Abstract: A manufacture and process for a winglet formed as a unitary structure by laying up and co-curing three ply-sets in a bifurcated configuration, without metal and fasteners, comprising three continuous surfaces: a first ply-set comprising a first continuous surface forming: an outboard surface of an upper blade; an outboard portion of a root region; and an outboard surface of a lower blade; a second ply-set forming a second continuous surface forming an inboard surface of the upper blade and an upper skin of the root region; and a third ply-set forming a third continuous surface forming an inboard surface of the lower blade and a lower skin of the root region . . . continuous surface. The root region being integral in the bifurcated configuration, matching a shape of an airfoil of a tip of a wing, and comprising two supports that comprise an additional ply-set shaped to receive an attachment system.

Abstract: A method for manufacturing a radius filler. The radius filler having a desired cross-sectional shape is formed. The radius filler has a composite material and a number of heating elements located within the composite material. The radius filler is positioned in a channel formed by a plurality of composite structures. The radius filler is inductively heated by inducing a current within the number of heating elements.

Abstract: A method and apparatus for forming a winglet formed as a one-piece composite for an aircraft is presented. The winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the winglet. The root region is configured to receive an attachment system for attaching the winglet to a wing of the aircraft.

Abstract: A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.

Abstract: A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.

Abstract: A method for manufacturing a radius filler. The radius filler having a desired cross-sectional shape is formed. The radius filler has a composite material and a number of heating elements located within the composite material. The radius filler is positioned in a channel formed by a plurality of composite structures. The radius filler is inductively heated by inducing a current within the number of heating elements.