Composite assembly for unhardened fuselage components

Patent metadata

Field	Value
Publication number	US-12350776-B2
Application number	US-202318171585-A
Country	US
Kind code	B2
Filing date	Feb 20, 2023
Priority date	Nov 18, 2020
Publication date	Jul 8, 2025
Grant date	Jul 8, 2025

Abstract

Systems are provided for fabricating a preform for a fuselage section of an aircraft. The system includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

First claim

What is claimed is:

1. A system for fabricating a preform for a fuselage section of an aircraft, the system comprising:
a series of arcuate mandrel sections that are advanced in a process direction through an assembly line;
at least one mandrel assembly station operable to unite the series of arcuate mandrel sections into a combined mandrel;
at least one layup station operable to layup fiber reinforced material onto the arcuate mandrel sections and splice the fiber reinforced material laid-up onto the arcuate mandrel sections; and
a mezzanine comprising a first port therethrough, the mezzanine operable to lower at least one of a sheet of IWWF, a sheet of surface, and a caul plate through the port and onto the fiber reinforced material on the combined mandrel.

2. The system of claim 1 , further comprising:
at least one stringer placement station operable to place stringer preforms onto the arcuate mandrel sections.

3. The system of claim 2 , wherein the at least one stringer placement station is operable to place the stringer preforms onto the arcuate mandrel sections during pauses between pulses of the arcuate mandrel sections along the assembly line.

4. The system of claim 2 , wherein the at least one stringer placement station is operable to place the stringer preforms onto the arcuate mandrel sections as the arcuate mandrel sections move continuously along the assembly line.

5. The system of claim 2 , further comprising:
at least one lamination station configured to layup and trim flat charges of fiber reinforced material; and
at least one forming station configured to shape the flat charges into the stringer preforms.

6. The system of claim 5 , further comprising a mandrel for the forming of the stringer preforms.

7. The system of claim 6 , further comprising a track, the mandrel for the stringer preforms operable to cycle through the at least one lamination station and the at least one forming station multiple times before exiting the track.

8. The system of claim 1 , the mezzanine further comprising a second port therethrough, the mezzanine further operable to lower the caul plate through the second port and onto the at least one of the sheet of IWWF and the sheet of surface.

9. The system of claim 1 , wherein the at least one mandrel assembly station comprises a frame, the at least one mandrel assembly station is operable to unite the series of arcuate mandrel sections by placing the arcuate mandrel sections onto the frame such that the arcuate mandrel sections are adjacent to each other.

10. The system of claim 1 , wherein the at least one mandrel assembly station is operable to unite the series of arcuate mandrel sections by fastening the arcuate mandrel sections to each other while the arcuate mandrel sections are chordwise adjacent.

11. The system of claim 1 , wherein the at least one mandrel assembly station is operable to unite the series of arcuate mandrel sections to form a half-barrel section of fuselage.

12. The system of claim 1 , wherein the at least one mandrel assembly station is operable to unite the series of arcuate mandrel sections to form a full-barrel section of fuselage.

13. The system of claim 1 , wherein the at least one layup station comprises at least one end effector, the at least one end effector operable to dispense tows of fiber reinforced material onto the arcuate mandrel sections.

14. The system of claim 1 , further comprising a controller, the controller operable to enforce uniform work times across the at least one layup station, the at least one mandrel assembly station, and such that the laying up and uniting is coordinated and synchronized according to a common schedule.

15. The system of claim 14 , further comprising:
at least one stringer placement station operable to place stringer preforms onto the arcuate mandrel sections;
at least one lamination station configured to layup and trim flat charges of fiber reinforced material; and
at least one forming station configured to shape the flat charges into stringer preforms, the controller further operable to coordinate and synchronize operations of the at least one lamination station, the at least one forming station, and the at least one stringer placement station according to the common schedule.

16. The system according to claim 1 , wherein at least one stringer placement station is operable to place batches of stringer preforms onto the arcuate mandrel sections.

17. An apparatus for fabricating a preform for a fuselage section of an aircraft, the apparatus comprising:
a series of arcuate mandrel sections that are advanced in a process direction through an assembly line, the series of arcuate mandrel sections joined together to form a combined mandrel, each arcuate mandrel section having troughs for receiving stringer preforms;
the stringer preforms placed into the troughs of each of the arcuate mandrel sections;
fiber reinforced material laid up over each of the arcuate mandrel sections via layup stations and spliced together to form the preform; and
a mezzanine comprising a first port therethrough, the mezzanine operable to lower at least one of a sheet of IWWF, a sheet of surface, and a caul plate through the port and onto the fiber reinforced material on the combined mandrel.

18. The apparatus of claim 17 , further comprising:
at least one stringer placement station operable to place the stringer preforms onto the arcuate mandrel sections.

19. The apparatus of claim 18 , wherein the at least one stringer placement station is operable to place the stringer preforms onto the arcuate mandrel sections during pauses between pulses of the arcuate mandrel sections in the process direction through the assembly line.

20. The apparatus of claim 18 , wherein the at least one stringer placement station is operable to place the stringer preforms onto the arcuate mandrel sections as the arcuate mandrel sections move continuously in the process direction through the assembly line.

21. The apparatus of claim 17 , wherein at least one layup station of the layup stations comprises at least one end effector, the at least one end effector operable to dispense tows of the fiber reinforced material onto the arcuate mandrel sections.

22. The apparatus of claim 17 , further comprising a controller, the controller operable to enforce uniform work times across the layup stations according to a common schedule.

23. The apparatus of claim 22 , further comprising:
at least one stringer placement station operable to place the stringer preforms onto the arcuate mandrel sections;
at least one lamination station configured to layup and trim flat charges of the fiber reinforced material; and
at least one forming station configured to shape the flat charges into the stringer preforms, the controller further operable to coordinate and synchronize operations of the at least one lamination station, the at least one forming station, and the at least one stringer placement station according to the common schedule.

24. A system for fabricating a preform for a fuselage section of an aircraft, the system comprising:
a series of arcuate mandrel sections that are advanced in a process direction through an assembly line;
at least one mandrel assembly station operable to unite the series of arcuate mandrel sections into a combined mandrel;
at least one layup station operable to layup fiber reinforced material onto the arcuate mandrel sections and splice the fiber r

Assignees

• Boeing Co

Inventors

• Smith Daniel R
• Jones Darrell D
• Pritchard Paul T
• Medenciy Jason A
• Kirchmeier Stephen Keith
• Willden Kurtis Shuldberg
• Whiting Robert William
• Beerman Michael
• Suriyaarachchi Raviendra Sidath
• Justice Jeremy Evan
• Wilcoxson Paul Chace

Classifications

• B64C1/068

  Fuselage sections · CPC title

• B29C70/682

  Preformed parts characterised by their structure, e.g. form · CPC title

• B29C70/30

  Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core · CPC title

• B29C70/342

  using isostatic pressure · CPC title

• B23P2700/12

  Laminated parts · CPC title