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Aircraft cabin window assembly method

A technology for aircraft and portholes, applied in the field of assembling portholes, can solve problems such as increased instrument maintenance costs, mechanical stability limitations, and increased bracket maintenance.

Inactive Publication Date: 2009-12-16
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, opening holes in the fuselage shell of synthetic material is very limited in terms of mechanical stability
[0016] [16] It can be observed that some brackets are very fragile and lead to increased repairs, thereby increasing the maintenance cost of the instrument

Method used

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  • Aircraft cabin window assembly method
  • Aircraft cabin window assembly method
  • Aircraft cabin window assembly method

Examples

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Embodiment Construction

[0049] [49] image 3 A partial sectional view is shown of a porthole mounted on an opening formed in a side wall of an aircraft fuselage according to a particular embodiment of the invention.

[0050] [50] The porthole comprises an outer transparent element 10 and an inner transparent element 11 . The outer transparent element 10 is mounted on an opening formed in a side wall 12 of the aircraft fuselage. The fuselage can be metal, or made of a synthetic material such as carbon fibre.

[0051] [51] The outer transparent element 10 is a one-piece piece. The outer transparent element comprises a first portion 13 having a diameter greater than the diameter of the opening. The first portion 13 comprises a partially chamfered edge 14 . The rim 14 thus has two substantially flat surfaces connected to each other by a bevel, so that it can be seen that the diameter of the first portion is reduced relative to its outermost surface 15 . As for its outermost surface 15, its shape ens...

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Abstract

The invention relates to a method for assembling a cabin window to a bay in a side wall (12) of an aircraft fuselage, said cabin window comprising an outer transparent element (10) and at least one inner transparent element (11). According to the invention, a non-through hole is made in a portion of the side wall (12) along the edge of the bay. Subsequently, the outer transparent element (10) is positioned in the bay from the exterior of the fuselage, said element including a first part (13) which has a diameter greater than that of the bay and which is shaped to co-operate with the above-mentioned portion such as to block the outer transparent element (10) in the bay both laterally and longitudinally. The outer transparent element (10) also includes a second part (16) having a groove (17) that projects into the fuselage.; The outer transparent element (10) and the at least one inner transparent element (11) are welded to the fuselage using a strap (22) which presses a seal (21) against at least the fuselage and the inner wall of the groove (17).

Description

technical field [0001] [01] The present invention relates to a method of fitting a porthole over an opening defined in a side wall of an aircraft fuselage. Background technique [0002] [02] Commercial aircraft are known to comprise a typically quasi-cylindrical fuselage reinforced by stiffening elements such as stringers and frames in order to be able to withstand mechanical stresses imposed, for example, in flight. [0003] [03] In, for example, commercial aircraft, openings are realized in the side walls of the fuselage to receive portholes and to allow passengers a direct view of the environment outside the fuselage. [0004] [04] However, this porthole creates a number of disadvantages. First of all, the aircraft portholes should ensure the heat and sound insulation between the interior space of the fuselage and the exterior, so as to ensure the comfort of passengers. Likewise, portholes need to be airtight and watertight. [0005] [05] The porthole frames, which are...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/14
CPCB64C1/1492Y10T29/49826B64C1/14B60J1/00E06B3/04E06B3/54
Inventor G·加朗D·阿格拉P·贝纳代特
Owner AIRBUS OPERATIONS (SAS)
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