Trapezoidal panel pin joint allowing free deflection between fuselage and wing

Abstract

The invention is directed a trapezoidal panel pin joint for allowing deflection of an aircraft between a fuselage section and a wing section, wherein the pin joint comprises a vertical pin portion, a lug portion, and a clevis portion; wherein at least one vertical flexible tee member is positioned below the pin joint; and wherein the pin joint is coupled to at least two horizontal flexible tee members, such that the pin joint and vertical and horizontal flexible tee members, in combination, release two rotational degrees of freedom.

Description

BACKGROUND OF THE INVENTION[0001]1) Field of the Invention[0002]The invention relates to a pin joint in an aircraft fuselage. More particularly, the invention relates to a trapezoidal panel pin joint allowing free deflection between the fuselage and the wing of an aircraft.[0003]2) Description of Related Art[0004]In aircraft, large deflections between the wing and the fuselage due to wing bending can cause design and durability problems in the fuselage and fuselage to wing attachment structure. Known aircraft have wing to fuselage attachment structure that have accounted for this differential deflection by separating the top of the wing box and the fuselage with a horizontal flexible tee member. Known aircraft have a trapezoidal panel that is an extension of the wing rib at the wing / fuselage joint. Known trapezoidal panel designs have accounted for the differential deflection between the wing and the fuselage / fixed pressure deck by vertically separating the trapezoidal panel and fix...

AI Technical Summary

Benefits of technology

[0006]The invention satisfies this need for an improved pin joint design in an aircraft fuselage. None of the known pin joint designs provides all of the numerous advantages of the invention. Unlike known designs, the design of the invention provides the following advantages: the trapezoidal panel pin joint design reduces significant weight and significant risk of durability issues in service; the trapezoidal panel pin joint design alleviates the induced stresses by allowing free rotation at the upper surface of the wing aft spar by use of a vertically oriented pin and vertical and horizontal flexible tee members allowing an added degree of freedom, and thus, the design of the invention releases two rotational degrees of freedom; the trapezoidal panel pin joint design allows a high deflection in a localized area and then uses flexible attachments a short distance away from the flexible joint; the trapezoidal panel pin joint and flexible tee members reduce induced loading from wing bending and allow the overwing joint to flex with wing deflection and fuselage pressurization; the trapezoidal panel pin joint design allows a trapezoidal panel to be able to handle wing deflections without inducing high loads into the joint; the trapezoidal panel pin joint design allows the fixed pressure deck and floor beams to be located in close proximity to the wing upper surface on a composite or metal aircraft without inducing high deflections or point loads into the aircraft fuselage, and thus enables efficient space utilization by locating the fixed pressure deck and wing upper surface in close proximity to each other; and, the trapezoidal panel pin joint design allows weight and space saving within the composite structure architecture of an aircraft.

[0007]The invention provides for a trapezoidal panel pin joint to allow deflection of an aircraft between a fuselage section and a wing section, wherein the pin joint comprises a vertical pin portion, a lug portion, and a clevis portion; wherein at least one vertical flexible tee member is positioned below the pin joint; and wherein the pin joint is coupled to at least two horizontal flexible tee members, such that the pin joint and vertical and horizontal flexible tee members, in combination, release two rotational degrees of freedom. Preferably, the vertical flexible tee member has a vertical flexible rebate within the member, and the horizontal flexible tee member has a horizontal flexible rebate within the member. The pin joint allows a trapezoidal panel of the fuselage section to be able to handle deflections in the wing section without inducing high loads into the joint. In another aspect of the invention, the invention provides for a flexible fuselage point to enable deflection of an aircraft without high strain comprising a panel pin joint and flexible tee members that, in combination, release two degrees of freedom.

Problems solved by technology

In aircraft, large deflections between the wing and the fuselage due to wing bending can cause design and durability problems in the fuselage and fuselage to wing attachment structure.

However, such known designs can have less vertical distance to incur the large wing deflections, and this can induce stresses to the wing and fuselage.

This can increase the risk of durability of the parts, can require more structure, and can increase the weight of the aircraft.

In addition, known designs only release one rotational degree of freedom.

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