A method and apparatus for forming a composite winglet (600)for an aircraft is presented. The composite winglet comprises a first blade (602), a second blade (604), and a root region (606). The first blade (602) includes a first leading edge (608) and a first trailing edge (610). The second blade (604) includes a second leading edge (612) and a second trailing edge (614). The second blade (604) is positioned at an angle to the first blade (602). The root region (606) is co-cured with the first blade (602) and the second blade (604) to form the composite winglet (600). The root region (606) is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.
One-piece composite bifurcated winglet
2015-07-15
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |