IP Library Granted Patent US 10,047,465
Granted Patent B2
US 10,047,465 · App. 14/845,468 · Granted Aug 14, 2018

Method for manufacturing a fiber composite component

Inventor: Thomas Meer (Egmating, DE)
Assignee: Airbus Defence and Space GmbH
D05C15/16B29C70/24B32B5/26B32B7/12D06M17/04B32B2260/00B32B2605/18Y10T29/49801
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Quick Facts
Patent No.
US 10,047,465
App. No.
14/845,468
Granted
Aug 14, 2018
Kind
B2
Abstract

A fiber composite component includes a composite including cured matrix material and a fiber material embedded therein. At least one partial area of the fiber composite component is provided with at least one thread, which undulates as it extends along a surface area of the composite, so that sections of the thread alternately run inside of the composite and outside of the composite. An adhesive arrangement for such fiber composite components is also disclosed. Finally, methods for manufacturing such a fiber composite component or for manufacturing such an adhesive arrangement are disclosed.

Claims (13)

1. A method for manufacturing a fiber composite component comprising:

a) providing a fiber material with a separating foil on a surface area;

b) introducing at least one thread into at least one partial area of the fiber material, such that the thread undulates as the thread extends along the surface area of the fiber material, such that sections of the thread alternately run inside of the fiber material and outside of the fiber material;

c) infiltrating the fiber material with a curable matrix material;

d) curing the matrix material; and

e) peeling away the separating foil from the fiber material, so that the thread loops are free of the matrix material.

2. The method of claim 1 , wherein the at least one thread includes a plurality of several fibers.

3. The method of claim 1 , wherein the thread sections running outside of the composite each have a length of at least 0.2 mm.

4. The method of claim 1 , wherein the thread sections running outside of the composite each have a length of at least 0.4 mm.

5. The method of claim 1 , wherein at least 20% of the at least one thread runs inside of the composite and/or at least 30% of the at least one thread runs outside of the composite.

6. The method of claim 1 , wherein at least 30% of the at least one thread runs inside of the composite and/or at least 40% of the at least one thread runs outside of the composite.

7. The method of claim 1 , wherein the thread sections running outside of the composite in the surface area of a partial area are provided with a density of at least 5,000/qm.

8. The method of claim 1 , wherein the thread sections running outside of the composite in the surface area of a partial area are provided with a density of at least 10,000/qm.

Assignments (2)
CORRECTIVE ASSIGNMENT TO CORRECT THE ASSIGNEE'S ADDRESS PREVIOUSLY RECORDED AT REEL: 037071 FRAME: 0963. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT. Recorded Dec 2, 2015
From: MEER, THOMAS
To: AIRBUS DEFENCE AND SPACE GMBH
Reel/Frame 037195/0539 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Nov 18, 2015
From: MEER, THOMAS
To: AIRBUS DEFENCE AND SPACE GMBH
Reel/Frame 037071/0963 →
Priority Claims (1)
DE 10 2014 012 915 · Sep 5, 2014 · national
Continuity (1)
Related Publication 20160069009A1 · Mar 10, 2016