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Airplane wing assembly

A wing and aircraft technology, applied in the field of aircraft wing components, can solve the problems of difficult parts processing and difficult winglet alignment, etc.

Active Publication Date: 2015-01-21
COMAC +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the connection method used in this application is 14 hinge lugs, which need to meet the high-precision coaxiality requirements, the processing technology of the parts is difficult, and the alignment of the winglets is difficult to assemble.

Method used

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  • Airplane wing assembly
  • Airplane wing assembly
  • Airplane wing assembly

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Embodiment Construction

[0023] Preferred embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although preferred embodiments of the invention are shown in the drawings, it should be understood that the invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0024] figure 1 A schematic diagram showing the positional relationship between the wing and the winglet in the prior art. Such as figure 1 As shown in , the winglet 10 is located at the tip of the aircraft wing 20 and is connected with the wing 20 through a specific connecting piece. Wing 20 has a wing box (not shown) through which winglet 10 is connected to wing 20 .

[0025] According to an embodiment of the invention, the connection between the winglet ...

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PUM

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Abstract

The invention provides an airplane wing assembly. The airplane wing assembly comprises a wing, a small wing and a connection piece, wherein the wing is provided with a wing box; the small wing is located at a wing tip of the wing and is connected with the wing by the wing box; the connection piece comprises a butt joint rib which is assembled with the wing box and a central connector which is assembled with the small wing; the butt joint rib is provided with a first shearing pin hole and a second shearing pin hole; a first shearing pin and a second shearing pin are pressed into the first shearing pin hole and the second shearing pin hole respectively to form interference fit; the central connector is provided with a first lining hole and a second lining hole; a first lining and a second lining are pressed into the first lining hole and the second lining hole respectively to form interference fit; and the position relation between the first shearing pin hole and the second shearing pin hole is the same as the position relation between the first lining hole and the second lining hole, so that small interference fit can be realized between the first shearing pin and the second shearing pin and between the first lining and the second lining when the small wing provided with the central connector moves towards the wing box provided with the butt joint rib and when the first shearing pin and the second shearing pin are inserted into the first shearing pin hole and the second shearing pin hole in the central connector respectively.

Description

technical field [0001] The present invention relates to an aircraft wing assembly, and more particularly, provides an aircraft wing assembly capable of realizing interchangeable connection between winglets and wing boxes. Background technique [0002] Winglets are located at the tip of the wing. They are aerodynamic efficiency-sensitive components designed to reduce aircraft induced drag, reduce wingtip vortex, reduce aircraft fuel consumption, and improve aircraft competitiveness. Its installation attitude needs to be strictly guaranteed. At the same time, the small wing parts are located in the lightning protection zone I-A, and are easily damaged by lightning strikes or collisions with boarding bridges, other adjacent aircraft or buildings when the aircraft is parked. The winglet structure is small, and when there is a large degree of damage, considering maintenance, cost and aerodynamic efficiency factors, it is usually replaced directly. And the winglet is a closed str...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/52
CPCB64C3/187B64C23/069B64F5/00B64C3/52Y02T50/10
Inventor 廉伟李明刘建刚翁晨涛申德红刘艳凯何瑞张元卿许萌萌
Owner COMAC
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