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