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Lining for an aircraft

A lining, aircraft fuselage technology, used in aircraft floors, aircraft accessories, fuselage and other directions

Inactive Publication Date: 2013-04-17
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, due to the stresses induced by insufficient elastic fastening of the panels forming the lining to the fuselage cells, the lining panels must be properly insulated from deformation of the fuselage cells

Method used

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  • Lining for an aircraft
  • Lining for an aircraft
  • Lining for an aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0028] In the figures, identical structural elements have in each case the same reference numerals.

[0029] figure 1 Shows the details of the lining in its normal state (i.e. with the lining board not lowered).

[0030] The lining 1 of the aircraft fuselage unit 2 is essentially formed by three lining panels 3 to 5 extending approximately horizontally. The lining panels 3 to 5 are formed in a known sandwich-type structure, for example with a honeycomb core and outer layers of fiber-reinforced polymer material applied on both sides. The lining 1 creates an intermediate space 6 which is separated from the interior space 7 of the aircraft fuselage unit 2 . In the region of the exterior space 8 outside the fuselage unit 2 , an atmospheric pressure is distributed, which corresponds to the altitude of the aircraft at approximately 0 hPa. In normal operating conditions of the aircraft, at an altitude of eg 10,000 meters, a pressure of approximately 500 hPa (corresponding to an a...

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PUM

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Abstract

A lining for an aircraft. The lining separates an intermediate space from an interior space of the aircraft in a pressuretight manner. The lining panels extend either substantially horizontally or are fastened approximately vertically on a lining framework formed by profiles for connection to the fuselage cell. At least one of the lining panels allows automatic pressure equalization between the interior space and the intermediate space in the event that the pressure in the interior space drops to something in the order of 0 hPa. This pressure corresponds to the air pressure prevailing at an altitude above 10,000 m. Mounts of the lining panels are provided with predetermined breaking points. The predetermined breaking points are formed in particular by plastic nuts, the thread of which tears away when a critical load-bearing capacity is exceeded.

Description

technical field [0001] The invention relates to a lining for an aircraft fuselage unit, comprising a plurality of lining panels adjoining each other, with an intermediate space present between the fuselage unit and the lining. [0002] Background technique [0003] Known configurations of lining panels for the lining of aircraft fuselage units, in particular used in propeller-powered aircraft, have to meet a number of requirements. [0004] First, the lining panels must have proper sound permeability. Also, the lining panels should provide adequate electromagnetic shielding in the event that electrical wires in the aircraft are not properly shielded. In addition, due to the stresses caused by insufficient elastic fastening of the panels forming the lining to the fuselage cells, the lining panels must be properly insulated from deformation of the fuselage cells. The lining panels themselves only resist pressure differences up to 80 hPa. Furthermore, in the event of a sudde...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/12B64C1/18
CPCF16B37/065F16B4/004B64C2001/009
Inventor 赫尔曼·本廷拉多斯拉夫·拉扎尔
Owner AIRBUS OPERATIONS GMBH
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