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Composite wing edge attachment and method

A composite material and wing technology, applied in the direction of wings, aircraft assembly, aircraft parts, etc., can solve problems such as expensive, increased processing steps, and complexity

Active Publication Date: 2019-12-27
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These can be heavy, complicated and expensive to make
Some approaches to this problem add additional processing steps to ensure joint integrity

Method used

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  • Composite wing edge attachment and method
  • Composite wing edge attachment and method
  • Composite wing edge attachment and method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment approach

[0067] 1. A composite material fixed edge of an airplane wing, comprising:

[0068] Composite wing wing box skin panel, attached to the outer wing spar in the attachment area and with overhanging edges, with

[0069] A substantially constant thickness and number of layers in the attachment area; and

[0070] The composite bevel, on the outer surface of the composite wing box skin panel, and co-cured with the composite wing box skin panel, has a proximal end and a distal end, with the largest bevel thickness at the distal end, and the distal end is set outside Behind the overhanging edge, the shoulder defined on the overhanging edge; and

[0071] A composite wing edge skin panel, having a thickness substantially equal to the thickness of the maximum slope, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the slope.

[0072] 2. The composite material fixed wing edge according to item 1, wherein the composite material wing edge skin panel ...

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PUM

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Abstract

A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp (238), upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge (232), with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness (t) at the distal end (230), is the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel (216), having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Description

Technical field [0001] The present disclosure generally relates to aircraft wing construction. More specifically, the present disclosure provides systems and methods for attaching fixed leading and trailing edges of aircraft wings, especially composite wing structures. Background technique [0002] In recent years, aircraft manufacturing companies have developed a large number of aircraft design and aircraft manufacturing methods using carbon fiber composite materials and the like ("composite materials" or "CFCM"), such as graphite / epoxy and carbon fiber reinforced plastics ("CFRP"). Composite materials are significantly lighter than traditional aircraft materials (for example, aluminum, titanium, steel, and alloys of these), and can provide light weight and high strength, allowing for lighter, more energy-efficient and efficient aircraft. In some new aircraft, for example, most of the main structure (including the fuselage and wings) is made of composite materials. Some new ai...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/00
CPCB64C3/26B64C3/28B64F5/10
Inventor 克里斯·J·福斯特格雷戈里·M·圣蒂尼约翰·V·多维
Owner THE BOEING CO
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