Longitudinal beam joint for a pressure deck assembly

Patent metadata

Field	Value
Publication number	US-11548607-B2
Application number	US-201916716379-A
Country	US
Kind code	B2
Filing date	Dec 16, 2019
Priority date	Dec 16, 2019
Publication date	Jan 10, 2023
Grant date	Jan 10, 2023

Abstract

A pressure deck assembly for a fuselage includes a longitudinal beam extending a length along a roll axis of the fuselage. The longitudinal beam includes a central member and opposing first and second flanges extending from the central member. The first flange includes a first upper side and a first lower side. The second flange includes a second upper side and a second lower side. The pressure deck assembly includes a pressure deck that includes first and second deck segments. The first deck segment is joined to the first flange of the longitudinal beam along the first lower side of the first flange. The second deck segment is joined to the second flange of the longitudinal beam along the second lower side of the second flange.

First claim

What is claimed is:

1. A pressure deck assembly for a fuselage, the pressure deck assembly comprising:
a longitudinal beam extending a length along a roll axis of the fuselage, the longitudinal beam comprising a central member and opposing first and second flanges extending from the central member, the first flange comprising a first upper side and a first lower side, the second flange comprising a second upper side and a second lower side,
a pressure deck comprising first and second deck segments, wherein the first deck segment is joined to the first flange of the longitudinal beam along the first lower side of the first flange, and wherein the second deck segment is joined to the second flange of the longitudinal beam along the second lower side of the second flange.

2. The pressure deck assembly of claim 1 , further comprising a second longitudinal beam extending the length along the roll axis of the fuselage, the second longitudinal beam comprising a second central member and opposing third and fourth flanges extending from the second central member, the third flange comprising a third upper side and a third lower side, the fourth flange comprising a fourth upper side and a fourth lower side, wherein the first deck segment is joined to the fourth flange of the second longitudinal beam along the fourth lower side of the fourth flange.

3. The pressure deck assembly of claim 1 , further comprising a splice extending a length from a first end portion to a second end portion, the first end portion of the splice being joined between the first flange of the longitudinal beam and the first deck segment of the pressure deck, the second end portion of the splice being joined between the second flange of the longitudinal beam and the second deck segment of the pressure deck.

4. The pressure deck assembly of claim 1 , wherein the central member of the longitudinal beam extends a height from a first end portion to a second end portion, the first and second flanges extending outward from the first end portion, wherein the first and second lower sides of the first and second flanges, respectively, face away from the second end portion of the central member.

5. The pressure deck assembly of claim 1 , wherein the first flange of the longitudinal beam extends from the central member such that the first flange and the central member form an L-shape, and wherein the second flange of the longitudinal beam extends from the central member such that the second flange and central member form an L-shape.

6. The pressure deck assembly of claim 1 , wherein a width of the pressure deck extends laterally across a width of the fuselage along a pitch axis.

7. The pressure deck assembly of claim 1 , wherein at least one of the first deck segment or the second deck segment of the pressure deck comprises a catenary shaped web.

8. The pressure deck assembly of claim 1 , wherein at least one of the first flange or the second flange is separated from the respective first or second deck segment by a predetermined distance that is configured to generate at least one closing moment that acts to close an angle between the central member and at least one of the first flange or the second flange under pressure loading.

9. The pressure deck assembly of claim 1 , wherein the central member of the longitudinal beam comprises first and second member segments joined together, the first flange extending from the first member segment, the second flange extending from the second member segment.

10. A pressure deck assembly for a fuselage, the pressure deck assembly comprising:
a longitudinal beam extending a length along a roll axis of the fuselage, the longitudinal beam comprising a central member and opposing first and second flanges extending from the central member, the first flange forming a first corner of the longitudinal beam with central member, the second flange forming a second corner of the longitudinal beam with the central member; and
a pressure deck comprising first and second deck segments, wherein the first deck segment is joined to the first flange of the longitudinal beam such that the first deck segment extends on an outside of the first corner of the longitudinal beam, and wherein the second deck segment is joined to the second flange of the longitudinal beam such that the second deck segment extends on an outside of the second corner of the longitudinal beam.

11. The pressure deck assembly of claim 10 , wherein the longitudinal beam comprises at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, or a thermoset carbon fiber composite material.

12. The pressure deck assembly of claim 10 , further comprising a splice extending a length from a first end portion to a second end portion, the first end portion of the splice being joined between the first flange of the longitudinal beam and the first deck segment of the pressure deck, the second end portion of the splice being joined between the second flange of the longitudinal beam and the second deck segment of the pressure deck.

13. The pressure deck assembly of claim 10 , wherein the first and second flanges of the longitudinal beam comprise respective first and second upper sides and respective first and second lower sides, the first lower side of the first flange defining a portion of the outside of the first corner, the first deck segment of the pressure deck being joined to the first flange along the first lower side of the first flange, the second lower side of the second flange defining a portion of the outside of the second corner, the second deck segment of the pressure deck being joined to the second flange along the second lower side of the second flange.

14. The pressure deck assembly of claim 10 , wherein at least one of the first deck segment or the second deck segment of the pressure deck comprises a catenary shaped web.

15. The pressure deck assembly of claim 10 , wherein at least one of the first flange or the second flange is separated from the respective first or second deck segment by a predetermined distance that is configured to generate at least one closing moment that acts to close an angle between the central member and at least one of the first flange or the second flange under pressure loading.

16. A fuselage for an aircraft, the fuselage comprising:
a pressure deck assembly comprising:
a longitudinal beam extending a length along a roll axis of the fuselage, the longitudinal beam comprising a central member and a flange extending from the central member, the flange comprising an upper side and a lower side; and
a pressure deck comprising a deck segment, wherein a width of the pressure deck extends laterally across a width of the fuselage along a pitch axis, and wherein the deck segment is joined to the flange of the longitudinal beam along the lower side of the flange.

17. The fuselage of claim 16 , wherein the longitudinal beam comprises at least one of a composite material, a carbon fiber composite material, a thermoplastic composite material, a thermoplastic carbon fiber composite material, a thermoset composite material, or a thermoset carbon fiber composite material.

18. The fuselage of claim 16 , wherein the central member of the longitudinal beam extends a height from a first end portion to a second end portion, the flange extending outward from the first end portion, wherein the lower side of the flanges faces away from the second end portion of the central member.

Assignees

• Boeing Co

Inventors

• Mclaughlin Mark R
• Ingham Steven D
• Cox Daniel J
• Lockin Charles B
• Vukosav Danilo

Classifications

• B64C1/18 Primary

  Floors · CPC title

• B64C2001/009

  comprising decompression panels or valves for pressure equalisation in fuselages or floors · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C1/00 Primary

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B64C1/069 Primary

  Joining arrangements therefor · CPC title