Composite wing structure and methods of manufacture

1. A composite skin for a torque box of a tiltrotor aircraft comprising:

a first skin having a periphery defined by a forward edge, an aft edge, and outboard ends, wherein the first skin comprises a pre-cured laminate;

a second skin comprises a pre-cured laminate;

a honeycomb core disposed between the first skin and the second skin, the honeycomb core comprised of a plurality of honeycomb panels positioned along a longitudinal axis of the first skin, the plurality of honeycomb panels having an array of large cells, each cell of the array of large cells having a width of at least 1 cm, the honeycomb core includes a plurality of filler members oriented generally perpendicular to the longitudinal axis of the first skin and between the plurality of honeycomb panels and on outboard ends of the honeycomb core, wherein each filler member of the plurality of filler members is butt jointed and co-bonded to a respective adjacent honeycomb panel of the plurality of honeycomb panels; and

a plurality of joint members on the first skin, the honeycomb core, and the second skin to form a joint system for the composite skin, wherein each joint member of the plurality of joint members is a composite material and includes a first flange, a second flange, and a support member disposed between the first flange and the second flange, the support member includes a first side and a second side, the first flange is a lower flange that extends laterally from the first side of the support member and the second flange is an upper flange that extends laterally from the second side to form generally a “Z” shape, the upper flange includes an attachment surface that overlaps a portion of the second skin and attaches thereto, the lower flange includes an attachment surface that overlaps a portion of the first skin and attaches thereto, the plurality of joint members provide a load path from the first skin to the second skin;

wherein the second skin and the honeycomb core have outer perimeters within the periphery of the first skin such that the outer perimeters of the second skin and the honeycomb core on their respective outboard edges form a length from about 5% to about 90% of a total spanwise length of the first skin;

wherein aft edges, forward edges and outboard ends of the honeycomb core and the second skin are about 90 degrees relative to a top surface of the first skin;

wherein the plurality of joint members in the joint system are disposed on the aft and forward edges of the second skin;

wherein the plurality of filler members and the plurality of joint members in the joint system provide a fluid barrier for the honeycomb panels in the honeycomb core.

2. The composite skin of claim 1 , wherein the outer perimeters of the honeycomb core and the second skin on the forward and aft edges is from about 1 cm to about 16 cm from the forward and aft edges of the first skin.

3. The composite skin of claim 1 , wherein the outer perimeters of the honeycomb core and the second skin on the outboard edges is from about 7 cm to about 91 cm from the outboard edges of the first skin.

4. The composite skin of claim 1 , wherein each filler member of the plurality of filler members is a compression molded material.

5. The composite skin of claim 1 , wherein the aft and forward edges of the honeycomb core and the second skin are aligned.

6. The composite skin of claim 1 , wherein the forward edge of the first skin is straight.