US 11,724,305 B2
Autonomous flexible manufacturing system for building a fuselage
Harinder S. Oberoi, Snohomish, WA (US); Branko Sarh, Huntington Beach, CA (US); Melissa Ann Findlay, Snohomish, WA (US); Alan S. Draper, Everett, WA (US); Jorge Alberto Arriaga, Kirkland, WA (US); Richard Griffith Reese, IV, Seattle, WA (US); Alfredo Jose Gerosa, Snohomish, WA (US); Kevin Marion Barrick, Kingston, WA (US); Michael J. Kozak, Snohomish, WA (US); Quang T. Do, Mukilteo, WA (US); Jeffrey Lawrence Miller, Mukilteo, WA (US); and Yuanxin Charles Hu, Newcastle, WA (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Feb. 25, 2019, as Appl. No. 16/284,417.
Application 16/284,417 is a division of application No. 14/559,518, filed on Dec. 3, 2014, granted, now 10,213,823.
Claims priority of provisional application 62/022,641, filed on Jul. 9, 2014.
Prior Publication US 2019/0184447 A1, Jun. 20, 2019
Int. Cl. B64F 5/10 (2017.01); B25J 9/16 (2006.01); B25J 11/00 (2006.01); B21J 15/28 (2006.01); B21J 15/02 (2006.01); B21J 15/10 (2006.01); B21J 15/14 (2006.01); B60G 3/14 (2006.01); B25J 5/00 (2006.01); B29C 65/70 (2006.01); F16B 19/06 (2006.01); B23P 19/10 (2006.01); B60G 7/00 (2006.01); B21J 15/32 (2006.01); B21J 15/40 (2006.01); G05B 19/418 (2006.01); B25B 5/16 (2006.01); B29C 39/12 (2006.01); B29C 39/22 (2006.01); B64C 1/06 (2006.01); G05D 1/00 (2006.01); G05D 3/12 (2006.01); B29C 45/14 (2006.01); B29C 39/02 (2006.01); B29C 39/10 (2006.01); B64F 5/50 (2017.01); B23P 21/00 (2006.01); B29L 31/00 (2006.01); B60P 3/025 (2006.01)
CPC B21J 15/28 (2013.01) [B21J 15/02 (2013.01); B21J 15/10 (2013.01); B21J 15/142 (2013.01); B21J 15/32 (2013.01); B21J 15/40 (2013.01); B23P 19/10 (2013.01); B25B 5/163 (2013.01); B25J 5/007 (2013.01); B25J 9/1682 (2013.01); B25J 9/1687 (2013.01); B25J 9/1697 (2013.01); B25J 11/005 (2013.01); B25J 11/007 (2013.01); B29C 39/026 (2013.01); B29C 39/10 (2013.01); B29C 39/123 (2013.01); B29C 39/22 (2013.01); B29C 45/14336 (2013.01); B29C 65/70 (2013.01); B60G 3/145 (2013.01); B60G 7/001 (2013.01); B60G 7/008 (2013.01); B64C 1/06 (2013.01); B64F 5/10 (2017.01); B64F 5/50 (2017.01); F16B 19/06 (2013.01); G05B 19/41805 (2013.01); G05D 1/0088 (2013.01); G05D 3/12 (2013.01); B23P 21/002 (2013.01); B23P 2700/00 (2013.01); B23P 2700/01 (2013.01); B29C 2045/14368 (2013.01); B29C 2793/0081 (2013.01); B29K 2715/00 (2013.01); B29L 2031/748 (2013.01); B60G 2204/143 (2013.01); B60G 2204/418 (2013.01); B60G 2206/8207 (2013.01); B60G 2300/60 (2013.01); B60P 3/025 (2013.01); G05B 2219/45071 (2013.01); Y02P 90/80 (2015.11); Y10S 901/01 (2013.01); Y10S 901/02 (2013.01); Y10S 901/41 (2013.01)] 20 Claims
OG exemplary drawing
 
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.