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Fastening device for a module element in an airplane

A technology for aircraft and components, applied in the direction of friction-clamped detachable fasteners, mechanical equipment, connecting components, etc., can solve complex problems that do not allow assembly or disassembly, and achieve the effect of simplifying assembly and facilitating manufacturing

Inactive Publication Date: 2012-01-18
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although more complex fastening systems are able to reduce the transmission of vibrations, their complexity does not allow assembly or disassembly without the use of special tools
Moreover, the known fastening system provides for potential equalization for the individual components, which, in addition to the fastening system, must be connected to the ground of the aircraft, thus requiring additional assembly steps

Method used

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  • Fastening device for a module element in an airplane
  • Fastening device for a module element in an airplane
  • Fastening device for a module element in an airplane

Examples

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Embodiment Construction

[0040] figure 1 An embodiment of a fastening apparatus (generally indicated at 100 ) for fastening a modular element to an aircraft structure is shown. Features on the module side are indicated by reference numerals 2xx and features on the aircraft side by 3xx.

[0041] The fastening device 100 includes a shaft 110, which is figure 1 The end shown on the left has a widened head 112 and a section 114 axially behind it. The section 114 having a cylindrical basic form has two mutually parallel flat portions 116 defining a first lateral dimension L between them. 1 . perpendicular to the first lateral dimension L 1 , segment 114 has a second lateral dimension L 2 , the second lateral dimension L 2 greater than the first lateral dimension L 1 and corresponds to the diameter of the cylindrical basic form of the section 114 . The two circular sectors of segment 114 are thus located on an imaginary lateral cylindrical surface coaxial with axis 110 . In the illustrated embodime...

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PUM

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Abstract

A fastening device (100) for attaching a module element to a support structure (300) in an airplane is provided. The fastening device (100) comprises a stud (110), having a broadened head (112) at a first end for engaging in a support recess (302) of the support structure (300) and a section (114) that connects to the head (112) and has a first lateral dimension (L1) and a second lateral dimension (L2), which is disposed at least substantially perpendicularly to the first lateral dimension (L1) and is larger than the first lateral dimension (L1). At an opposite second end, the stud (110) is provided with a lever (150), which is connected to the stud (110) for rotation and can be moved into an opening position and a closing position.; A bushing (120), which is provided on the stud (110) so as to be moved longitudinally, is designed to support an outer wall (200) of the module element and supports an electrically conductive leaf spring (130) for contacting the outside of the outer wall (200) on the one side and the support structure (300) on the other side. An eccentric (158), which can be actuated by the lever (150), moves the bushing (120) along the stud (110) toward the head (112) during a movement of the lever (150) into the closing position thereof.

Description

technical field [0001] The invention relates to a fastening device for a module in a transport device, in particular a fastening device for a module element in an aircraft, and a fastening system comprising such a fastening device. Background technique [0002] Aircraft interiors are subject to special requirements. Modular construction is often desired to speed final assembly and simplify future maintenance by mounting subassemblies. For an exact fit, it must be possible to compensate for tolerances during final assembly anyway. For example, when a module has to be fitted into a recess, even if the visible surface of the module does not end flush with the adjoining edge of the recess, an undesired fit orientation can occur. [0003] Furthermore, the modules may comprise heavy supply units, such as those used for air conditioning or water supply and treatment on long-distance flights. The fastening device must be able to transfer the inertial forces of the heavy modules t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16B2/18
CPCF16B21/09F16B2/185Y10T403/55
Inventor 甘特尔・施米茨
Owner AIRBUS OPERATIONS GMBH
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