Method for limiting interlaminar fatigue in composite laminate and a component incorporating the same

Patent metadata

Field	Value
Publication number	US-10792896-B2
Application number	US-201514798658-A
Country	US
Kind code	B2
Filing date	Jul 14, 2015
Priority date	Jul 14, 2014
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

In some embodiments, a rotor system for a rotorcraft includes a yoke, a blade, and a grip that is configured to couple the blade to the yoke. The grip has a plurality of baseline layers and a compliant layer. The baseline layers each have a plurality of fibers disposed in a first polymeric matrix. The compliant layer has a plurality of fibers disposed in a second polymeric matrix. The compliant layer is stronger than the baseline layer and the first polymeric matrix has a different chemical composition than the second polymeric matrix.

First claim

The invention claimed is:

1. A composite component, comprising:
a composite laminate portion, comprising:
a plurality of baseline layers, each baseline layer having a plurality of carbon fibers disposed in a first polymeric matrix and an end section; and
a compliant layer having a plurality of basalt fibers disposed in a second polymeric matrix, wherein the compliant layer has a tensile strength greater than the baseline layer and the first polymeric matrix has a different chemical composition than the second polymeric matrix; the compliant layer includes an end section that overlaps an end section of a baseline layer.

2. The composite component of claim 1 , wherein the compliant layer is placed within the composite component at a location where peak interlaminar stresses occur.

3. The composite component of claim 1 , wherein the compliant layer has a planar dimension that is substantially the same as the planar dimension of the composite component.

4. The composite component of claim 1 , wherein the tensile strength of the compliant layer is greater than two-hundred and fifty thousand pounds per square inch.

5. The composite component of claim 1 , wherein the compliant layer is smaller than a baseline layer.

6. The composite component of claim 1 , wherein the second polymeric matrix has more elastomer than the first polymeric matrix.

7. The composite component of claim 1 , wherein the second polymeric matrix of the compliant layers is stronger than the first polymeric matrix of the baseline layers.

8. The composite component of claim 7 , wherein the first polymeric matrix of the baseline layers is an amine cured, toughened epoxy resin system.

9. The composite component of claim 8 , wherein the plurality of fibers of the baseline layers are unidirectional tape layers that are pre-impregnated with the amine cured, toughened epoxy resin system.

10. A composite component, comprising:
a composite laminate portion, comprising:
a plurality of baseline layers, each baseline layer is a unidirectional carbon fiber tape layer disposed in a first polymeric matrix and an end section; and
a compliant layer having a plurality of basalt fibers disposed in a second polymeric matrix and the first polymeric matrix has a different chemical composition than the second polymeric matrix, the compliant layer includes an end section that overlaps an end section of a baseline layer;
wherein the compliant layer has a tensile strength greater than the baseline layer.

11. The composite component of claim 10 , wherein the tensile strength of the compliant layer is greater than two-hundred and fifty thousand pounds per square inch.

12. The composite component of claim 10 , wherein the compliant layer is smaller than a baseline layer.

13. The composite component of claim 10 , wherein the second polymeric matrix has more elastomer than the first polymeric matrix.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Krasnowski Bogdan Roman
• Brack Robert Arnold
• Li Xiaoming
• Wardlaw Robert

Classifications

• B32B37/144

  using layers with different mechanical or chemical conditions or properties, e.g. layers with different thermal shrinkage, layers under tension during bonding (constructional features for tensioning B32B38/1825) · CPC title

• B29C70/30

  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 title

• B32B27/08 Primary

  of synthetic resin · CPC title

• B29L2031/3088

  Helicopters · CPC title

• B32B2262/106

  Carbon fibres, e.g. graphite fibres · CPC title