A wing airframe (36, 100, 222) for a wing (18, 102, 200) of a tiltrotor aircraft (10) includes a wing airframe coreassembly (110, 206) and a wing skin assembly (24, 118, 202) disposed on the wing airframe core assembly. The wing skin assembly (118, 202) includes an outer skin (52, 130, 208) and a damping sublayer (50, 128, 204), the damping sublayer interposed between the outer skin and the wing airframe core assembly (110, 206). The tiltrotor aircraft (10) includes a pylon assembly (30a, 30b) subject to aeroelastic movement during forward flight. The wing (18, 102, 200) is subject to deflection in response to the aeroelastic movement of the pylon assembly (30a, 30b). The damping sublayer (50, 128, 204) reduces the deflection of the wing (18, 102, 200), thereby stabilizing the wing during forward flight.
DAMPING STRUCTURES FOR TILTROTOR AIRCRAFT WINGS
DÄMPFUNGSSTRUKTUREN FÜR KIPPROTORFLUGZEUGFLÜGEL
STRUCTURES D'AMORTISSEMENT POUR AILES D'AVION À ROTORS BASCULANTS
03.06.2020
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |