Autonomous flexible manufacturing system for building a fuselage

Patent metadata

Field	Value
Publication number	US-10213823-B2
Application number	US-201414559518-A
Country	US
Kind code	B2
Filing date	Dec 3, 2014
Priority date	Jul 9, 2014
Publication date	Feb 26, 2019
Grant date	Feb 26, 2019

Abstract

A method and apparatus for building a fuselage assembly for an aircraft. A number of fixtures may be drive across a floor to an assembly area to form an assembly fixture. The fuselage assembly may be built on the assembly fixture.

First claim

What is claimed is:

1. A method for building a fuselage assembly for an aircraft, the method comprising:
driving a tower across a floor into a selected tower position relative to a utility fixture selected from a plurality of utility fixtures in an assembly area, wherein the tower comprises a top platform that is configured to provide access to a top floor of an interior of the fuselage assembly by a human operator or an internal mobile platform moving across the top platform onto the top floor of the interior of the fuselage assembly and a bottom platform that is configured to provide access to a bottom floor of the interior of the fuselage assembly by the human operator or the internal mobile platform moving across the bottom platform onto the bottom floor of the interior of the fuselage assembly;
physically coupling the tower to the utility fixture by a first physical interface such that a number of utilities flow from the utility fixture to the tower through the first physical interface, wherein the number of utilities comprise at least one of electricity, air, hydraulic fluid, and water;
driving a cradle fixture across the floor into a selected cradle position relative to the tower in the assembly area to form an assembly fixture;
physically coupling the cradle fixture to the tower by a second physical interface to such that the number of utilities flow downstream from the tower to the cradle fixture through the second physical interface; and building the fuselage assembly on the assembly fixture;
driving a number of the internal mobile platforms autonomously from the tower into the interior of the fuselage assembly; and
building the fuselage assembly on the assembly fixture.

2. The method of claim 1 , wherein building the fuselage assembly comprises:
building the fuselage assembly on the assembly fixture using a plurality of mobile platforms.

3. The method of claim 2 further comprising:
distributing the number of utilities to the plurality of mobile platforms through a distributed utility network.

4. The method of claim 1 , wherein driving the cradle fixture comprises:
driving the cradle fixture autonomously into the selected cradle position to form the assembly fixture.

5. The method of claim 1 , wherein coupling the tower to the utility fixture comprises:
coupling the tower to the utility fixture autonomously.

6. The method of claim 1 , wherein building the fuselage assembly comprises:
engaging a plurality of fuselage sections for the fuselage assembly with the assembly fixture.

7. The method of claim 6 , wherein engaging the plurality of fuselage sections comprises:
engaging a plurality of panels with the assembly fixture.

8. The method of claim 7 , wherein engaging the plurality of panels with the assembly fixture comprises:
engaging keel panels in the plurality of panels with the assembly fixture;
engaging side panels in the plurality of panels with the keel panels; and
engaging crown panels in the plurality of panels with the side panels.

9. The method of claim 8 , wherein engaging the plurality of panels with the assembly fixture further comprises:
engaging an end panel with the assembly fixture and at least one of the keel panels, the side panels, or the crown panels, wherein the end panel is selected from one of a cone-shaped panel, a cylindrically-shaped panel, and a tapered cylindrical panel.

10. The method of claim 8 , wherein engaging the keel panels of the plurality of panels with the assembly fixture comprises:
engaging the keel panels with a number of retaining structures.

11. The method of claim 7 , wherein building the fuselage assembly further comprises:
connecting, temporarily, the plurality of panels to each other.

12. The method of claim 11 , wherein connecting, temporarily, the plurality of panels comprises:
tacking the plurality of panels together with temporary fasteners.

13. The method of claim 7 , wherein building the fuselage assembly further comprises:
joining the plurality of panels together while the plurality of panels are being supported by the assembly fixture.

14. The method of claim 13 , wherein joining the plurality of panels together comprises:
joining a first panel and a second panel together by at least one of fastening the first panel directly to the second panel, joining a first member associated with the first panel to a second member associated with the second panel, joining a member associated with the first panel directly to the second panel, joining one member associated with both the first panel and the second panel to another member, or joining a selected member to both the first panel and the second panel.

15. The method of claim 14 , wherein joining the plurality of panels together comprises:
installing a plurality of fasteners substantially autonomously to join the plurality of panels together.

16. The method of claim 1 further comprising:
supporting a plurality of panels and a plurality of members associated with the plurality of panels for the fuselage assembly using the assembly fixture during building of the fuselage assembly.

17. The method of claim 1 further comprising:
maintaining a shape and a configuration of the fuselage assembly within selected tolerances using the assembly fixture during the building of the fuselage assembly.

18. The method of claim 1 further comprising:
adjusting cradle fixture during building of the fuselage assembly to maintain compliance with outer mold line requirements and inner mold line requirements for the fuselage assembly within selected tolerances.

19. The method of claim 1 , wherein building the fuselage assembly comprises:
joining a plurality of panels together using an autonomous tooling system.

20. The method of claim 1 , wherein building the fuselage assembly comprises:
driving an external mobile platform to an external position relative to a location on the fuselage assembly; and
driving the internal mobile platform to an internal position relative to the location on the fuselage assembly.

21. The method of claim 20 , wherein driving the external mobile platform comprises:
driving the external mobile platform autonomously to the external position; and

wherein driving the internal mobile platform comprises:
driving the internal mobile platform autonomously to the internal position.

22. The method of claim 21 , wherein building the fuselage assembly further comprises:
performing a fastening process autonomously at the location on the fuselage assembly using the internal mobile platform and the external mobile platform.

23. The method of claim 22 , wherein performing the fastening process comprises:
drilling a hole at the location autonomously using at least one of the external mobile platform or the internal mobile platform;
inserting a fastener into the hole autonomously using the at least one of the external mobile platform or the internal mobile platform; and
installing the fastener autonomously using the at least one of the external mobile platform or the internal mobile platform.

24. The method of claim 1 further comprising:
accessing the interior of the fuselage assembly using the tower.

25. The method of claim 1 , wherein building the fuselage assembly comprises:
performing operations autonomously within the interior of the fuselage assembly using the number of internal mobile platforms.

26. The method o

Assignees

• Boeing Co

Inventors

• Oberoi Harinder S
• Sarh Branko
• Findlay Melissa Ann
• Draper Alan S
• Arriaga Jorge Alberto
• Reese Iv Richard Griffith
• Gerosa Alfredo Jose
• Barrick Kevin Marion
• Kozak Michael J
• Do Quang T
• Miller Jeffrey Lawrence
• Hu Yuanxin Charles

Classifications

• G05B19/41865

  characterised by job scheduling, process planning, material flow · CPC title

• B21J15/02 Primary

  Riveting procedures · CPC title

• B29C39/22

  Component parts, details or accessories; Auxiliary operations · CPC title

• B25J5/007

  mounted on wheels · CPC title

• B60G7/001

  Suspension arms, e.g. constructional features (B60G7/006 takes precedence) · CPC title