Integral central wing box made of composite materials

A central wing box and composite material technology, which is applied in the field of aerospace composite material structure design to achieve the effects of reduced workload, high dimensional accuracy, and reduced weight and cost

Active Publication Date: 2012-06-27
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to avoid the above disadvantages, the present invention adopts an integral composite center wing box and its manufacturing method, which solves the typical problems existing in the existing type of center wing box

Method used

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  • Integral central wing box made of composite materials
  • Integral central wing box made of composite materials
  • Integral central wing box made of composite materials

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Embodiment Construction

[0016] Hereinafter, a description of preferred embodiments of the present invention will be provided in detail with reference to the accompanying drawings.

[0017] figure 1 It is a structural schematic diagram of an integral composite center wing box according to an embodiment of the present invention. The central wing box of integral composite material according to the present invention comprises: a front beam 2, an upper wall plate 1, a lower wall plate 3 and a rear beam 4, wherein the upper wall plate 1 and the lower wall plate 3 are arranged oppositely, and the front beam 2 and the rear beam 4 The two sides of the central wing box are oppositely arranged and the respective two ends are respectively connected with the upper wall plate 1 and the lower wall plate 3, wherein the central wing box is composed of the upper wall plate 1 and the lower wall plate 3, the front beam 2 and the rear beam 4 Formed in one piece.

[0018] Further, the overall central wing box structure...

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Abstract

The invention provides an integral central wing box made of composite materials, which comprises a front beam, an upper wall plate, a lower wall plate and a rear beam, wherein the upper wall plate is over against the lower wall plate; the front beam and the rear beam are arranged over against each other on both sides of the central wing box, and both ends of the front beam and the rear beam are respectively connected with the upper wall plate and the lower wall plate; and the central wing box is integrated from the upper wall plate, the lower wall plate, the front beam and the rear beam. According to the integral central wing box, the advanced performance of the structure is improved and the sealing safety of an oil tank is improved, and the process manufacturing and assembly difficulty is reduced, so that the cost is reduced.

Description

technical field [0001] The invention relates to the structural design of aviation composite materials, in particular to an integral composite central wing box. Background technique [0002] Today's civil aircraft composite material structure design is developing rapidly, and the percentage of composite material structure weight in the total aircraft structure weight has become one of the important symbols to measure the advanced nature of aircraft. The central wing box of civil aircraft is divided into two types: metal central wing box structure and composite material central wing box structure: the metal central wing box is generally composed of front beams, upper wall panels, lower wall panels and rear beams through mechanical connections. Among them, the beam is generally composed of upper edge strips, webs and lower edge strips, and the wall panel skin is mostly composed of multiple pieces due to the size limitation of metal materials. [0003] The existing composite ma...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/00
Inventor 李庆飞崔卫军张明星刘婷吴承思汤平袁新浩葛建彪刘朝妮方芳
Owner COMAC
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