Wrinkle control method and tool therefor

• US 9,067,371 B2
• Filed: 11/08/2012
• Issued: 06/30/2015
• Est. Priority Date: 11/23/2011
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Williams, Stephen, Sanderson, Timothy
• Primary Examiner(s): DANIELS, MATTHEW J
• Application Number:
  US13/671,809
• Publication Number:
  US 20130129526A1
• Time in Patent Office: 964 Days
• Field of Search: 264/258
• US Class Current: 1/1
• CPC Class Codes: B29C 70/30 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 Class Codes: B29C 70/462 Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
• CPC Class Codes: B29C 70/56 Tensioning reinforcements before or during shaping
• CPC Class Codes: B29C 70/88 characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
• CPC Class Codes: B29L 2031/001 Profiled members, e.g. beams, sections
• CPC Class Codes: B29L 2031/3076 Aircrafts blades, propellers B29L2031/08
• CPC Class Codes: B29L 2031/3085 Wings
• CPC Class Codes: Y10T 156/1002 with permanent bending or reshaping or surface deformation of self sustaining lamina
• CPC Class Codes: Y10T 428/24446 Wrinkled, creased, crinkled or creped
• CPC Class Codes: Y10T 428/24612 Composite web or sheet

Abstract

A method for forming a laminate component, the method comprising the steps of: a) providing a tool having a molding surface; b) arranging a stack of ply layers on the molding surface of the tool; and c) molding the stack of ply layers over the molding surface in a molding process, wherein the tool has a wrinkle control feature in its molding surface for managing the development of wrinkle in the ply layers during the molding process, and wherein the wrinkle control feature cooperates with the stack of ply layers during the molding process to produce a local surface undulation in a nominal surface of the laminate component nearest the tool to either prevent wrinkling in the ply layers or initiate wrinkling in one or more of the ply layers at a predetermined location. Also, a tool having a wrinkle control feature, and a laminate component so formed.

Claims

1. A method for forming a composite spar comprising:

a) providing an elongate tool having a moulding surface comprising an edge and a corner and a recess and/or protrusion wrinkle control feature in the moulding surface extending from the edge and tapering toward the corner;

b) arranging a stack of ply layers on the moulding surface of the tool;

c) moulding the stack of ply layers over the moulding surface in a moulding process; and

d) curing the stack of ply layers to form a composite spar;

wherein the wrinkle control feature cooperates with the stack of ply layers during the moulding process to produce a local surface undulation only in the surface of the stack of ply layers moulded against the moulding surface that either prevents wrinkling in the ply layers or initiates wrinkling in one or more of the ply layers at a predetermined location.

2. A method according to claim 1 wherein the wrinkle control feature comprises a recess extending into the moulding surface of the tool.

3. A method according to claim 1 wherein the wrinkle control feature comprises a protrusion extending out from the moulding surface of the tool.

4. A method according to claim 1 wherein the wrinkle control feature provides an increased path length over a region of the moulding surface which accommodates excess material in at least one of the ply layers.

5. A method according to claim 1 wherein the wrinkle control feature accommodates sufficient excess material in at least one of the ply layers so as to prevent wrinkling of the ply.

6. A method according to claim 1 wherein the wrinkle control feature has a height which varies across its extent.

7. A method according to claim 1 wherein the wrinkle control feature is substantially dart or arrowhead shaped.

8. A method according to claim 1 comprising a plurality of wrinkle control features.

9. A method according to claim 8 wherein at least some of the wrinkle control features are adjacent one another.

10. A method according to claim 1 wherein the moulding surface has a complex three-dimensional shape.

11. A method according to claim 1 wherein the tool is elongate and has a longitudinal direction, and the shape of the moulding surface varies in the longitudinal direction.

12. A method according to claim 1 wherein the composite spar has a complex three dimensional shape.

13. A method according to claim 1 wherein the composite spar has an L-section or a C-section.

14. A method according to claim 1 wherein the composite spar is an aircraft component.

15. A method according to claim 1 wherein the aircraft component is a wing spar.