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Combination rib for aircraft wings

An aircraft and airfoil technology, which is applied in the directions of wings, aircraft parts, chords/stringers, etc., can solve the problems of inability to provide process access and poor construction manufacturability, so as to improve the manufacturability and construction efficiency, and solve the problem of poor construction access. Good results

Inactive Publication Date: 2019-01-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The web of the combined rib of the traditional aircraft wing is a whole, which cannot provide a process path when the web is installed, and the construction process is poor

Method used

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  • Combination rib for aircraft wings
  • Combination rib for aircraft wings

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specific Embodiment

[0017] The invention provides a combination rib of an aircraft wing, such as figure 1 As shown, it includes upper edge strip 1, lower edge strip 2, front web 3, rear web 4 and butt angle material 5, upper edge strip 1, lower edge strip 2, front web 3, rear web 4 and butt joint The angle material 5 is preferably made of aluminum alloy machined parts;

[0018] The cross-section of the upper edge strip 1 and the lower edge strip 2 is T-shaped, and its thickness is preferably 3mm to 5mm. Both sides of the upper edge strip 1 and the lower edge strip 2 along the span of the aircraft are provided with gaps, which are used for wall panels. The long stringer is inserted during docking, the upper edge of the front web 3 and the upper edge of the rear web 4 are fixed to the lower edge of the upper edge bar 1 through fasteners, and the lower edge of the front web 3 and the lower edge of the rear web 4 are both passed through The fastener is fixed to the lower edge of the lower edge strip...

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Abstract

The invention relates to the technical field of aircraft structural design, and specifically provides a combination rib for aircraft wings. The combination rib includes an upper edge strip, a lower edge strip, a leading web and a trailing web; the cross sections of the upper edge strip and lower edge strip are in T shapes; the upper edges of the leading web and trailing web are in fixation with the lower edge of the upper edge strip through fasteners; the lower edges of the leading web and trailing web are in fixation with the lower edge of the lower edge strip through the fasteners; the leading web is in fixation with the trailing web through a butt-jointed angle section whose cross section is in the T shape; the two side end faces of the leading web and trailing web are provided with vertical reinforcing ribs; the end faces of the leading web and trailing web are provided with auxiliary holes; horizontal reinforcing ribs are arranged on at least one side end face of the leading web and trailing web, and separately located on the upper and lower sides of the auxiliary holes. Craftsmanship and construction efficiency can be enhanced by dividing the web of the combination rib of anaircraft wing into the leading web and the trailing web and using the auxiliary holes arranged on the webs to install the webs for construction paths.

Description

technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to an aircraft wing surface composite rib. Background technique [0002] The web of the combined rib of the traditional aircraft wing is a whole, which cannot provide a process path when the web is installed, and the construction process is poor. Contents of the invention [0003] In order to overcome at least one defect in the above-mentioned prior art, the present invention provides an aircraft wing composite rib, comprising an upper edge strip, a lower edge strip, a front web and a rear web; [0004] The cross-sections of the upper edge strip and the lower edge strip are T-shaped, the upper edge of the front web and the upper edge of the rear web are fixed with the lower edge of the upper edge strip by fasteners, the lower edge of the front web and the lower edge of the rear web The edges are all fixed to the lower edge of the lower edge by fasteners, and the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/18
CPCB64C3/187
Inventor 王运锋杨立文韩全民
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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