Composite laminate including interlayers with through-plane regions fused to fiber beds

Patent metadata

Field	Value
Publication number	US-9821530-B2
Application number	US-201414553553-A
Country	US
Kind code	B2
Filing date	Nov 25, 2014
Priority date	Nov 25, 2014
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A composite laminate comprises first and second fiber beds, and an interlayer between the fiber beds. The interlayer includes toughened regions that extend between the fiber beds and are fused to the fiber beds.

First claim

The invention claimed is:

1. A composite laminate comprising:
first and second fiber beds; and
an interlayer between the fiber beds, the interlayer including toughened regions consisting of one of thermoplastic particles, thermoplastic filaments, and at least one thermoplastic film, the toughened regions extending between the first and second fiber beds in a through-plane direction and each of the toughened regions including first and second ends respectively fused to the first and second fiber beds by mechanical interlocking or bonding.

2. The laminate of claim 1 , wherein the toughened regions are continuous in the through-plane direction and discontinuous in an in-plane direction.

3. The laminate of claim 1 , wherein the fiber beds include reinforcing fibers embedded in a matrix.

4. The laminate of claim 3 , wherein composition of the matrix includes a thermoset.

5. The laminate of claim 1 , wherein the toughened regions are mechanically interlocked to the first and second fiber beds.

6. The laminate of claim 1 , wherein the toughened regions are bonded to the first and second fiber beds.

7. The laminate of claim 1 , wherein the toughened regions consist of at least one thermoplastic film.

8. The laminate of claim 1 , wherein the toughened regions consist of thermoplastic particles.

9. The laminate of claim 1 , wherein the toughened regions consist of thermoplastic filaments.

10. The laminate of claim 1 , wherein the interlayer is patterned to provide a plurality of portions having different levels of resistance to crack propagation, the different portions having at least one of different spatial densities of toughened regions and different compositions for the toughened regions.

11. A method comprising fabricating a composite laminate including fusing a plurality of toughened regions of an interlayer to adjacent dry first and second fiber beds, the toughened regions consisting of one of thermoplastic particles, thermoplastic filaments, and at least one thermoplastic film, the thermoplastic regions extending between the first and second fiber beds in a through-plane direction and each including first and second ends respectively fused to the first and second fiber beds by mechanical interlocking or bonding.

12. The method of claim 11 , wherein fabricating the composite laminate further includes adding matrix resin to the fiber beds after fusing the thermoplastic regions, and thereafter curing the matrix resin.

13. The method of claim 11 , wherein the interlayer includes first and second portions; and the first portion is fused to the first fiber bed, the second portion is fused to the second fiber bed; and the fiber beds are stacked with the first and second portions making contact.

14. The method of claim 13 , wherein the first and second fiber beds are impregnated with matrix resin after the fusing but before the stacking.

15. The method of claim 14 , wherein fabricating the composite laminate further includes curing the stack, whereby the first and second portions of the interlayer are fused together.

16. The method of claim 14 , wherein each portion includes an insoluble thermoplastic film, and a soluble thermoplastic film on the insoluble film; wherein each insoluble film is fused to its fiber bed; wherein matrix resin is infused into the fiber beds via through-holes in the films; and wherein the fiber beds are stacked with the soluble films making contact.

17. The method of claim 16 , further comprising curing the stack, whereby the soluble films blend with the matrix resin.

18. The method of claim 13 , wherein the first portion includes first thermoplastic particles that are fused to the first fiber bed, and the second portion includes second thermoplastic particles that are fused to the second fiber bed; and wherein at least some of the first and second particles make contact when the first and second fiber beds are stacked.

19. The method of claim 13 , wherein the first portion includes first thermoplastic filaments that are fused to the first fiber bed, and the second portion includes second thermoplastic filaments that are fused to the second fiber bed; and wherein the first and second filaments make contact when the first and second fiber beds are stacked.

20. The method of claim 19 , wherein the first filaments and the first fiber bed are oriented at a first angle, and the second filaments and the second fiber bed are oriented at a second angle.

21. The composite laminate of claim 1 , wherein the first and second fiber beds are dry.

Assignees

• Boeing Co

Inventors

• Wilenski Mark Stewart
• Hurley Kelsi Marie

Classifications

• B32B2605/18

  Aircraft · CPC title

• B32B2605/00

  Vehicles · CPC title

• B32B2307/558

  Impact strength, toughness · CPC title

• B32B2307/552

  Fatigue strength · CPC title

• B32B2307/50

  having particular mechanical properties · CPC title