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Method for connecting a structural member made of a composite material to a tube

A technology of structural elements and composite materials, applied in the direction of household elements, connecting rods, tubular objects, etc., can solve the problems of heavy components, huge connections, and difficult manufacturing

Active Publication Date: 2012-05-02
SAFRAN LANDING SYSTEMS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Components then become heavier and more difficult to manufacture, and connections become bulkier

Method used

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  • Method for connecting a structural member made of a composite material to a tube
  • Method for connecting a structural member made of a composite material to a tube
  • Method for connecting a structural member made of a composite material to a tube

Examples

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Embodiment Construction

[0027] The invention is described below as applied to the field of aviation, and in particular to the field of landing gear. Of course, the invention is not limited to this type of application.

[0028] Figure 1 shows the nose wheel undercarriage of an aircraft comprising a strut 1 made of an aluminum alloy comprising a cylindrical part 2 with two side arms 4, 6 terminating in At the top of the reels 8, 9, these reels receive the articulation pins for connecting the struts to the aircraft. The strut 1 also includes fasteners 12 here in the form of two lugs forming forks (not shown) for receiving the strut in order to stabilize the undercarriage in the extended position.

[0029] A rod 14 is mounted to slide vertically in the cylindrical portion 2 of the strut 1 . The bottom of the rod 14 carries an axle 16 which receives the wheels. The rod 14 is connected by a torque link 18 to a steering member 20 fastened to the strut 1 , where the steering member includes a hydraulic br...

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PUM

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Abstract

The invention relates to a method for making a structural part comprising a tubular portion (30) from which a structural member made of a composite material protrudes, said method comprising the steps of: shaping a planar preform (59) including a stack of several fibre plies placed one on top of the other so that the plies are secured together on at least a portion of the preform intended to form a structure portion, and so that the plies are separable so as to form two opposite leaflets (54) on at least another portion of the preform intended to form a portion for connecting to the tube; inserting a tube (30) between the leaflets of the connection portion so that the leaflets at least partially surround said tube; connecting the tube to the preform so that the tube forms the tubular portion and so that the preform forms the structural member of the structural part.

Description

technical field [0001] The invention relates to a method of manufacturing a structural part, especially for the aeronautical field, comprising structural elements made of composite material and connected to pipes. Background technique [0002] The aircraft includes landing gear in which a primary structural member called a "strut" is typically pivotally mounted to the aircraft to enable the landing gear to retract into a housing within the aircraft after takeoff. The struts consist of a tube with a rod slidably mounted therein, the rod carrying the wheels at its bottom end. The struts also include structural elements, such as arms or webs, for connecting the tubes to the aircraft. In particular, some struts include side arms extending on either side of the tube and terminating in reels for receiving pins used to articulate the strut to the aircraft. [0003] Struts of that type are generally made of metal, such as aluminum or steel, especially as castings or forgings. It ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/24B29C70/86D03D11/02D03D25/00B64C25/02F16C7/00B29B11/04B29B11/16B29C70/44
CPCB29L2023/22Y02T50/43D10B2505/02B29L2031/3076B29C70/446B29C70/24B29B11/16D03D11/02D03D25/005B29C70/443B64C25/02B29B11/04Y02T50/433F16C7/026B29C70/86F16C2326/43Y10T156/1036Y10T74/2142Y10T156/1079Y10T156/1002Y10T156/1052Y10T74/2144Y10T156/1062Y10T156/1028Y10T156/1075Y10T156/1038Y02T50/40
Inventor J-P·瑟瑞P·邓里维
Owner SAFRAN LANDING SYSTEMS
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