Split resistant composite laminate
First Claim
1. A wing skin, comprising:
- a composite laminate comprisinga matrix; and
reinforcing fibers embedded in the matrix, a first plurality of the reinforcing fibers generally being parallel with an orientation in a range of 3 to 8 degrees, a second plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
3 to −
8 degrees, a third plurality of the reinforcing fibers generally being parallel with an orientation in a range of 21 to 40 degrees, a fourth plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
21 to −
40 degrees, and a fifth plurality of the reinforcing fibers generally being parallel with an orientation of approximately 90 degrees, the orientations being with respect to a predetermined axis, the reinforcing fibers of the composite laminate collectively having a total volume, the first and the second pluralities of the reinforcing fibers making up about 50 percent of the total volume, and the third and the fourth pluralities of the reinforcing fibers making up about 40 percent of the total volume.
1 Assignment
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Accused Products
Abstract
A composite laminate, method of forming same, and use for same are disclosed. One example of a composite laminate has multiple layers or plies (305A-305E) composed of generally parallel reinforcing fibers (315A-315E) embedded in a matrix (305M). The reinforcing fibers have orientations in the ranges of 3 to 8 degrees, −3 to −8 degrees, 10 to 40 degrees, −10 to −40 degrees, and approximately 90 degrees, the orientations being with respect to a predetermined axis (320), such as an axis of tension (T). A method of manufacturing a composite laminate includes laying a resin and fibers having these orientations and then curing the resulting laminate. One example of a use is for the skin on the fuselage or wing of an aircraft.
102 Citations
23 Claims
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1. A wing skin, comprising:
a composite laminate comprising a matrix; and reinforcing fibers embedded in the matrix, a first plurality of the reinforcing fibers generally being parallel with an orientation in a range of 3 to 8 degrees, a second plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
3 to −
8 degrees, a third plurality of the reinforcing fibers generally being parallel with an orientation in a range of 21 to 40 degrees, a fourth plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
21 to −
40 degrees, and a fifth plurality of the reinforcing fibers generally being parallel with an orientation of approximately 90 degrees, the orientations being with respect to a predetermined axis, the reinforcing fibers of the composite laminate collectively having a total volume, the first and the second pluralities of the reinforcing fibers making up about 50 percent of the total volume, and the third and the fourth pluralities of the reinforcing fibers making up about 40 percent of the total volume.- View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A method of manufacturing a composite laminate of a wing skin, comprising:
embedding reinforcing fibers in a matrix, a first plurality of the reinforcing fibers generally being parallel with an orientation in a range of 3 to 8 degrees, a second plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
3 to −
8 degrees, a third plurality of the reinforcing fibers generally being parallel with an orientation in a range of 31 to 40 degrees, a fourth plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
31 to −
40 degrees, and a fifth plurality of the reinforcing fibers generally being parallel with an orientation of approximately 90 degrees, the orientations being with respect to a predetermined axis, wherein the reinforcing fibers collectively have a total volume, the first and the second pluralities of the reinforcing fibers making up about 50 percent of the total volume, and the third and the fourth pluralities of the reinforcing fibers making up about 40 percent of the total volume.- View Dependent Claims (12, 13, 14, 15, 16, 17)
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18. An aircraft, comprising:
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a fuselage; a wing assembly operatively connected to the fuselage; and a composite laminate incorporated into at least a selected portion of a skin of the fuselage or the wing assembly, the composite laminate comprising reinforcing fibers embedded in a matrix, a first plurality of the reinforcing fibers generally being parallel with an orientation in a range of 3 to 8 degrees, a second plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
3 to −
8 degrees, a third plurality of the reinforcing fibers generally being parallel with an orientation in a range of 21 to 40 degrees, a fourth plurality of the reinforcing fibers generally being parallel with an orientation in a range of −
21 to −
40 degrees, and a fifth plurality of the reinforcing fibers generally being parallel with an orientation of approximately 90 degrees, the orientations being with respect to a predetermined axis such that none of the orientations are parallel with the predetermined axis, the reinforcing fibers collectively having a total volume, the first and the second pluralities of the reinforcing fibers making up about 50 percent of the total volume, and the third and the fourth pluralities of the reinforcing fibers making up about 40 percent of the total volume,wherein the first, second, third, fourth, and fifth pluralities of the reinforcing fibers abut one another to comprise a first set of layers, and wherein the composite laminate comprises a plurality of sets of layers abutting one another, each set of layers equivalent to the first set of layers. - View Dependent Claims (19, 20, 21, 22, 23)
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Specification