Metrology-Based System for Operating a Flexible Manufacturing System

Patent metadata

Field	Value
Publication number	US-2016008981-A1
Application number	US-201414559855-A
Country	US
Kind code	A1
Filing date	Dec 3, 2014
Priority date	Jul 9, 2014
Publication date	Jan 14, 2016
Grant date	—

Abstract

A method and apparatus for positioning an end effector relative to a fuselage assembly. A configuration of the fuselage assembly may be determined. The end effector may be positioned relative to the fuselage assembly based on the configuration determined. A set of actual reference locations may be identified for a set of reference points on the fuselage assembly. The end effector may be positioned at an operation location based on the set of actual reference locations identified.

First claim

What is claimed is:

1 . A method for positioning an end effector relative to a fuselage assembly, the method comprising:
determining a configuration of the fuselage assembly; positioning the end effector relative to the fuselage assembly based on the configuration determined; identifying a set of actual reference locations for a set of reference points on the fuselage assembly; and positioning the end effector at an operation location based on the set of actual reference locations identified.

2 . The method of claim 1 , wherein positioning the end effector relative to the fuselage assembly comprises:
meso-positioning the end effector relative to the fuselage assembly.

3 . The method of claim 1 further comprising:
determining a current position of the end effector relative to the configuration of the fuselage assembly.

4 . The method of claim 1 , wherein determining the configuration comprises:
identifying fuselage target locations for fuselage laser targets associated with the fuselage assembly.

5 . The method of claim 4 , wherein identifying the fuselage target locations comprises:
receiving laser measurement data from a set of laser tracking devices; and identifying the fuselage target locations for the fuselage laser targets using the laser measurement data.

6 . The method of claim 3 further comprising:
identifying a set of expected reference locations for the set of reference points based on the configuration of the fuselage assembly.

7 . The method of claim 6 , wherein positioning the end effector relative to the fuselage assembly comprises:
positioning the end effector relative to one of the set of expected reference locations.

8 . The method of claim 1 , wherein identifying the set of actual reference locations for the set of reference points comprises:
generating imaging data of a reference point of the set of reference points; and computing an actual reference location for the reference point based on the imaging data.

9 . The method of claim 8 , wherein generating the imaging data comprises:
generating the imaging data using an imaging system while the end effector is positioned relative to an expected reference location for the reference point.

10 . The method of claim 1 further comprising:
computing the operation location based on the set of actual reference locations identified.

11 . The method of claim 1 , wherein positioning the end effector at the operation location comprises:
micro-positioning the end effector at the operation location.

12 . The method of claim 1 , wherein positioning the end effector relative to the fuselage assembly comprises:
meso-positioning the end effector relative to an expected reference location for a reference point.

13 . The method of claim 1 further comprising:
macro-positioning the end effector relative to the fuselage assembly.

14 . The method of claim 13 , wherein macro-positioning the end effector comprises:
macro-positioning a base of a mobile platform with which the end effector is associated relative to the fuselage assembly.

15 . The method of claim 1 further comprising:
driving a base of a mobile platform with which the end effector is associated autonomously into a position relative to one of an interior and an exterior of the fuselage assembly.

16 . The method of claim 1 further comprising:
driving a base of a mobile platform with which the end effector is associated using a platform movement system associated with the base based on radar data received from a set of radar sensors associated with at least one of the platform movement system or the base.

17 . The method of claim 1 further comprising:
driving a base of a mobile platform with which the end effector is associated inside the fuselage assembly.

18 . The method of claim 17 , wherein driving the base comprises:
driving the base of the mobile platform across a floor within an interior of the fuselage assembly.

19 . The method of claim 17 , wherein driving the base comprises:
driving the base of the mobile platform from a home position on a tower onto a floor inside the fuselage assembly.

20 . The method of claim 1 , wherein positioning the end effector relative to the fuselage assembly comprises:
moving the end effector from a current position to a position relative to an expected reference location for a reference point of the set of reference points.

21 . The method of claim 1 , wherein positioning the end effector relative to the fuselage assembly comprises:
moving the end effector from a default position with respect to a base of a mobile platform with which the end effector is associated to a position relative to an expected reference location for a reference point of the set of reference points.

22 . The method of claim 1 further comprising:
detecting at least three of fuselage laser targets associated with the fuselage assembly; and
identifying fuselage target locations for the fuselage laser targets based on detecting the at least three of the fuselage laser targets.

23 . The method of claim 22 , wherein determining the configuration comprises:
determining the configuration of the fuselage assembly based on the fuselage target locations identified.

24 . The method of claim 1 , wherein positioning the end effector relative to the operation location comprises:
micro-positioning a tool center point located at an end of the end effector relative to the operation location.

25 . The method of claim 1 , wherein positioning the end effector relative to the fuselage assembly comprises:
meso-positioning the end effector relative to each of a set of expected reference locations for the set of reference points on the fuselage assembly.

26 . The method of claim 25 , wherein identifying the set of actual reference locations comprises:
generating imaging data for a reference point of the set of reference points when the end effector is positioned relative to the reference point; and computing the set of actual reference locations for the set of reference points using the imaging data.

27 . The method of claim 25 , wherein positioning the end effector relative to the operation location comprises:
computing the operation location based on the set of actual reference locations for the set of reference points; and positioning the end effector relative to the operation location.

28 . The method of claim 1 further comprising:
performing an assembly operation at the operation location using a number of tools associated with the end effector.

29 . The method of claim 1 further comprising:
performing a fastening process at the operation location on the fuselage assembly using a number of tools associated with the end effector.

30 . A method for positioning an end effector, the method comprising:
macro-positioning the end effector relative to a fuselage assembly; meso-positioning the end effector relative to the fuselage assembly; computing a set of actual reference locations for a set of reference points on the fuselage assembly; and micro-positioning the end effector relative to each of a set of operation locations on the fuselage assembly based on the set of actual reference locations computed.

31 . The method of claim 30 , wherein meso-p

Assignees

• Boeing Co

Inventors

• Oberoi Harinder S
• Dorsey-Palmateer John Willard
• Hu Yuanxin Charles
• Sarh Branko
• Barrick Kevin Marion
• Findlay Melissa Ann
• Arriaga Jorge Alberto
• Gudzinski Gregory

Classifications

• G05B19/41865

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

• B21J15/02 Primary

  Riveting procedures · CPC title

• Y10S901/41

  Tool · CPC title

• G05B19/418 Primary

  Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM] · CPC title

• B25J11/007

  Riveting · CPC title