
US5160771A	1992-11-03
DE19534031C1	1997-01-30
US5716178A	1998-02-10

Attorney, Agent or Firm:

AUGARDE, Eric et al. (56 boulevard de l'Embouchur, B.P. 27519 Toulouse Cedex 2, FR)

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