Frame fabrication line

Patent metadata

Field	Value
Publication number	US-11845566-B2
Application number	US-202117454301-A
Country	US
Kind code	B2
Filing date	Nov 10, 2021
Priority date	Nov 18, 2020
Publication date	Dec 19, 2023
Grant date	Dec 19, 2023

Abstract

Systems and methods are provided for fabrication of frames for aircraft.

First claim

What is claimed is:

1. A method for fabricating an aircraft, the method comprising:
receiving a frame comprising one of a metal frame or a hardened composite frame;
advancing the frame through one station of an array of stations arranged in an arc to a starting location;
performing work on the frame via the one station at the starting location;
attaching a second station of the array of stations to the frame;
performing work on the frame via the second station as the frame advances along the arc; and
after performing work on the frame via the second station, returning the second station to the starting location.

2. The method of claim 1 , wherein:
the arc corresponds to a shape of the frame.

3. The method of claim 1 , wherein:
the one station of the array of stations comprises one of a Non-Destructive Inspection (NDI) station, a drilling station, a trimming station, a machining station, or a cut-out station; and
wherein performing the work on the frame via the one station comprises one of inspecting the frame, drilling the frame, trimming the frame, machining the frame, or performing cut-out operations on the frame.

4. The method of claim 1 , further comprising:
advancing the frame through multiple stations of the array of stations; and
performing work on the frame via the multiple stations of the array of stations upon different sections of the frame at a same time.

5. The method of claim 1 , wherein:
advancing the frame through the one station of the array of stations comprises pulsing the frame along the arc by a distance less than a length of the frame.

6. The method of claim 1 , wherein:
advancing the frame through the one station of the array of stations comprises pulsing the frame along the arc by a distance equal to a length of the frame.

7. The method of claim 1 , wherein:
advancing the frame comprises moving the frame along the arc continuously.

8. The method of claim 7 , wherein:
performing work on the frame via the one station occurs during pauses between pulses of the frame.

9. The method of claim 7 , wherein:
performing work on the frame via the one station is performed while the frame advances during a pulse.

10. The method of claim 1 , wherein:
advancing the frame comprises causing the frame to undergo circular motion.

11. The method of claim 1 , further comprising:
indexing the stations of the array to indexing features at a manufacturing excess of the frame.

12. The method of claim 1 , wherein:
advancing the frame comprises physically interlocking a drive unit to a manufacturing excess of the frame.

13. The method of claim 1 , wherein:
the frame is held by a tool that includes indexing features and is advanced through the array of stations and further comprising:
interlocking a drive unit with the tool while the tool carries the frame.

14. The method of claim 1 , wherein:
the array of stations includes a Non-Destructive Inspection (NDI) station that inspects lengthwise sections of the frame.

15. The method of claim 14 , wherein:
the array of stations further includes an additional Non-Destructive Inspection (NDI) station for inspecting radii.

16. The method of claim 14 , wherein:
the array of stations includes a drilling station, disposed downstream of the Non-Destructive Inspection (NDI) station, and configured to drill Determinant Assembly (DA) holes into lengthwise sections of the frame.

17. The method of claim 16 , wherein:
the array of stations includes a machining station, disposed downstream of the drilling station, and configured to trim lengthwise sections of the frame to form datum planes at the frame.

18. The method of claim 17 , wherein:
the array of stations includes a cut-out station, disposed downstream of the machining station, that is configured to cut out mouse holes from lengthwise sections of the frame.

19. The method of claim 14 , wherein:
the Non-Destructive Inspection (NDI) station is configured to inspect a web and flanges of the frame, and the array of stations further comprises an additional Non-Destructive Inspection (NDI) station configured to inspect a radius of the frame.

20. The method of claim 1 , wherein:
advancing the frame through the one station of the array of stations comprises advancing the frame along the arc clockwise.

21. The method of claim 1 , wherein:
advancing the frame through the one station of the array of stations comprises advancing the frame along the arc counterclockwise.

22. The method of claim 10 , wherein:
the circular motion follows the arc, the arc having a radius that corresponds with a radius of the frame.

23. The method of claim 1 , wherein:
the frame is held by a tool that includes indexing features and is advanced through the array of stations.

24. The method of claim 3 , wherein:
the Non-Destructive Inspection (NDI) station is disposed upstream of the machining station.

25. The method of claim 3 , wherein:
the Non-Destructive Inspection (NDI) station is disposed downstream of the machining station.

26. A method for fabricating an aircraft, the method comprising:
receiving a frame comprising one of a metal frame or a hardened composite frame;
advancing the frame through multiple stations of an array of stations arranged in an arc by pulsing the frame along the arc, the arc corresponding to a shape of the frame, the array of stations comprises at least one of a Non-Destructive Inspection (NDI) station, a drilling station, a trimming station, a machining station, or a cut-out station; and
performing work on the frame via the multiple stations of the array of stations upon different sections of the frame at a same time during pauses between pulses of the frame, wherein performing the work on the frame via the multiple stations upon the frame comprises at least one of inspecting the frame, drilling the frame, trimming the frame, machining the frame, or performing cut-out operations on the frame.

27. The method of claim 26 , wherein:
advancing the frame through multiple stations of the array of stations comprises pulsing the frame along the arc by a distance less than a length of the frame.

28. The method of claim 26 , wherein:
advancing the frame comprises causing the frame to undergo circular motion, the circular motion follows the arc, the arc having a radius that corresponds with a radius of the frame.

29. The method of claim 26 , further comprising:
indexing the multiple stations of the array of stations to indexing features at a manufacturing excess of the frame.

30. The method of claim 26 , wherein:
advancing the frame comprises physically interlocking a drive unit to a manufacturing excess of the frame.

Assignees

• Boeing Co

Inventors

• Smith Daniel R
• Jones Darrell D

Classifications

• B64C1/061

  Frames · CPC title

• B64F5/10 Primary

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

• B23P23/06

  Metal-working plant comprising a number of associated machines or apparatus · CPC title

• B23P21/004 Primary

  the units passing two or more work-stations whilst being composed · CPC title

• B23P2700/01

  Aircraft parts · CPC title