Robot-deployed assembly tool

• US 8,051,547 B2
• Filed: 12/29/2006
• Issued: 11/08/2011
• Est. Priority Date: 12/29/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Harman, Edward Bruce, Sarh, Branko, Toh, Chin H.
• Primary Examiner(s): Banks; Derris H
• Assistant Examiner(s): PARVEZ, AZM A
• Application Number:
  US11/618,431
• Publication Number:
  US 20080155807A1
• Time in Patent Office: 1,775 Days
• Field of Search: 294/64, 294/65, 294/68, 297/09, 297/12, 297/14, 297/20, 297/21, 297/98, 298/972, 294/070.9, 294/071, 901/40
• US Class Current: 29/525.01
• CPC Class Codes: B21J 15/14 specially adapted for riveting specific articles, e.g. brake lining machines
• CPC Class Codes: B21J 15/142 Aerospace structures
• CPC Class Codes: B23P 19/04 for assembling or disassembling parts
• CPC Class Codes: B23P 2700/01 Aircraft parts
• CPC Class Codes: Y10T 29/49616 Structural member making
• CPC Class Codes: Y10T 29/49895 Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
• CPC Class Codes: Y10T 29/49947 by applying separate fastener
• CPC Class Codes: Y10T 29/4995 Nonthreaded
• CPC Class Codes: Y10T 29/53 Means to assemble or disassemble
• CPC Class Codes: Y10T 29/53039 with control means energized in response to activator stimulated by condition sensor
• CPC Class Codes: Y10T 29/53087 with signal, scale, illuminator, or optical viewer
• CPC Class Codes: Y10T 29/5343 Means to drive self-piercing work part

Abstract

An assembly system and method for assembling an aircraft wing box or other structure that may define an interior area accessible through at least one access opening are provided. The method includes inserting a robot having an assembly tool mounted thereto into the interior area through the at least one access opening. The assembly tool may be positioned at a fastener location, and may be clamped to the structure. A hole may be made through the structure, and a fastener may be installed in the hole.

Claims

1. An assembly system for assembling a wing box of an aircraft, the wing box defining an enclosed area accessible through at least one access opening, the assembly system comprising:

a robot located outside the wing box that extends and guides a robot arm into the enclosed area of the wing box through the at least one access opening; and

an assembly tool mounted to the robot arm, the assembly tool comprising;

a positioning mechanism for positioning the assembly tool in the enclosed area;

a clamp for clamping the assembly tool to an interior surface of the enclosed area of the wing box; and

an electromagnet located outside the wing box positioned to activate the clamp to clamp the assembly tool to the interior surface.

2. The assembly system according to claim 1, further comprising:

a robot arm link operably coupled to the robot arm; and

a connector link operably coupled to the robot arm link.

3. The assembly system according to claim 1, further comprising:

a vision module in the positioning mechanism for guiding the assembly tool to a fastener location in the enclosed area.

4. The assembly system according to claim 3, further comprising a camera in the vision module that guides the assembly tool to a fastener location in the enclosed area by a laser beam passing through a notch in the clamp.

5. The assembly system according to claim 4, further comprising:

at least one of a light source and a laser sensor in the vision module.

6. The assembly system according to claim 1, further comprising:

a fastener installing mechanism for installing a fastener in the hole;

a securing utility tool in the fastener installing mechanism for securing a fastener securing element to the fastener.

7. The assembly system according to claim 6, further comprising:

a dispensing utility tool in the fastener securing mechanism for dispensing the fastener securing element to the fastener.

8. The assembly system according to claim 7, further comprising:

actuators in the assembly tool for moving the dispensing utility tool and the securing utility tool into dispensing and securing positions, respectively.

9. The assembly system according to claim 1, further comprising:

a clamping foot operably coupled to the clamp for being magnetically clamped to an interior surface of the enclosed area.

10. The assembly system according to claim 9, further comprising:

a gap between a wing spar cap and a skin panel or between a wing bulkhead flange and a skin panel that is eliminated by clamping the clamping foot to the interior surface of the enclosed area when the electromagnet located outside of the wing box activates the clamp thereby enabling substantially burr-less drilling of the hole through the wing spar cap and the skin panel or the wing bulkhead flange and the skin panel from outside of the wing box.

11. The assembly system according to claim 9, further comprising:

a taper of the clamping foot for clamping the assembly tool to the interior surface of the enclosed area at corner fastener locations.