Aircraft cabin panel for sound reduction

A technology for aircraft cockpits and panels, applied to aircraft parts, fuselage, weight reduction, etc., to achieve the effects of improving sound absorption characteristics, simplifying processing, and simplifying manufacturing

Inactive Publication Date: 2011-11-23
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the increased weight represents an economical and also ecological disadvantage in the operation of an airplane or other aircraft

Method used

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  • Aircraft cabin panel for sound reduction
  • Aircraft cabin panel for sound reduction
  • Aircraft cabin panel for sound reduction

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0121] figure 1 An aircraft 10 is shown, which has a fuselage 12 and two wings 14 attached laterally to the fuselage, on which engines 15 are arranged. fuselage 12 in figure 1 It is shown in section transverse to its longitudinal axis. The fuselage 12 is divided by a horizontally extending floor 20 into an upper passenger cabin area 16 and a cargo area 18 arranged below the upper passenger cabin area. Furthermore, the fuselage 12 has a substantially surrounding outer aircraft skin 22 which is fastened to an aircraft fuselage structure (not shown in detail). In simple terms, the aircraft fuselage structure consists of a support structure consisting of bulkheads and stringers and ensures a stable design for absorbing external and internal loads.

[0122] In the cabin area 16 arranged above the floor 20 there are lateral cabin linings 24 , 26 along the outer wall 22 and a roof cabin lining 28 in the roof area.

[0123] The elements of the cabin lining 24 , 26 , 28 together wi...

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PUM

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Abstract

An aircraft cabin panel (40) is provided for sound reduction in an interior space, which has in at least one region a sandwich construction comprising a core layer (50), a first outer layer (52) and a second outer layer (54). The core layer consists of a sound-absorbing open-pore core material. The first and second outer layers are joined to the core layer over their surface area. The first outer layer is arranged in the direction of the sound waves to be absorbed and the second outer layer is arranged opposite the first outer layer. The first outer layer is formed so as to be acoustically transparent.

Description

technical field [0001] The invention relates to an aircraft cabin panel for sound attenuation in an interior space. The invention also relates in particular to an aircraft having an interior space lining with sound-absorbing and sound-insulating panels. Background technique [0002] In aircraft, sound-damping panels are used in the region of the cockpit in order to improve the acoustics of the interior of the cockpit by reducing disturbing sounds with the help of the panels. In general, as the requirements for spatial comfort increase, so do the requirements for the quality of the dwelling in the aircraft, since in addition high requirements are also placed on the acoustics of the room during flight operations. For this purpose, it is desirable to use wall panels for sound absorption in the interior of, for example, an aircraft cabin, in order to minimize the noise load inside the cabin. The noise to be reduced is, for example, the noise generated by the engine, the noise ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/06B64C1/40G10K11/16
CPCY02T50/46G10K11/168B64C1/066B64C1/40Y02T50/40
Inventor 克里斯蒂安·托马斯弗洛里安·黑塞尔巴赫斯特凡·霍策尔特维尔弗里德·米凯利斯乌韦·施奈德拉尔夫·斯特姆阿尔诺·贝格尔
Owner AIRBUS OPERATIONS GMBH
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