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Spar connecting structure of aircraft wing

A technology for connecting structures and spar, applied in the directions of wings, aircraft parts, chords/stringers, etc., can solve problems such as fatigue life reduction, galvanic corrosion, etc., and achieve the effect of avoiding galvanic corrosion

Inactive Publication Date: 2017-01-11
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The object of the present invention is to provide a spar connection structure of an aircraft wing, to solve the problems of galvanic corrosion and fatigue life reduction that exist when the spar connections made of composite materials

Method used

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  • Spar connecting structure of aircraft wing
  • Spar connecting structure of aircraft wing
  • Spar connecting structure of aircraft wing

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Experimental program
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Effect test

Embodiment 1

[0026] This embodiment provides a spar connection structure of an aircraft wing, such as figure 1 and figure 2 As shown, the spar connection structure of the aircraft wing includes a central wing spar 1, an outer wing spar 2 and a connecting assembly 3; the central wing spar 1 made of a composite material and the outer wing spar 2 made of a composite material are made of a titanium alloy or the connection assembly 3 made of aluminum alloy; at least one layer of insulation is provided between the contact surfaces of the connection assembly 3 made of aluminum alloy and the central wing spar 1 made of composite material and the outer wing spar 2 made of composite material layer (not shown in the figure). In this embodiment, the insulating layer is a layer of glass cloth, and other insulating materials may also be used to make the insulating layer. Due to the potential difference between the composite material and the aluminum alloy material, it is easy to cause galvanic corros...

Embodiment 2

[0039] In this embodiment, on the basis of Embodiment 1, the structure of the central wing spar 1 is further improved. The end of the central wing spar 1 close to the outer wing spar 2 is provided with a first gap along its width direction, and the upper flange of the central wing The outer surface of the butt joint corner box 31 at the first notch is on the same plane as the outer surface of the upper flange 12 of the central wing spar, and the outer surface of the butt joint corner box 32 at the first notch of the central wing lower flange is on the same plane as the central wing spar. The outer surfaces of the rim 13 lie on the same plane. Specifically, the part where the central wing upper flange butt joint corner box 31 connects to the central wing spar upper flange 12 and the central wing lower flange butt joint corner box 32 connects to the central wing spar lower flange 13 adopts a "Z" shape. Structural design retains as much of the central wing spar web 11 as possible...

Embodiment 3

[0042] The difference between this embodiment and Embodiment 1 lies in that the structures of the central wing spar 1 and the outer wing spar 2 are different. That is, the end faces of the central wing spar web 11, the central wing spar upper flange 12 and the central wing spar lower flange 13 at the end of the central wing spar 1 near the outer wing spar 2 are located on the same plane, and the outer wing spar 2 is close to the central wing spar. The end surfaces of the outer spar web 21 at one end of the wing spar 1 , the upper flange 22 of the outer wing spar and the lower flange 23 of the outer wing spar are located on the same plane.

[0043] Specifically, when processing the central wing spar 1 and the outer wing spar 2, the central wing spar web 11 near the outer wing spar 2, the central wing spar upper flange 12 and the central wing The end faces of the lower flange 13 of the beam are located on the same plane, and the end faces of the outer spar web 21 of the outer wi...

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Abstract

The invention discloses a spar connecting structure of an aircraft wing, comprising a central wing spar, an outer wing spar and a connecting component. The central wing spar made of composite materials and the outer wing spar made of composite materials are connected to each other through the connecting component made of titanium alloy or aluminum alloy; at least one contact layer is arranged between the connecting component made of the aluminum alloy and the contact face between the central wing spar made of the composite materials and the outer wing spar made of composite materials. The connecting component made of the titanium alloy material is connected with the central wing spar and the outer wing spar which are made of composite materials, thereby avoiding the galvanic corrosion. When the connecting component made of the aluminum alloy is connected with the central wing spar and the outer wing spar which are made of composite materials, the potential difference between the composite materials and the aluminum alloy material is solved through arranging the connecting component and the contact face between the central wing spar and the outer wing spar, happening of the galvanic corrosion is effectively avoided, and the service life of the wing is prolonged.

Description

technical field [0001] The invention relates to the technical field of aviation machinery, in particular to a spar connection structure of an aircraft wing. Background technique [0002] The connection of the aircraft wing is mainly the connection of the spar. There are two connection forms, one is the form of the butt joint structure, and the other is the form of the lap joint structure. The spars of the existing wings are usually metal spars or spars made of composite materials, and the connection between the metal spars is connected by a connection structure made of aluminum alloy. There is a problem of galvanic corrosion when the spar made of composite materials is connected through the connection structure made of aluminum alloy; in addition, if the connection end of the spar made of composite materials is cut, it is easy to cause delamination during use , thereby reducing the fatigue life of the spar. Contents of the invention [0003] The object of the present inv...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/18
CPCB64C3/182Y02T50/40
Inventor 刘传军王海军季少华梁斌李星王栋
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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