Composite aircraft joint
A method and apparatus comprises a first number of layers of a composite material for a wing, a second number of layers of the composite material for the wing, and a metal layer located between the first number of layers and the second number of layers in the wing. The metal layer has a first thickness at a first area configured to receive a number of fasteners and a second thickness at a second area.
1. An apparatus comprising:
a first number of layers of a composite material forming an exterior of a skin of a wing;
a second number of layers of the composite material forming an interior of the skin of the wing;
a metal layer located between the first number of layers and the second number of layers in the wing, wherein the metal layer has a first thickness at a first area configured to receive a number of fasteners and a second thickness that is different from the first thickness at a second area, wherein the exterior is parallel to the interior from the first area to the second area.
2. The apparatus of claim 1 , wherein the second area is configured to transfer loads carried by the metal layer to the first number of layers and the second number of layers in the second area.
3. The apparatus of claim 1 , wherein the metal layer changes in thickness by at least one of tapering from the first thickness to the second thickness and changing from the first thickness to the second thickness with a stair-step shape.
4. The apparatus of claim 1 , wherein the first number of layers, the second number of layers, and the metal layer extend to an edge of the wing configured to be attached to a fuselage of an aircraft in which the first area of the metal layer configured to receive the number of fasteners is at the edge of the wing.
5. The apparatus of claim 1 , wherein a portion of the metal layer extends beyond an edge for the first number of layers and the second number of layers, wherein the portion of the metal layer is configured for use in testing the metal layer with a selected load that is less than a maximum load expected during flight of an aircraft.
6. The apparatus of claim 1 , wherein the metal layer is comprised of a material selected from one of titanium, steel, and a metal alloy.
7. The apparatus of claim 1 , wherein the first number of layers and the second number of layers are configured to carry a load up to a maximum load expected during flight of an aircraft.
8. The apparatus of claim 7 , wherein the first number of layers, the second number of layers, and the metal layer are configured to carry a load greater than the maximum load expected during the flight of the aircraft.
9. The apparatus of claim 7 , wherein the load extends in a direction along a plane through the metal layer.
10. The apparatus of claim 1 , wherein the metal layer is bonded to the first number of layers and the second number of layers.
11. The apparatus of claim 1 , wherein the metal layer has a first side and a second side opposite to the first side and further comprising:
a first layer of adhesive located on the first side of the metal layer, wherein the first number of layers is on the first layer of adhesive; and
a second layer of adhesive located on the second side of the metal layer, wherein the second number of layers is on the second layer of adhesive.