Composite laminate forming apparatus and method therefor

Patent metadata

Field	Value
Publication number	US-10926490-B2
Application number	US-201815948106-A
Country	US
Kind code	B2
Filing date	Apr 9, 2018
Priority date	Apr 9, 2018
Publication date	Feb 23, 2021
Grant date	Feb 23, 2021

Abstract

An apparatus is provided for forming a composite laminate. The apparatus comprises a mandrel having a surface on which the composite laminate can be formed. The apparatus further comprises an application surface and a conveyor configured to move a composite material piece that has been cut to a desired shape to the application surface. The apparatus also comprises an actuating mechanism for, when actuated, lifting the application surface upward towards the mandrel to apply the composite material piece to the surface of the mandrel to form at least a portion of the composite laminate on the surface of the mandrel.

First claim

What is claimed is:

1. A method for forming a composite laminate, the method comprising:
conveying a composite material piece that has been cut to a desired shape to a first portion of an application surface; and
after the composite material piece has been conveyed to the first portion of the application surface, moving a second portion of the application surface towards a mandrel to form at least a portion of the composite laminate on a surface of the mandrel, wherein the first portion of the application surface is stationary during the step of moving the second portion of the application surface.

2. The method of claim 1 wherein the mandrel is in an inverted position and wherein moving the second portion of the application surface towards the mandrel to form the at least a portion of the composite laminate on the surface of the mandrel includes:
lifting the second portion of the application surface upward towards the mandrel to form the at least a portion of the composite laminate on a bottom surface of the mandrel.

3. The method of claim 2 wherein lifting the second portion of the application surface upward towards the mandrel to form the at least a portion of the composite laminate on the bottom surface of the mandrel includes:
actuating certain pins of a matrix of actuatable pins to lift the composite material piece upward towards the mandrel.

4. The method of claim 1 wherein moving the second portion of the application surface towards the mandrel to form the at least a portion of the composite laminate on the surface of the mandrel includes:
automatically moving the second portion of the application surface towards the mandrel.

5. The method of claim 1 further comprising:
automatically removing backing material from the composite material piece that has been cut to the desired shape.

6. The method of claim 1 further comprising:
removing backing material from the composite material piece before the composite material piece is conveyed to the first portion of the application surface.

7. The method according to claim 1 wherein the method is controlled by a computer having a memory executing one or more program of instructions which are tangibly embodied in a storage medium readable by the computer.

8. A method for forming a composite laminate comprising:
providing a sheet of composite material having a backing material thereon to a conveyor;
automatically cutting the sheet of composite material to form a cut composite ply with the backing material thereon to a desired shape while the sheet of composite material is on the conveyor;
removing the backing material from the cut composite ply while the cut composite ply is on the conveyor;
moving the cut composite ply to an application surface using the conveyor; and
applying the cut composite ply to a mandrel from the application surface.

9. The method of claim 8 wherein the application surface is a mesh conveyor.

10. The method of claim 9 wherein the step of applying the cut composite ply to the mandrel includes:
lifting the cut composite ply using a matrix of actuatable pins from the mesh conveyor to apply the cut composite ply to the mandrel.

11. The method of claim 10 wherein the step of lifting the cut composite ply using the matrix of actuatable pins includes:
actuating at least one actuatable pin of the matrix of actuatable pins to precisely support a shape of the cut composite ply during the lifting of the cut composite ply from the mesh conveyor to the mandrel.

12. The method of claim 11 further comprising:
locating the mandrel relative to a location of the cut composite ply lifted above the mesh conveyor.

13. The method of claim 11 further comprising:
robotically locating the mandrel relative to a location of the cut composite ply lifted above the mesh conveyor.

14. The method of claim 8 wherein the step of applying the cut composite ply to the mandrel comprises applying the cut composite ply in an edge-to-edge orientation against a previously applied cut composite ply.

15. The method of claim 8 further comprising:
robotically picking the backing material from the cut composite ply to remove the backing material.

16. The method of claim 8 further comprising:
lowering the mandrel into engagement with the cut composite ply to apply the cut composite ply to the mandrel.

17. The method of claim 8 further comprising pre-heating the mandrel.

18. A method for forming a composite laminate, the method comprising:
supporting a cut composite ply on a mesh surface; and
lifting the cut composite ply using actuated pins of a matrix of actuatable pins to apply the cut composite ply to a mandrel to form at least a portion of the composite laminate on a surface of the mandrel, wherein the actuated pins extend through openings in the mesh surface to lift the cut composite ply.

19. The method of claim 18 , further comprising actuating a matrix of electromechanical actuators to lift the actuated pins of the matrix of actuatable pins.

20. The method of claim 18 , further comprising actuating a matrix of pneumatically-charged actuators to lift the actuated pins of the matrix of actuatable pins.

Assignees

• Boeing Co

Inventors

• Petrovski Goce
• Kokarevski Steven

Classifications

• B29C31/002 Primary

  Handling tubes, e.g. transferring between shaping stations, loading on mandrels · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• B29C2793/0072

  combined with rearranging and joining the cut parts · CPC title

• B29C66/81463

  comprising a plurality of single pressing elements, e.g. a plurality of sonotrodes, or comprising a plurality of single counter-pressing elements, e.g. a plurality of anvils, said plurality of said single elements being suitable for making a single joint · CPC title

• B32B43/006

  Delaminating · CPC title