System for assembling aircraft

• US 8,620,470 B2
• Filed: 07/14/2011
• Issued: 12/31/2013
• Est. Priority Date: 10/26/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cobb, James M., Barnes, John G., Jones, Alan K., Sollenberger, Brian K., Stone, Patrick B.
• Primary Examiner(s): Shechtman, Sean P.
• Assistant Examiner(s): GARLAND, STEVEN R
• Application Number:
  US13/183,002
• Publication Number:
  US 20110276172A1
• Time in Patent Office: 901 Days
• Field of Search: 700/114, 700/60, 700/62, 700/117, 700/57, 294/070.9, 294/071
• US Class Current: 700/114
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor
• CPC Class Codes: Y10T 29/49778 with aligning, guiding, or instruction
• CPC Class Codes: Y10T 29/4978 Assisting assembly or disassembly
• CPC Class Codes: Y10T 29/53061 Responsive to work or work-related machine element

Abstract

A system for assembling aircraft is disclosed. An example system for moving components of an airplane into assembly alignment includes a jacking system including assembly jacks for supporting and moving components of the airplane into assembly alignment; a measurement system independent of the jacking system for determining locations of a plurality of features the components of the airplane while the components are supported on the assembly jacks; and a computer system for determining the relative positions of the components in a coordinate system of the airplane and for controlling the movement of the assembly jacks to bring the components into assembly alignment.

Claims

1. A system for moving components of an airplane into assembly alignment, comprising:

a jacking system including assembly jacks for supporting and moving components of the airplane into assembly alignment;

a measurement system independent of the jacking system for determining locations of a plurality of features of the components of the airplane while the components are supported on the assembly jacks, wherein the measurement system includes;

a plurality of transmitters arranged in a constellation on a first structure defining an assembly space in which the airplane is being assembled;

a plurality of component targets disposed on the components in a plurality of predetermined locations known in a first coordinate system of the airplane; and

a plurality of reference targets arranged on a second structure defining the assembly space in a plurality of predetermined positions known in a second coordinate system of the assembly space; and

a computer system responsive to measurements from the measurement system for determining the relative positions of the components in the first coordinate system of the airplane and for controlling the movement of the assembly jacks to bring the components into assembly alignment.

2. The system of claim 1, further comprising:

an input interface to receive data from the measurement system representing initial locations of the components to be moved and desired final locations for the components to be moved; and

a processor operatively coupled to the input interface, the processor to;

automatically determine the initial locations of the components to be moved and the desired final locations from the initial locations;

automatically determine motion to align the components to be moved with the desired final locations;

automatically determine displacements of the assembly jacks to produce the determined motion; and

after the components have been moved, automatically determine locations of the moved components at final assembled positions.

3. The system of claim 1, wherein:

the system includes a photogrammetry system including a plurality of cameras;

the plurality of transmitters includes a plurality of flash-emitting devices, each of the flash-emitting devices being co-located with one of the cameras; and

the plurality of component targets and the plurality of reference targets includes a plurality of passive reflectors.

4. The system of claim 1, further comprising means for determining a cruise orientation of the airplane based on final assembly locations of the components determined by a locating system.

5. The system of claim 4, further comprising means for transferring the cruise orientation of the airplane into a physical reference located inside the airplane.

6. The system of claim 5, wherein the means for transferring the cruise orientation of the airplane further comprises:

a tool positioned outside the airplane and including a tool reference surface;

means for moving the tool reference surface to an orientation corresponding to the determined cruise orientation; and

means for recording the orientation of the tool reference surface.

7. The system of claim 6, wherein the means for moving the tool reference surface includes servo motors for moving the tool reference surface about pitch, roll and yaw axes.

8. The system of claim 6, wherein:

the means for recording the orientation of the tool reference surface includes an inertial reference unit; and

the tool reference surface is removably mounted on the tool to allow the tool reference surface and the inertial reference unit to be moved into the airplane.

9. The system of claim 4, wherein the means for determining the cruise orientation of the airplane, as-built includes:

a first computer processing component to automatically compute deviation from nominal orientation of the as-built airplane; and

a second computer processing component to apply the computed deviation from the nominal orientation of the as-built airplane to the nominal orientation of the as-built airplane.

10. The system of claim 1, wherein the jacking system includes a jack location computing system for computing assembly jack locations to align the components for assembly.

11. The system of claim 10, wherein the jack location computing system comprises:

an input interface to receive data from a locating system representing the initial locations of the components to be moved and a desired final location for the components to be moved; and

a computer processor operatively coupled to the input interface.

12. The system of claim 1, wherein the first structure comprises a ceiling of the assembly space, and the second structure comprises a floor of the assembly space.

13. A method of moving components of an airplane into assembly alignment, comprising:

determining initial positions of the components responsive to determining locations of a plurality of transmitters relative to a plurality of reference targets, the transmitters being arranged in a constellation on a first structure defining an assembly space in which the airplane is assembled, the reference targets being arranged on a second structure defining the assembly space in a plurality of predetermined positions known in a first coordinate system of the assembly space;

determining relative positions of the components in a second coordinate system of the airplane, the second coordinate system being different than the first coordinate system;

determining desired final locations for the components to be moved from the initial positions;

automatically determining motion to align the components to be moved with the desired final locations;

automatically determining displacements of assembly jacks to produce the determined motion;

performing the determined motion; and

after the components have been moved, automatically determining locations of the moved components at final assembled positions.

14. The method of claim 13, further comprising:

determining whether additional assembly jack displacements have been made after the determined motion; and

when an additional assembly jack displacement has been made;

adjusting a determined optimal location for the components to be moved; and

determining additional motion due to the additional assembly jack displacement.

15. The method of claim 13, wherein determining motion to align the components with the desired final locations includes determining a rigid motion which aligns a first reference frame determined by a plurality of points of the components to be moved with a second reference frame determined by a plurality of points of the desired final locations.

16. The method of claim 15, wherein determining the rigid motion includes:

moving a plurality of points in design space of the components to be moved to a plurality of corresponding points on the components to be moved; and

moving a plurality of points in design space of the desired final locations to a plurality of corresponding points on the desired final locations.

17. The method of claim 13, wherein determining at least one of the initial locations or the desired final locations of the components includes simultaneously determining azimuth and elevation of a plurality of component targets arranged in a plurality of predetermined positions on the components relative to the locations of the plurality of transmitters.

18. The method of claim 17, wherein determining relative positions of the components includes converting azimuth and elevation into coordinates in the second coordinate system of the airplane.

19. A system, comprising:

assembly jacks to support and move components of an airplane into assembly alignment;

a measurement system to locate features of the components of the airplane while the components are supported on the assembly jacks;

a computer system to determine relative positions of the components in a coordinate system of the airplane and to control movement of the assembly jacks to bring the components into assembly alignment; and

means for determining a cruise orientation of the airplane based on final assembly locations of the assembly jacks.