Manufacturing method for trumpet spar and other curved objects

• US 8,871,126 B2
• Filed: 10/04/2006
• Issued: 10/28/2014
• Est. Priority Date: 10/17/2005
• Status: Expired due to Fees

• Current Assignee: Saab AB
• Original Assignee: Saab AB
• Inventors: Krogager, Max, Petersson, Mikael, Weidmann, Bjrn, Turesson, Ingemar, Westerdahl, Anders, Vaara, Jan
• Primary Examiner(s): Khare, Atul P.
• Application Number:
  US11/538,442
• Publication Number:
  US 20080048359A1
• Time in Patent Office: 2,946 Days
• Field of Search: 264/258, 264/553, 264/136, 264/137, 264/257, 264/237, 264/322, 264/101, 264/102, 264/339, 156/196, 156/227, 156/285, 156/286, 156/299, 156/307.1
• US Class Current: 264/258
• 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 70/34 and shaping or impregnating by compression , i.e. combined with compressing after the lay-up operation
• CPC Class Codes: B29C 70/342 using isostatic pressure
• CPC Class Codes: B29C 70/543 Fixing the position or configuration of fibrous reinforcements before or during moulding for non-woven fabrics D04H3/08
• CPC Class Codes: B29D 99/0003 Producing profiled members, e.g. beams
• CPC Class Codes: B29L 2031/3085 Wings
• CPC Class Codes: B32B 27/04 as impregnant, bonding, or embedding substance not used
• CPC Class Codes: B32B 37/0015 to avoid warp or curl
• CPC Class Codes: B32B 38/1808 characterised by the laying up of the layers
• CPC Class Codes: B32B 38/1841 during laying up
• CPC Class Codes: B32B 38/1866 conforming the layers or laminate to a convex or concave profile
• CPC Class Codes: Y10T 156/1051 by folding
• CPC Class Codes: Y10T 156/1092 All laminae planar and face to face
• CPC Class Codes: Y10T 428/31504 Composite [nonstructural laminate]

Abstract

A method for producing an object of composite material comprising the steps of:

• • placing one or several prepregs on a plane surface, forming a fiber stack;
  • lifting over the fiber stack to a molding tool;
  • downforming the fiber stack;
  • curing the downformed fiber stack;
    where the method also comprises the step of:
  • orienting the fiber directions so that all fibers, when the fiber stack is lifted over to the molding tool, will cross an edge of the molding tool only once.

Claims

1. A method for producing an object of composite material, the method comprising:

providing a curved molding tool having a curved spar rib surface forming corners at opposite sides thereof with a concave flange surface and a convex flange surface, each corner having a curvature matching that of the spar rib surface, and the concave and convex flange surfaces each having a curvature matching that of its respective corner with the spar rib surface;

forming a fiber stack of a plurality of fiber prepregs over the spar rib surface so that the fiber stack folds over each of said corners, wherein no fiber directions of the fiber stack are parallel with curvature of the molding tool, and wherein all fibers of the fiber stack cross each of said corners only once;

downforming the fiber stack by activation of a vacuum bag applying pressure causing the fiber stack to conform to the molding tool; and

curing the downformed fiber stack.

2. The method according to claim 1, wherein fiber directions of the prepregs are oriented so that a difference between a critical prepreg fiber direction and said curvature of the molding tool permits downforming in a simple manner, the critical prepreg fiber direction being a fiber direction which is most parallel with said curvature of the molding tool.

3. The method according to claim 1, wherein a difference between any stack fiber direction and said curvature of the molding tool is between 0 and 90 degrees.

4. The method according to claim 1, wherein a difference between any stack fiber direction and said curvature of the molding tool is between 5 and 85 degrees.

5. The method according to claim 1, wherein a difference between any stack fiber direction and said curvature of the molding tool is between 0 and 45 degrees.

6. The method according to claim 1, wherein a difference between any stack fiber direction and said curvature of the molding tool is between 5 and 40 degrees.

7. The method according to claim 1, wherein a difference between any stack fiber direction and said curvature of the molding tool is between 10 and 35 degrees.

8. The method according to claim 1, wherein a difference between stack fiber direction and said curvature of the molding tool is between 0 and 22.5 degrees.

9. The method according to claim 1, wherein a difference between stack fiber direction and said curvature of the molding tool is between 5 and 17.5 degrees.

10. The method according to claim 1, wherein a difference between stack fiber direction and said curvature of the molding tool is between 10 and 12.5 degrees.

11. The method according to claim 1, wherein the concave and convex flange surfaces comprise curved planes, and wherein the spar rib surface comprises a plane having curved edges forming said corners at intersections with the concave and convex flange surfaces.

12. The method according to claim 1, wherein each fiber prepreg comprises one of a fiber tape, a fiber fabric, and a non-woven fiber cloth.

13. The method according to claim 1, wherein each fiber prepreg is a fiber tape of unidirectional fibers impregnated with a matrix material.