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Co-cured spar and stringer center wing box

A technology of central wing box and stringers, applied in the field of central wing box, can solve the problems of limited space, additional weight of aircraft, and additional space occupied

Active Publication Date: 2019-03-05
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As a result, this relatively thick structure adds additional weight to the aircraft and can take up additional space, resulting in limited space for cargo and / or passengers

Method used

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  • Co-cured spar and stringer center wing box
  • Co-cured spar and stringer center wing box
  • Co-cured spar and stringer center wing box

Examples

Experimental program
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Embodiment Construction

[0018] As previously stated, there is a need to manufacture a wing box assembly that is less expensive, strong, and lightweight. To make the wing box less expensive and lightweight, the wing box structures described herein will selectively utilize composite spar associated with at least one of the composite upper wing skin, composite lower wing skin, and composite spar bar structure. The resulting composite assembly will have a co-cured fixation of the part with the wing box structure. Such a wing box structure would result in a cost effective and lightweight wing box structure with optimal strength provided by co-cured fixation of components within the wing box assembly.

[0019] refer to figure 1 , aircraft 10 in this example has wing box assembly 12 positioned within fuselage 14 . Wing box assemblies 12 are secured to and positioned between wings 16 and provide support and rigidity to wings 16 of aircraft 10 as previously described. Span W denotes the direction of the s...

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PUM

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Abstract

The invention discloses a co-cured spar and a stringer center wing box. A center wing box assembly for an aircraft which includes: a composite lower wing skin, a composite upper wing skin and a composite spar which extends between the composite lower wing skin and the composite upper wing skin. The center wingbox assembly further includes a composite stringer which extends along a web of the composite spar in a wing span direction. The composite spar has a co-cure securement with the composite lower wing skin and with the composite upper wing skin and the composite stringer has a co-cure securement with the web of the composite spar.

Description

technical field [0001] The present disclosure relates to a center wing box for a wing assembly of an aircraft, and more particularly to a co-cured center wing box assembly. Background technique [0002] A wing box is a structural component of an aircraft that provides support and rigidity to the aircraft's wings. The design of the wing box will vary depending on the size and function of the aircraft, and is usually positioned between the roots to which the wings are attached. The wing box is one of the strongest sections of the fuselage and usually includes multiple supporting spars. [0003] Wing boxes are positioned between and connected to the wings. Due to the weight of the wing itself and due to the fuel contained within the wing, the wing box will experience shear stress when the aircraft is on the ground. Wing boxes are subjected to stresses such as tension, compression, shear and torsion when the aircraft is in operation. The wing box absorbs some of the stress e...

Claims

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Application Information

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IPC IPC(8): B64C1/26
CPCB64C1/26B64C3/182B64C3/185B64C3/26Y02T50/40B29D99/001B29L2031/3085B64C3/20
Inventor 理查德·F·埃温
Owner THE BOEING CO