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Pinned fuselage to wing connection

A technology for fixing connectors and pins, which is applied in the direction of connecting components, fuselages, thin plates, etc., and can solve the problems of increasing fuel consumption and operating costs

Active Publication Date: 2021-06-18
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Added weight increases fuel consumption and other aircraft operating costs

Method used

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  • Pinned fuselage to wing connection
  • Pinned fuselage to wing connection
  • Pinned fuselage to wing connection

Examples

Experimental program
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Effect test

Embodiment Construction

[0015] reference figure 1 The illustration illustrates the aircraft 110 including the body 120, the wing assembly 130, and the tail 140. The body 120 includes a skin and a reinforced sub-structure, such as a set of ring frames and reinforcements).

[0016] The body 120 has the following global (X-Y-Z) Cartesian coordinate system, regardless of which point (anywhere on the aircraft 110) does not change the orientation.

[0017] The x-axis = the axial direction of the head to the end of the machine and is the axis of rotation of the cylindrical portion of the body 120.

[0018] The Y-axis = from the middle of the body 120 toward the horizontal direction of the right wing tip.

[0019] The Z-axis = the vertical direction of the upper fingers (when the pen is straight and horizontally).

[0020] Wing assembly 130 can include a wing box, a leading edge, and a trailing edge. The wing case includes a front spar and a rear flange and a plurality of ribs between the spar. The spar extends ...

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Abstract

The present application discloses a pinned fuselage to wing connection. An aircraft comprising a fuselage, a wing assembly, and a pinned fuselage-to-wing connection comprising a forward pin joint, an aft pin joint, and an Middle pin joint between front pin joint and rear pin joint. The central pin joint has pins aligned in the axial direction and is configured to slide in the axial direction without transferring axial loads from the wing assembly to the fuselage. At least one of the forward pin joint and the trailing pin joint is constrained against translation in the axial direction.

Description

Background technique [0001] The pneumatic force applied to the wing of the aircraft causes the wing to be bent primarily vertically and distorted forward. In a large jet, these wing bendles can cause undesired loads in the body, resulting in a valid design of the wing and the body of the body ("connecting the wing to the body connection") challenge . These forces are mainly acting in the fuselage in the vertical direction, lateral direction, and axial direction. In addition, the vertical force produces a bending moment. The additional body load at the connector of the wing to the body is produced by changes in the pressure in the body. [0002] The connecting member of the "rigid" wing to the body can be designed to transfer all wing curved bend deflection to the body member at the connection interface. Therefore, these design causal to rotate and bend with the wings. "Compliant" wing to the body can be replaced to transfer vertical load, lateral load, and axial load without trans...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/26
CPCB64C1/26F16B5/0088B64F5/10
Inventor B·拉基奇D·H·雷柏
Owner THE BOEING CO