Method and apparatus for fabrication of lattice composite fuselage for commercial aircraft employing steered fiber lay up

Patent metadata

Field	Value
Publication number	US-10525639-B2
Application number	US-201816024477-A
Country	US
Kind code	B2
Filing date	Jun 29, 2018
Priority date	Mar 23, 2017
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

A system for fabrication of an aerospace structure incorporates a mold having a surface and at least one unidirectional SFL head adapted to lay down a plurality of collimated tows in a predetermined laminated pattern on the mold surface to produce a fuselage skin. At least one cross plied laminate SFL head is adapted to lay down a cross plied laminate base interface on the fuselage skin to establish a lattice rib shape for each of a plurality of lattice ribs. The cross plied laminate SFL head has a band placement head steerable to avoid structural design features and to maintain spacing from adjacent steered lattice ribs. The unidirectional SFL head is further adapted to lay down a plurality of collimated tows on the base interface of each of the plurality of lattice ribs for a first plurality of unidirectional tow plies in each lattice rib. The unidirectional SFL head has a fiber placement head steerable to match the lattice rib shape to avoid structural design features and to maintain spacing from adjacent steered lattice ribs.

First claim

What is claimed is:

1. A method for fabrication of an aerospace structure comprising: employing at least one unidirectional steered fiber layup head to lay down a plurality of first collimated tows in a predetermined laminated pattern on a mold surface to produce a fuselage skin; steering at least one cross plied laminate steered fiber layup head laterally diverging from a baseline geodesic lattice to lay down a cross plied laminate base interface on the fuselage skin to establish a lattice rib shape for each of a plurality of lattice ribs; steering a band placement head in the at least one cross plied laminate steered fiber layup head laterally diverging from the baseline geodesic lattice to avoid structural design features and to maintain spacing from adjacent steered lattice ribs; employing the at least one unidirectional steered fiber layup head to lay down a plurality of second collimated tows on the base interface of each of the plurality of lattice ribs for a plurality of unidirectional tow plies in each lattice rib; steering a fiber placement head in the at least one unidirectional steered fiber layup head to match the lattice rib shape laterally diverging from the baseline geodesic lattice to avoid the structural design features and to maintain spacing from the adjacent steered lattice ribs;
employing the at least one cross plied laminate steered fiber layup head to lay a cap over the plurality of unidirectional tow plies in each of the plurality of lattice ribs;
and steering the band placement head in the at least one cross plied laminate steered fiber layup head laterally diverging from the baseline geodesic lattice to track the lattice rib shape and position the cap over the plurality of unidirectional tow plies.

2. The method as defined in claim 1 , wherein steering of the fiber placement head additionally includes rotating the fiber placement head about a nominal axis perpendicular to the mold surface to maintain fiber alignment with a direction of travel.

3. The method as defined in claim 1 , wherein steering of the band placement head additionally includes rotating the band placement head about a nominal axis perpendicular to the mold surface to maintain band alignment with the direction of travel.

4. The method as defined in claim 1 , wherein the step of employing at least one unidirectional steered fiber layup head to lay down the plurality of first collimated tows in the predetermined laminated pattern on the mold surface to produce the fuselage skin further includes employing a tow cutter and clamp mechanism in the fiber placement head to terminate and restart the plurality of first collimated tows at the structural design features.

5. The method as defined in claim 1 , wherein the step of employing the at least one cross plied laminate steered fiber layup head to lay the cap over the plurality of unidirectional tow plies further comprises draping of the cap over the plurality of tow plies.

6. The method as defined in claim 5 , further comprising extending the draped cap over a surface of the skin adjacent the lattice rib.

7. The method as defined in claim 1 , further comprising rotating the fiber placement head about a nominal axis perpendicular to the surface of the mold to maintain fiber alignment with a direction of travel.

8. The method as defined in claim 1 , wherein the at least one unidirectional steered fiber layup head comprises a plurality of spindles each carrying tows of structural fiber, and further comprising dispensing said tows of structural fiber from the spindles with controlled tension to the fiber placement head as individual tows.

9. The method as defined in claim 8 , further comprising combining the individual tows in a band collimator in the fiber placement head into the plurality of first and second collimated tows.

10. The method as defined in claim 9 , further comprising receiving the plurality of first and second collimated tows from the band collimator in tow restart rollers.

11. The method as defined in claim 10 , further comprising pressing the plurality of first collimated tows from the tow restart rollers initially onto the surface of the mold and subsequently on prior laid collimated tows or the base interface with a compaction roller to produce multiple layers.

12. The method as defined in claim 11 , further comprising adhering the plurality of first and second collimated tows with a controlled heat source proximate the compaction roller.

13. The method as defined in claim 12 , further comprising terminating each fiber band along a direction of travel of the fiber placement head with a band cutter and clamp mechanism.

14. The method as defined in claim 1 , wherein the at least one cross plied laminate steered fiber layup head comprises a plurality of cassettes each cassette having rolled cross plied fiber laminate bands of determined widths for the cap and base interface and further comprising feeding each cross plied laminate band under controlled tension to the band placement head.

15. The method as defined in claim 14 , further comprising receiving each cross plied laminate band in band restart rollers.

16. The method as defined in claim 15 , further comprising pressing each cross plied laminate band onto the skin as the laminate base interface using a compaction roller.

17. The method as defined in claim 16 , further comprising adhering each cross plied laminate band using a controlled heat source proximate the compaction roller.

18. The method as defined in claim 17 , further comprising terminating a run of each cross plied laminate band along a direction of travel of the band placement head with a band cutter and clamp mechanism.

19. The method as defined in claim 1 , further comprising: employing the at least one unidirectional steered fiber layup head to lay down a third plurality of collimated tows on the cap of each of the plurality of lattice ribs for the plurality of unidirectional tow plies in each lattice rib; and steering the fiber placement head in the at least one unidirectional steered fiber layup head to match the lattice rib shape laterally diverging from the baseline geodesic lattice to avoid the structural design features and to maintain spacing from the adjacent steered lattice ribs.

20. The method as defined in claim 19 , further comprising: employing the at least one cross plied laminate steered fiber layup head to lay a second cap over the third plurality of unidirectional tow plies in each of the plurality of lattice ribs; and steering the band placement head in the at least one cross plied laminate steered fiber layup head laterally diverging from the baseline geodesic lattice to track the lattice rib shape and position the second cap over the plurality of unidirectional tow plies.

Assignees

• Boeing Co

Inventors

• Sokolov Boris B
• Rassaian Mostafa
• Piehl Marc J

Classifications

• B64C1/08

  Geodetic or other open-frame structures · CPC title

• B29C70/38 Primary

  Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns {(application heads for tyres B29D30/28)} · CPC title

• B29D99/0014

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B64F5/10 Primary

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

• B64C2001/0072

  from composite materials · CPC title