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Structure for assembly of the pressure bulkhead of an aircraft

A technology for assembling structures and pressures, applied in fuselage bulkheads, climate sustainability, air transportation, etc., can solve problems of disproportion, complex tools, frame delamination, etc.

Inactive Publication Date: 2014-12-17
AIRBUS OPERATIONS SL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

First, this solution would result in a disproportionate structural member design given the number of layers of oriented fibers that would have to be laid in order to give the frame the proper strength
Second, the manufactured frame is prone to delamination problems, especially at the intersection of the center web and upper flange, where forces perpendicular to the lamination will be concentrated
Third, due to the relatively complex shape of the frame section, this scheme will require relatively complex tools

Method used

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  • Structure for assembly of the pressure bulkhead of an aircraft
  • Structure for assembly of the pressure bulkhead of an aircraft
  • Structure for assembly of the pressure bulkhead of an aircraft

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0070] According to the reference numbers used in the figures, image 3 An A-A' section of one embodiment of the assembled structure of the present invention is shown.

[0071] The structure of the present invention provides a pressure bulkhead assembly 1 for an aircraft and a device for joining together the front 4 and rear 5 parts of the fuselage of the aircraft. The pressure partition 1 separates the pressurized area 2 from the unpressurized area 3 in the aircraft.

[0072] like image 3 As shown in , the embodiment includes a simple frame 18 having an upper flange 19 , a central web 20 and a lower flange 21 .

[0073] The corner ring 22 is riveted by the rear portion inclined upwardly and rearwardly towards the pressure partition wall 1 .

[0074] The simple frame 18 rests on the unslanted front part of the corner ring 22 , which in turn rests on the butt strap 23 . The assembly of simple frame 18, corner rings and butt straps 23 is riveted to the rear portion 7 of the...

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PUM

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Abstract

The structure comprises: a rim angle (22) with a front portion and a rear portion, the latter being slanted upward and backward and connected to the bulkhead (1); a simple frame (18), being connected to the front portion of the bulkhead (22); a buttstrap (23), being connected between the front portion of the rim angle (22) and the skin (6, 7) of the fuselage of the aircraft; and tension fittings (24, 25), being fitted between the buttstrap (23) and the longitudinal stringers (8, 9) of the fuselage.

Description

technical field [0001] The present invention is designed for use in the field of aircraft design and manufacture in the aviation industry. [0002] Purpose of invention [0003] As stated in the title of this specification, the object of the present invention is to provide an aircraft pressure partition assembly structure. [0004] The pressure partition is the element that isolates the pressurized area at the rear of the aircraft. From a structural point of view, the element is concave in shape from the pressurized area side and is substantially hemispherical, so that the material of the partition wall can be fully utilized to absorb the load caused by the pressure difference, hereinafter referred to as the pressure load. [0005] Another object of the present invention is to provide an assembled structure such that all the components included in the structure can be easily made of composite materials, thereby resulting in a reduction in weight, which is a decisive factor ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/10B29C70/30B29C70/48
CPCB64C1/10Y02T50/433Y02T50/40B29C70/30B29C70/48
Inventor E.维拉维拉雷斯I.奥顿赫南德斯
Owner AIRBUS OPERATIONS SL