Autonomous flexible manufacturing system for building a fuselage

Patent metadata

Field	Value
Publication number	US-11724305-B2
Application number	US-201916284417-A
Country	US
Kind code	B2
Filing date	Feb 25, 2019
Priority date	Jul 9, 2014
Publication date	Aug 15, 2023
Grant date	Aug 15, 2023

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 flexible fuselage manufacturing system that comprises:
a utility fixture affixed to a floor of a manufacturing environment;
a drivable tower configured to transport a drivable internal mobile platform to an interior of a fuselage assembly;
an external end effector connected to a drivable external mobile platform and configured to:
drill, from an exterior of the fuselage assembly, a hole through a first panel and a second panel of the fuselage assembly; and
insert a fastener through the hole;

an internal end effector configured to fasten the fastener within the hole and connected to the drivable internal mobile platform within the interior of the fuselage assembly, the drivable internal mobile platform configured to:
drive autonomously within the interior of the fuselage assembly; and
maintain in tension, a utility cable that connects the drivable internal mobile platform within the interior of the fuselage assembly to the utility fixture through the drivable tower;

the utility cable connected to the utility fixture through the drivable tower; and
a number of drivable fixtures configured to support the fuselage assembly and to physically couple autonomously to the drivable tower such that a number of utilities flow from the utility fixture to the drivable tower and to the number of drivable fixtures.

2. The flexible fuselage manufacturing system of claim 1 , further comprising the internal end effector configured to control a riveting tool.

3. The flexible fuselage manufacturing system of claim 1 , wherein the drivable tower is an autonomously drivable tower configured to autonomously couple to the utility fixture and wherein the number of drivable fixtures comprise a number of autonomously drivable fixtures.

4. A flexible fuselage manufacturing system that comprises:
a utility fixture affixed to a floor of a manufacturing environment and configured to provide a direct connection of power;
a drivable external mobile platform that comprises an external end effector configured to:
drill a hole through a first panel and a second panel of a fuselage assembly; and
place a fastener in the hole with an interference fit; and

an internal end effector configured to fasten the fastener within the hole and connected to a drivable internal mobile platform configured to:
move autonomously within an interior of the fuselage assembly; and
maintain in tension, a utility cable that connects the drivable internal mobile platform to the utility fixture through a drivable tower configured to:
transport the drivable internal mobile platform to the interior of the fuselage assembly; and
physically couple autonomously with the utility fixture and connect power from the utility fixture to the drivable tower;

the utility cable connected to the utility fixture through the drivable tower; and
a number of drivable cradle fixtures configured to:
support the fuselage assembly;
physically couple autonomously in series to the drivable tower; and
connect the power from the drivable tower to the number of drivable cradle fixtures in series.

5. The flexible fuselage manufacturing system of claim 4 , wherein the utility fixture is coupled to a number of utility sources such that the utility fixture provides a number of utilities, wherein the number of utilities comprises air.

6. The flexible fuselage manufacturing system of claim 4 , wherein the number of drivable cradle fixtures form an assembly fixture when the number of drivable cradle fixtures are located in a number of selected cradle positions relative to each other.

7. The flexible fuselage manufacturing system of claim 4 , wherein the drivable internal mobile platform is configured to join a plurality of panels together to form the fuselage assembly on the number of drivable cradle fixtures.

8. The flexible fuselage manufacturing system of claim 7 , further comprising the internal end effector configured to control a riveting tool.

9. The flexible fuselage manufacturing system of claim 8 , wherein the drivable internal mobile platform comprises an autonomously drivable internal mobile platform.

10. The flexible fuselage manufacturing system of claim 8 , further comprising the external end effector configured to control a second riveting tool.

11. The flexible fuselage manufacturing system of claim 10 , wherein the drivable external mobile platform comprises an autonomously drivable external platform.

12. The flexible fuselage manufacturing system of claim 4 , wherein the drivable tower comprises an autonomously drivable tower.

13. The flexible fuselage manufacturing system of claim 12 , wherein the autonomously drivable tower is configured to autonomously couple to the utility fixture.

14. The flexible fuselage manufacturing system of claim 12 , wherein the number of drivable cradle fixtures is a number of autonomously drivable cradle fixtures.

15. The flexible fuselage manufacturing system of claim 4 , wherein the utility fixture is coupled to a number of utility sources such that the utility fixture is configured to provide a number of utilities in addition to the power.

16. The flexible fuselage manufacturing system of claim 4 , further comprising the internal end effector configured to control at least one of: an internal drilling tool, an internal fastener insertion tool, an internal fastener installation tool, or an internal inspection tool.

17. The flexible fuselage manufacturing system of claim 2 , further comprising the external end effector configured to control a second riveting tool.

18. The flexible fuselage manufacturing system of claim 1 , further comprising the internal end effector configured to control at least one of: an internal drilling tool, an internal fastener insertion tool, an internal fastener installation tool, an internal inspection tool.

19. The flexible fuselage manufacturing system of claim 1 , wherein the number of utilities comprises air.

20. The flexible fuselage manufacturing system of claim 1 , wherein the number of utilities comprises power.

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

• B64C1/06

  Frames; Stringers; Longerons {; Fuselage sections} · CPC title

• B64C1/068

  Fuselage sections · CPC title

• B64C1/00 Primary

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B64C1/069

  Joining arrangements therefor · CPC title

• B21J15/28 Primary

  Control devices specially adapted to riveting machines not restricted to one of the preceding subgroups · CPC title