Keel beam assembly for an aircraft

Patent metadata

Field	Value
Publication number	US-12110094-B2
Application number	US-202217579241-A
Country	US
Kind code	B2
Filing date	Jan 19, 2022
Priority date	Jan 20, 2021
Publication date	Oct 8, 2024
Grant date	Oct 8, 2024

Abstract

The present disclosure provides a keel beam assembly, an aircraft including the keel beam assembly, and a method of aircraft manufacture using the keel beam assembly. An illustrative keel beam assembly comprises a pair of keel chords extending outside an aircraft fuselage and forming at least part of a lower keel box portion of a keel box. An upper keel box portion of the keel box is coupled to the pair of keel chords and has an aft end engaged with and secured to an aft wheel well bulkhead (AWWB).

First claim

What is claimed is:

1. A keel beam assembly, comprising:
a pair of keel chords extending outside an aircraft fuselage and forming at least part of a lower keel box portion of a keel box; and
an upper keel box portion of the keel box coupled to the pair of keel chords and having an aft end engaged with and secured to an aft wheel well bulkhead (AWWB),
wherein the AWWB includes a web, the upper keel box portion having a pair of side portions spaced laterally from one another, and an upper portion connecting the pair of side portions, wherein the pair of side portions are separately secured through the web to a backup structure engaged with an aft side of the web.

2. The keel beam assembly of claim 1 , wherein an aft portion of the keel box has a center of mass located within 10 centimeters of an envelope defined by an exterior surface of a skin of the aircraft fuselage.

3. The keel beam assembly of claim 1 , wherein the upper keel box portion is bolted to the AWWB.

4. The keel beam assembly of claim 1 , secured to a peripheral portion of the aircraft fuselage.

5. The keel beam assembly of claim 4 , wherein the keel box includes a body and one or more brackets fastened to the body, and wherein each bracket has one or more flanges engaged with the web of the AWWB and defining apertures through which the bracket is secured to the backup structure through the web using fasteners.

6. The keel beam assembly of claim 1 , further comprising a pair of aft chord extensions spliced to the pair of keel chords at aft ends of the keel chords and extending outside the aircraft fuselage.

7. The keel beam assembly of claim 1 , wherein the AWWB includes a web and a horizontal stiffener located on a forward side of the web, and wherein the upper keel box portion is engaged with and fastened to the horizontal stiffener.

8. The keel beam assembly of claim 1 , further comprising a clip having a first portion mounted to the keel box at one of the keel chords and a second portion engaged with and secured to a forward side of the AWWB.

9. The keel beam assembly of claim 1 , wherein the upper keel box portion is welded to the AWWB.

10. An aircraft, comprising:
a fuselage;
an aft wheel well bulkhead (AWWB) including a web;
a keel beam assembly including a pair of keel chords extending outside the fuselage and forming at least part of a lower keel box portion of a keel box, the keel beam assembly also including an upper keel box portion of the keel box coupled to the pair of keel chords and having an aft end mounted onto a forward side of the web of the AWWB; and
a backup structure engaged with an aft side of the web and secured to a peripheral portion of the fuselage, wherein;
the upper keel box portion has a pair of side portions spaced laterally from one another; and
each side portion is separately bolted through the web to the backup structure.

11. The aircraft of claim 10 , further comprising a pair of aft chord extensions spliced to the pair of keel chords at aft ends of the keel chords and extending outside the fuselage.

12. The aircraft of claim 10 , wherein an aft portion of the keel box has a center of mass located within 10 centimeters of an envelope defined by an exterior surface of a skin of the fuselage.

13. The aircraft of claim 10 , wherein each side portion is bolted through the web to a respective vertical beam of the backup structure.

14. The aircraft of claim 10 , wherein the keel box includes a body and one or more brackets fastened to the body, and wherein each bracket has one or more flanges engaged with the AWWB and defining apertures through which the bracket is mounted onto the AWWB.

15. The aircraft of claim 10 , wherein the backup structure includes a vertical beam.

16. The aircraft of claim 10 , wherein the aft end of the upper keel box portion is bolted to the backup structure, the backup structure being secured against the aft side of the web.

17. The aircraft of claim 10 , wherein the backup structure is comprised of a left vertical beam and a right vertical beam.

18. A method of aircraft manufacture using an aircraft section including a fuselage portion coupled to a pair of keel chords, wherein the keel chords extend outside the fuselage portion, form at least part of a lower keel box portion of a keel box, and are coupled to an upper keel box portion of the keel box, the method comprising:
mounting an aft end of the upper keel box portion onto a forward side of an aft wheel well bulkhead (AWWB),
wherein the AWWB includes a web, and wherein mounting includes bolting the upper keel box portion through the web of the AWWB to a vertical beam located on an aft side of the web.

19. The method of claim 18 , wherein the aircraft section is a first aircraft section, the method further comprising coupling the AWWB to a fuselage portion of a second aircraft section prior to mounting.

20. The method of claim 18 , wherein mounting comprises positioning the keel box such that no part of the keel box extends through the web.

Assignees

• Boeing Co

Inventors

• Vukosav Danilo
• Cox Daniel
• Potupchik Evgeny M
• Tummons James David
• Slater Ryan Matthew
• Portway Timothy R

Classifications

• B64C1/064 Primary

  Stringers; Longerons · CPC title

• B64C25/04

  Arrangement or disposition on aircraft · CPC title

• B64C1/069

  Joining arrangements therefor · CPC title

• B64C2025/125

  into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage · CPC title

• B64C1/10

  Bulkheads · CPC title