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System and method for integrating structural components of wing box

A technology for structural components and integrated wing boxes, applied in the field of aircraft, to solve problems such as underutilization of composite materials

Active Publication Date: 2018-03-06
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, doing so does not take full advantage of the composite

Method used

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  • System and method for integrating structural components of wing box
  • System and method for integrating structural components of wing box
  • System and method for integrating structural components of wing box

Examples

Experimental program
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example

[0043] In the following examples, additional processes, systems, and methods are described in the context of integrating sections of sheet stringers and / or skin between the wing and central section.

[0044] Figure 16 is a block diagram of an aircraft 1600 in an exemplary embodiment. In this example, aircraft 1600 includes wing box 1610 including outboard section 1620 and central section 1630 . Each outboard section 1620 includes a sheet stringer (“panel”) 1640 . Each plate 1640 includes a plurality of layers 1645 each extending a different distance along the central section 1630 . Meanwhile, the central section 1630 includes a skin 1650 and a plate 1660 . Each layer 1665 of sheet stringers 1660 extends a different distance toward the outer section 1620 . Also shown is a thickened riser 1680 of the skin 1650 .

[0045] Referring more specifically to the accompanying drawings, available at as Figure 17 Methods of Aircraft Manufacturing and Maintenance as shown in 1700 a...

Embodiment approach

[0053] 1. A system comprising:

[0054] an outboard sheet stringer laterally oriented within the outboard section of the wing box and co-cured with the composite skin at the outboard section,

[0055] each outboard sheet stringer comprises a planar ply of carbon fiber reinforced polymer (CFRP) parallel to the composite skin of the outboard section with aligned fiber orientation to withstand the tension and compression applied to the wing box, and each planar layer extends a different distance along the composite skin of the outboard section toward the central section of the wing box, and

[0056] a central sheet stringer, laterally oriented within the central section and co-cured with the composite skin at the central section,

[0057] Each sheet stringer of the central section comprises a planar ply of CFRP parallel to the skin at the central section with aligned fiber orientation to withstand the tension and compression applied to the wing box, and each planar ply The comp...

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Abstract

Systems and methods are provided for integrating structural components of a wing box. One embodiment is a system that includes outboard planked stringers within an outboard section of a wing box and the outboard planked stringers are co-cured with composite skin at the outboard section. Each outboard planked stringer of the outboard section includes planar layers of Carbon Fiber Reinforced Polymer(CFRP) that are parallel with the composite skin at the outboard section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distancealong the composite skin at the outboard section. The system also includes center planked stringers within the center section and are co-cured with composite skin at the center section. Each center planked stringer of the center section includes planar layers of CFRP that are parallel with the composite skin at the center section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the skin at the center section.

Description

technical field [0001] This disclosure relates to the field of aircraft, and in particular, to structural components of aircraft wings. Background technique [0002] Structural components of aircraft wings are subjected to various forces during flight, takeoff, and landing. These structural components are also designed to meet numerous requirements (eg, bird strikes, lightning strikes, air loads, ground loads, fuel pressure, etc.), and meeting these requirements while adhering to cost and manufacturing constraints remains a complex process. [0003] A wide variety of techniques and designs exist for constructing aircraft wings. In particular, designs for airfoils utilizing composite components have become popular because these designs reduce weight and increase strength. However, composite aircraft wings are still complex to model and expensive to test. To meet all of the above requirements, engineers prefer to design composite parts that essentially follow existing desig...

Claims

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Application Information

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IPC IPC(8): B64C3/18B64C3/26
CPCB64C3/182B64C3/26B29C70/00B29D99/0014B29L2031/3085B64F5/10Y02T50/40B64C1/26
Inventor 马克斯·U·基什毛尔顿克莱顿·L·芒克
Owner THE BOEING CO