Contour retention in segmented fuselage assemblies

Patent metadata

Field	Value
Publication number	US-10822071-B2
Application number	US-201816190381-A
Country	US
Kind code	B2
Filing date	Nov 14, 2018
Priority date	Jun 22, 2016
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

Systems and methods are provided for enforcing contours onto parts of an aircraft. One embodiment is a method for enforcing a contour onto aircraft parts. The method includes removably attaching segmented ring details to aircraft skin details, attaching stringers to skin details to create skin assemblies, positioning skin assemblies at a support structure defining a contour, and fastening frames to the skin assemblies to create a panel. The method also includes removably installing a spreader section onto the panel to complete assembly of a brace prior to removal of the panel, transporting the panel while the brace enforces the contour, attaching the brace to braces for other panels to form a barrel section of a fuselage for an aircraft while the brace enforces the contour, and removing the brace from the barrel section after the barrel section has been formed.

First claim

The invention claimed is:

1. An apparatus comprising:
fuselage contour tooling comprising:
a brace that removably mounts to an end of a panel and enforces a contour onto the panel, the brace comprising:
a segmented ring assembly attached to skin details of the panel;
a spreader bar attached to the segmented ring assembly at endpoints of an arc defined by the segmented ring assembly.

2. The apparatus of claim 1 wherein:
the brace enforces the contour regardless of whether the panel is separated from a support structure used to fabricate the panel.

3. The apparatus of claim 1 wherein:
the brace includes attachment points on the segmented ring assembly that enable attachment of the brace to braces for other panels.

4. The apparatus of claim 1 wherein:
the segmented ring assembly comprises multiple segments, and each segment is attached to a different skin detail of the panel.

5. The apparatus of claim 1 wherein:
the spreader bar forms a non-linear shape.

6. The apparatus of claim 1 wherein:
the spreader bar is rotatably attached to the segmented ring assembly.

7. The apparatus of claim 1 wherein:
the panel is a portion of aircraft fuselage and the brace enforces the contour onto the panel during transport of the panel.

8. The apparatus of claim 1 further comprising:
struts that attach the spreader bar to the segmented ring assembly.

9. A system comprising:
a support structure defining a contour for shaping panels;
a panel that is mounted to the supports, comprising:
multiple skin details that follow the contour; and
stringers and frames that attach the skin details together; and

a brace that is mounted to an end of the panel, is distinct from the support structure, and enforces the contour during transport of the panel, the brace comprising:
a segmented ring assembly attached to the skin details; and
a spreader bar attached to the segmented ring assembly at endpoints of an arc defined by the segmented ring assembly.

10. The system of claim 9 wherein:
the brace enforces the contour regardless of whether the panel is separated from the support structure.

11. The system of claim 9 wherein:
each skin detail comprises an aluminum sheet.

12. The system of claim 9 wherein:
the segmented ring assembly comprises one ring element attached to each skin detail in the panel.

13. The system of claim 9 wherein:
the spreader bar is rotatably attached to the segmented ring assembly.

14. The system of claim 9 further comprising:
struts that are rotatably attached to the spreader bar and are rotatably attached to the segmented ring assembly.

15. The apparatus of claim 1 wherein:
the brace further comprises a base to which struts are rotatably attached.

16. The apparatus of claim 1 wherein:
the brace further comprises attachment points disposed at the endpoints of the arc defined by the ring assembly, for attachment the spreader bar to the segmented ring assembly.

17. The apparatus of claim 1 wherein:
the brace defines an indented region.

18. The system of claim 9 wherein:
the brace further comprises a base to which struts are rotatably attached.

19. The system of claim 9 wherein:
the brace further comprises attachment points disposed at the endpoints of the arc defined by the ring assembly, for attachment the spreader bar to the segmented ring assembly.

20. The system of claim 9 wherein:
the brace defines an indented region.

Assignees

• Boeing Co

Inventors

• Payne James Steven

Classifications

• B64C1/26 Primary

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

• B64C1/068 Primary

  Fuselage sections · CPC title

• Y02T50/40

  Weight reduction · CPC title

• B64F5/10

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

• B64F5/50

  Handling or transporting aircraft components · CPC title