Fuselage sections having tapered wing rib interfaces

Patent metadata

Field	Value
Publication number	US-11401024-B2
Application number	US-201916597081-A
Country	US
Kind code	B2
Filing date	Oct 9, 2019
Priority date	Oct 9, 2019
Publication date	Aug 2, 2022
Grant date	Aug 2, 2022

Abstract

Fuselage sections having tapered wing rib interfaces are disclosed. A disclosed example apparatus includes a rib associated with a fuselage section, and a wing interface surface defined by the rib, where the wing interface surface is tapered relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section.

First claim

What is claimed is:

1. An apparatus comprising:
a rib associated with a fuselage section, the fuselage section including a cylindrical shaped portion that is contoured to the rib, the cylindrical shaped portion including:
a first taper relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section, and
a second taper angled inward relative to a vertical axis of the fuselage section; and

a wing interface surface defined by the rib, the wing interface positioned at a converging end of the second taper, the wing interface surface tapered relative to the longitudinal axis of the fuselage section from the aft end of the fuselage section to the fore end of the fuselage section.

2. The apparatus as defined in claim 1 , further including a blended curved contour of the fuselage section to transition the fuselage section to an adjacent fuselage section.

3. The apparatus as defined in claim 1 , wherein the wing interface surface tapers at an angle between approximately 0.8 degrees to 1.4 degrees from the aft end to the fore end.

4. The apparatus as defined in claim 1 , wherein an acute angle is defined in a space between a wing and the fuselage section.

5. The apparatus as defined in claim 4 , further including a blended contour extending across the space between the wing and the fuselage section.

6. The apparatus as defined in claim 5 , wherein the acute angle is defined by an angled wing splice bracket.

7. The apparatus as defined in claim 1 , wherein the wing interface surface tapers from a rear wing spar to a front wing spar.

8. The apparatus of claim 6 , wherein the angled wing splice bracket is positioned between the fuselage section and an upper surface of the wing at the second taper.

9. The apparatus of claim 8 , wherein the angled wing splice bracket includes:
a first panel to align the fuselage section at the second taper,
a second panel to align an outer wing section of the wing at the second taper; and
a third panel to align an inner wing section of the wing at the second taper.

10. The apparatus of claim 9 , wherein the angled wing splice bracket is a first angled wing splice bracket, and further including a second angled wing splice bracket to align the inner wing section relative to the outer wing section at a bottom surface of the wing.

11. The apparatus of claim 8 , wherein the blended contour extends between the fuselage section and the upper surface of the wing at the second taper, the angled wing splice bracket separate from the blended contour.

12. A fuselage section of an aircraft, the fuselage section comprising:
an outer surface to at least partially define an exterior of the aircraft, the outer surface at least partially defined by a cylindrical shaped portion of the fuselage section, the cylindrical shaped portion including:
a first taper relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section, and
a second taper angled inward relative to a vertical axis of the fuselage section; and

a rib to support a wing positioned at a converging end of the second taper, the rib defining a wing interface surface that exhibits a third taper, the third taper angled inward relative to the longitudinal axis of the fuselage section and extending from the aft end of the fuselage section to the fore end of the fuselage section, the cylindrical shaped portion contoured to the rib.

13. The fuselage section as defined in claim 12 , wherein the wing interface surface tapers at an angle between approximately 0.8 degrees to 1.4 degrees from the aft end to the fore end.

14. The fuselage section as defined in claim 12 , wherein the wing interface surface tapers between from a rear wing spar to a front wing spar.

15. The fuselage section as defined in claim 12 , wherein an acute angle is defined in a space between the wing and the fuselage section.

16. The fuselage section as defined in claim 15 , further including a blended contour extending across the space between the wing and the fuselage section.

17. The fuselage section as defined in claim 15 , wherein the acute angle is defined by an angled wing splice bracket.

18. The fuselage section as defined in claim 12 , further including a blended curved contour to transition the rib to the outer surface of the fuselage section.

19. A method of producing a fuselage section, the method comprising:
orienting a rib relative to a longitudinal axis of the fuselage section, the rib to be angled from the longitudinal axis to define a tapered wing interface at which a wing is to be supported; and
coupling the rib to the fuselage section, the fuselage section having a cylindrical shaped portion that is contoured to the rib, the cylindrical shaped portion including:
a first taper relative to the longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section, and
a second taper angled inward relative to a vertical axis of the fuselage section, wherein the wing is to be coupled to the fuselage section positioned at a converging end of the second taper.

20. The method as defined in claim 19 , further including coupling the fuselage section to an adjacent fuselage section.

21. The method as defined in claim 20 , further including forming a blended contour between the fuselage section and the adjacent fuselage section.

22. The method as defined in claim 19 , further including coupling the wing to the fuselage section via the rib, wherein an acute angle is defined between the fuselage section and the wing.

23. The method as defined in claim 22 , wherein the acute angle is defined by an angled wing splice plate operationally coupled between the wing and the fuselage section.

24. The method as defined in claim 22 , further including defining a blended contour between the wing and the fuselage section.

Assignees

• Boeing Co

Inventors

• Rosman Richard R
• Cominsky Kenneth D
• Lakic Branko

Classifications

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/187

  Ribs · CPC title

• B64C1/26 Primary

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64U20/70

  Constructional aspects of the UAV body · CPC title

• B64C1/068 Primary

  Fuselage sections · CPC title