Aircraft tail assembly

Patent metadata

Field	Value
Publication number	US-11420718-B2
Application number	US-202016832176-A
Country	US
Kind code	B2
Filing date	Mar 27, 2020
Priority date	Mar 27, 2020
Publication date	Aug 23, 2022
Grant date	Aug 23, 2022

Abstract

An aircraft tail assembly includes an aft fuselage section secured to a forward fuselage section, and includes a stiffener-reinforced pivot bulkhead defined by separate parts secured together by a first set of splices. A longeron extends longitudinally along the aft and forward fuselage sections, and includes a discontinuity adjacent a peripheral edge of the pivot bulkhead. The aircraft tail assembly includes a second set of splices that overlie the discontinuity. One of the second set of splices extends laterally over the longeron to bridge the discontinuity adjacent the peripheral edge of the pivot bulkhead, and another of the second set of splices extends longitudinally along the longeron to secure the longeron to the pivot bulkhead adjacent the discontinuity. A chord engages the peripheral edge of the pivot bulkhead to facilitate transfers of force loads from the bulkhead along a load path that includes the longerons and the splices.

First claim

The invention claimed is:

1. An aircraft tail assembly including an aft fuselage section joined to a forward fuselage section, the aircraft tail assembly comprising:
a pivot bulkhead formed of separate parts secured together by a first set of splices, the pivot bulkhead having a peripheral edge positioned at an interface of the aft and forward fuselage sections;
a longeron extending longitudinally through, and orthogonally relative to, the pivot bulkhead adjacent the peripheral edge thereof, the longeron having a discontinuity adjacent the peripheral edge;
wherein the longeron includes a web that extends laterally and an inner chord that extends vertically;
wherein the aircraft tail assembly includes at least one of a second set of splices extending laterally over the web and the inner chord of the longeron to bridge the discontinuity.

2. The aircraft tail assembly of claim 1 , further including a bulkhead chord secured to the peripheral edge of the pivot bulkhead to transfer flight force loads from the pivot bulkhead to the aft and forward fuselage sections.

3. The aircraft tail assembly of claim 2 , wherein the longeron is channel-shaped and includes an outer chord extending vertically, and wherein one of the second set of splices comprises a longeron inner chord splice that extends laterally over the web and the inner chord of the longeron to bridge the discontinuity.

4. The aircraft tail assembly of claim 3 , wherein one of the second set of splices comprises a longeron strap that extends longitudinally over the discontinuity of the longeron.

5. The aircraft tail assembly of claim 4 , wherein the longeron strap secures the longeron to the pivot bulkhead.

6. The aircraft tail assembly of claim 3 , wherein one of the second set of splices comprises a longeron clip, which extends longitudinally along the longeron, and secures the longeron to the pivot bulkhead adjacent to the discontinuity.

7. The aircraft tail assembly of claim 3 , wherein one of the second set of splices comprises a web splice plate that extends longitudinally along the web of the longeron.

8. The aircraft tail assembly of claim 2 , wherein the longeron, the pivot bulkhead, the bulkhead chord, and wherein the first set of splices and the second sets of splices are each formed of a composite fiber reinforced plastic.

9. The aircraft tail assembly of claim 1 , wherein the longeron borders a horizontal stabilizer opening of the forward fuselage section, and is configured to react fuselage loads at the horizontal stabilizer opening.

10. The aircraft tail assembly of claim 1 , wherein the pivot bulkhead comprises an upper header and a lower header, and a left header support and a right header support, each header support fixed to left and right sides, respectively, of the upper and lower headers.

11. The aircraft tail assembly of claim 10 wherein the each of the pivot bulkhead upper and lower headers and left and right header supports includes a plurality of vertical and lateral stiffeners.

12. The aircraft tail assembly of claim 10 , further including a T-chord framing each of the left and right header supports.

13. The aircraft tail assembly of claim 10 , wherein the upper header and the lower header, along with the left header support and the right header support collectively frame a tail plane access opening.

14. The aircraft tail assembly of claim 10 , wherein a left bulkhead T-chord frames the pivot bulkhead at the left header support, and a right bulkhead T-chord frames the pivot bulkhead at the right header support.

15. The aircraft tail assembly of claim 5 , wherein the longeron strap bridges the discontinuity on the outer chord of the longeron.

16. The aircraft tail assembly of claim 3 , wherein the inner chord splice is positioned on an underside of the longeron and bridges the discontinuity on the inner chord of the longeron.

17. An aircraft comprising:
an aircraft tail assembly including an aft fuselage section joined to a forward fuselage section;
a pivot bulkhead formed of separate parts secured together by a first set of splices, the pivot bulkhead having a peripheral edge positioned at an interface of the aft and forward fuselage sections;
a longeron extending longitudinally through, and orthogonally relative to, the pivot bulkhead adjacent the peripheral edge thereof, the longeron including a discontinuity adjacent to the peripheral edge;
wherein the aircraft tail assembly includes at least one of a second set of splices to bridge the discontinuity;
wherein the pivot bulkhead comprises an upper header, a lower header, a left header support and a right header support; and
wherein the left header support and the right header support are fixed to left and right sides, respectively, of the upper header and the lower header.

18. The aircraft of claim 17 , wherein the aircraft tail assembly further includes a bulkhead chord secured to the peripheral edge of the pivot bulkhead to transfer flight force loads from the pivot bulkhead to aft and forward fuselage sections, and wherein the longeron, the pivot bulkhead, the bulkhead chord, and the first set of splices and the second set of splices are each formed of a composite fiber reinforced plastic.

19. A method of making an aircraft tail assembly, the method including steps of:
forming an aircraft tail assembly to include an aft fuselage section and a forward fuselage section, and joining the aft and fuselage sections together;
forming a pivot bulkhead of separate parts, the separate parts being secured together by a first set of splices, the pivot bulkhead having a peripheral edge, the pivot bulkhead including an upper header, a lower header, a left header support and a right header support;
configuring and placing the peripheral edge at an internal interface of the aft and forward fuselage sections;
forming and placing a longeron longitudinally along both aft and forward fuselage sections, such that the longeron extends through, and orthogonally relative to, the pivot bulkhead, and adjacent the peripheral edge thereof, the longeron including a discontinuity positioned adjacent the peripheral edge;
providing at least one of a second set of splices to bridge the discontinuity; and
positioning a left header support and a right header support to left and right sides, respectively, of the upper header and the lower header.

20. The method of claim 19 , further including a step of securing a bulkhead chord to the peripheral edge of the pivot bulkhead.

Assignees

• Boeing Co

Inventors

• Joseph Joel Kevin
• Breedlove Max Tyler
• Diep Paul
• Newnham Peter John

Classifications

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C1/0685 Primary

  Tail cones · CPC title

• B64C1/10

  Bulkheads · CPC title

• B64C5/02

  Tailplanes · CPC title

• B64C1/069

  Joining arrangements therefor · CPC title