Gantry system and method for processing an aircraft

Patent metadata

Field	Value
Publication number	US-10501208-B2
Application number	US-201715639470-A
Country	US
Kind code	B2
Filing date	Jun 30, 2017
Priority date	Jun 30, 2017
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

A gantry system for processing an aircraft includes a gantry receiving a fuselage of the aircraft having a gantry frame with an arched member. The gantry system includes first and second locating arms extending between inner and outer ends movably coupled to the gantry frame. The gantry system includes a bracket assembly having a first locating arm bracket pivotably coupled to the first locating arm, a second locating arm bracket pivotably coupled to the second locating arm, and a head assembly bracket with a head assembly coupled thereto having an end effector for processing the fuselage. The head assembly is variably positionable by the first and second locating arms moving along the gantry frame for positioning the end effector relative to the fuselage.

First claim

What is claimed is:

1. A gantry system for processing an aircraft comprising:
a gantry having an interior space configured to receive a fuselage of the aircraft, the gantry having a gantry frame having an arched member configured to pass from a first side of the interior space to a second side of the interior space along an arcuate path;
a first locating arm extending between an inner end and an outer end, the outer end being movably coupled to the gantry frame;
a second locating arm extending between an inner end and an outer end, the outer end being movably coupled to the gantry frame;
a bracket assembly having a first locating arm bracket pivotably coupled to the inner end of the first locating arm, a second locating arm bracket pivotably coupled to the inner end of the second locating arm, and a head assembly bracket; and
a head assembly coupled to the head assembly bracket, the head assembly having an end effector for processing the fuselage;
wherein the head assembly is variably positionable in the interior space by the first and second locating arms moving along the gantry frame for positioning the end effector relative to the fuselage.

2. The gantry system of claim 1 , wherein the first and second locating arms are movable along the gantry frame to change an angular position of the head assembly in the interior space.

3. The gantry system of claim 1 , wherein the first locating arm includes a telescoping member operable to change a length of the first locating arm between the inner end and the outer end to change a radial position of the head assembly in the interior space, the second locating arm including a telescoping member operable to change a length of the second locating arm between the inner end and the outer end to change a radial position of the head assembly in the interior space.

4. The gantry system of claim 1 , wherein the gantry frame includes a track, and wherein the outer ends of the first and second locating arms include slides operably coupled to the track to move along the track.

5. The gantry system of claim 1 , wherein the first and second locating arms include locking elements at the outer ends to fix the locations of the first and second locating arms along the gantry frame.

6. The gantry system of claim 1 , wherein the first and second locating arms are independently movable along the gantry frame to change a relative spacing of the outer ends of the first and second locating arms along the arcuate path.

7. The gantry system of claim 1 , further comprising a pivot driver operably coupled to at least one of the first locating arm and the first locating arm bracket to change a pivot angle between the bracket assembly and the first locating arm to orient the head assembly in the interior space.

8. The gantry system of claim 1 , wherein the head assembly includes a rail including a track, and wherein the end effector is movable along the track relative to the head assembly bracket.

9. The gantry system of claim 8 , wherein the outer ends of the first and second locating arms are configured to be fixed along the gantry frame when the end effector moves along the track to process the aircraft.

10. The gantry system of claim 1 , wherein the arcuate path of the arched member is configured to generally follow a shape of the fuselage of the aircraft in a spaced apart relationship.

11. A gantry system for processing an aircraft comprising:
a gantry having an interior space configured to receive a fuselage of the aircraft, the gantry having a forward gantry frame having a forward arched member configured to pass from a first side of the interior space to a second side of the interior space along an arcuate path, the gantry having an aft gantry frame having an aft arched member configured to pass from a first side of the interior space to a second side of the interior space along an arcuate path;
a forward carrier assembly coupled to the forward gantry frame, the forward carrier assembly comprising a first locating arm extending between an inner end and an outer end being movably coupled to the forward gantry frame, a second locating arm extending between an inner end and an outer end being movably coupled to the forward gantry frame, and a forward bracket assembly pivotably coupled to the inner ends of the first and second locating arms, the forward bracket assembly having a forward head assembly bracket;
an aft carrier assembly coupled to the aft gantry frame, the aft carrier assembly comprising a first locating arm extending between an inner end and an outer end being movably coupled to the aft gantry frame, a second locating arm extending between an inner end and an outer end being movably coupled to the aft gantry frame, and an aft bracket assembly pivotably coupled to the inner ends of the first and second locating arms, the aft bracket assembly having an aft head assembly bracket; and
a head assembly coupled to the forward head assembly bracket and the aft head assembly bracket, the head assembly having a rail including a track, the head assembly having an end effector movable along the track between the forward and aft head assembly brackets for processing the fuselage;
wherein the head assembly is variably positionable in the interior space by the forward carrier assembly and the aft carrier assembly for positioning the end effector relative to the fuselage.

12. The gantry system of claim 11 , wherein the first and second locating arms of the forward carrier assembly are movable along the forward gantry frame to change an angular position of the head assembly in the interior space.

13. The gantry system of claim 11 , wherein the first and second locating arms of the forward carrier assembly include telescoping members operable to change lengths of the corresponding first and second locating arms.

14. The gantry system of claim 11 , wherein the forward gantry frame is movable relative to the aft gantry frame to change a gantry frame spacing therebetween to change a spacing between the forward and aft bracket assemblies corresponding to a change in angle of the rail in the interior space relative to the fuselage.

15. The gantry system of claim 11 , wherein the forward carrier assembly is movable along the forward gantry frame independent of movement of the aft carrier assembly along the aft gantry frame to change an angle of the rail in the interior space relative to the fuselage.

16. The gantry system of claim 11 , wherein the forward carrier assembly is configured to be fixed along the forward gantry frame and the aft carrier assembly is configured to be fixed along the aft gantry frame to fix the position of the rail of the head assembly relative to the fuselage, and wherein the end effector is configured to move in a linear path along the track to process the fuselage while the forward and aft carrier assemblies remain fixed.

17. The gantry system of claim 11 , further comprising a forward pivot driver operably coupled to at least one of the forward bracket assembly and the first locating arm of the forward carrier assembly to change a pivot angle between the forward bracket assembly and the first locating arm of the forward carrier assembly to orient the head assembly in the interior space and further comprising an aft pivot driver operably coupled to at least one of the aft bracket assembly and the first locating arm of the aft carrier assembly to change a pivot angle between the aft bracket assembly and the first locating arm of the aft carrier assembly to orient the head assembly in the interior space.

18. A method of processing

Assignees

• Boeing Co

Inventors

• Whitlaw James Grady
• Miller John Eric
• Diaz Jairo A
• Mellin Matthew H

Classifications

• B64F5/10 Primary

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

• B64F5/30

  Cleaning aircraft · CPC title

• B25J11/0075

  Manipulators for painting or coating · CPC title

• B25J9/0084

  comprising a plurality of manipulators · CPC title

• B25J9/0036

  with kinematics chains of the type prismatic-rotary-rotary · CPC title