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Method of assembling aircraft pylon and aircraft pylon obtained by method

An assembly method and aircraft technology, which are applied in the layout/installation of power units, aircraft assembly, aircraft parts, etc., can solve the problems of increasing hanger assembly time, long and complicated installation operators, and limited accessibility.

Pending Publication Date: 2022-02-18
AIRBUS SAS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0016] According to this mode of operation, the accessibility of setting the internal system 44 inside the already assembled primary structure 20 is limited, which sometimes makes its installation lengthy and complicated for the operator
Furthermore, placing these internal systems 44 sequentially in the primary structure 20 tends to significantly increase the assembly time of the hanger

Method used

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  • Method of assembling aircraft pylon and aircraft pylon obtained by method
  • Method of assembling aircraft pylon and aircraft pylon obtained by method
  • Method of assembling aircraft pylon and aircraft pylon obtained by method

Examples

Experimental program
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Embodiment Construction

[0047] exist Figure 5 , 10 , 13, the main structure 50 of the aircraft hanger is shown, which includes:

[0048] - upper beam 52,

[0049] - lower beam 54,

[0050] - a front reinforcement 56 connecting the front end of the upper beam 52 and the front end of the lower beam 54,

[0051] - a rear stiffener 58 connecting the rear end of the upper beam 52 and the rear end of the lower beam 54,

[0052]- A first lateral panel 60 and a second lateral panel 62 connecting the upper beam 52 and the lower beam 54 and arranged on either side of the front reinforcement 56 and the rear reinforcement 58 .

[0053] According to one embodiment, the primary structure 50 comprises at least one intermediate reinforcement 64 connecting the upper beam 52 and the lower beam 54 in the form of a frame arranged in a transverse plane.

[0054] The aircraft pylon also includes a secondary structure covering and spaced from the primary structure 50; at least one internal system 66 positioned at lea...

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Abstract

The invention relates to a method of assembling an aircraft pylon. The aircraft pylon includes a main structure (50) and at least one internal system (66) positioned at least partially inside the main structure (50); the invention characterized in that the assembly method comprises: a first assembly step of assembling a part of the main structure to keep the interior of the main structure (50) accessible; a mounting step of mounting an internal system module (68), wherein the internal system module comprises at least one support (70) and at least one internal system (66) connected to the support (70); a second assembling step of assembling the internal system module (68) and the partially assembled main structure (50); and a third assembling step of assembling elements of the main structure (50) that are not assembled during the first assembling step. The invention also relates to an aircraft pylon obtained by this method.

Description

technical field [0001] The present application relates to a method for assembling an aircraft pylon and an aircraft pylon obtained by the method. Background technique [0002] according to figure 1 and figure 2 In the configuration seen in , aircraft 10 includes a plurality of propeller assemblies 12 positioned below wings 14 of aircraft 10 . [0003] The propeller assembly 12 includes an engine 16, a pod ( figure 2 not shown in ) and the pylon 18 ensuring the connection between the engine 16 and the wing 14 . The hanger 18 includes a rigid primary structure 20 and a secondary structure 22 (in Figure 4 ), the primary structure 20 notably ensures the transfer of stresses between the engine 16 and the rest of the aircraft 10 , the secondary structure 22 encloses the primary structure 20 and limits the head-on drag of the pylon 18 . According to one configuration, primary structure 20 is connected to engine 16 by engine attachment 24 and to wing 14 by wing attachment 26...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/26B64F5/10B64D27/40
CPCB64F5/10B64D27/404B64D27/40B64D27/402
Inventor S·阿尔比J·格利奥特T·德福雷特O·杜波依斯J·德迪乌X·巴德伊
Owner AIRBUS SAS