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Panel, component for an airplane airfoil comprising the panel, and method for producing the panel

A wing and aircraft technology, applied in the field of plates, components for aircraft wings with the plates, and used to manufacture the plates, can solve the problem of difficulty in adding honeycomb filling parts or ribs, increasing the complexity of box-shaped structure assembly and Manufacturing costs and other issues to achieve the effect of increased stability and damage resistance

Inactive Publication Date: 2014-09-03
空中客车简易股份公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the honeycomb filling or the ribs will increase the assembly complexity and manufacturing cost of the box structure
[0007] Moreover, it is difficult to add such honeycomb fillings or ribs in members with a box-shaped structure where space is small (such as flap trailing edges)

Method used

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  • Panel, component for an airplane airfoil comprising the panel, and method for producing the panel
  • Panel, component for an airplane airfoil comprising the panel, and method for producing the panel
  • Panel, component for an airplane airfoil comprising the panel, and method for producing the panel

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Embodiment Construction

[0021] In the following, the panel according to the invention is described as a preferred embodiment for a panel for a trailing edge of a flap in an aircraft wing. It should be noted that the trailing edge of the flap is only exemplary, and the embodiments described below do not limit the present invention. The panel according to the invention can be used in aircraft wings with box-shaped components, for example main wings, flaps, ailerons, slats, empennages or components thereof, such as flap trailing edges.

[0022] The flap includes a flap body and a trailing edge. refer to figure 1 , the trailing edge of the flap includes an upper skin 10 , a lower skin 20 , a front spar 30 and a closed end 40 . The upper skin 10 and the lower skin 20 respectively cover above and below the front spar 30 and the closed end 40, thereby forming a box-shaped structure.

[0023] Figures 2 and 3 show a panel according to an embodiment of the invention for replacing the upper skin 10 or the lo...

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PUM

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Abstract

The present invention relates to a panel, especially for a component having a box structure in an airplane airfoil, comprising a surface shaped body and grid-like reinforcement bars protruding from the body on one side of the body, and the body and the grid-like reinforcement bars are integral molded. Since the body and the grid-like reinforcement bars of the panel are integral molded, no additional connecting process is required, so that the disconnection phenomenon as happened between the skin and the stiffener or stringer of the prior art would not occur, and the assembly complexity can be decreased.

Description

technical field [0001] The invention relates to a panel, a box-shaped component for an aircraft wing comprising the panel and a method for producing the panel. Background technique [0002] There are various box-shaped components in aircraft wings, such as main wings, flaps, ailerons, slats, and empennages. A box structure generally consists of a skin and beams to support the skin. The skin is generally composed of sheet metal or composite material, and is connected to the beam by fasteners (such as rivets) or by bonding. [0003] During aircraft operation and maintenance, the member having a box-like structure is subjected to shear forces and tends to buckle due to its size, thereby reducing its stability. On the other hand, during the take-off and landing of the aircraft, the skin of the aircraft wing (especially the trailing edge of the flap) is often impacted by, for example, stones, which may leave dents on the surface of the skin. If the dent is too large or too dee...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/24B64C3/26
CPCB64C3/26B64C3/24
Inventor 刘东
Owner 空中客车简易股份公司
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