The present disclosure relates to a propeller for tilt-rotor aircraft which comprises blades and hub. The blades are fixedly connected with the hub through a rotating shaft. The rotating shaft can rotate relative to the hub. A torsion adjusting mechanism is arranged in the hub. The torsion adjusting mechanism can adjust and control the rotation of the rotating shaft, thereby driving the blades to rotate to make the tilt-rotor aircraft has a good comprehensive aerodynamic performance, and ensure that the tilt rotor/propeller can achieve good aerodynamic efficiency in the hovering state and cruising state, and work reasonably and efficiently in both states. Figure 6
PROPELLER FOR TILT-ROTOR AIRCRAFT
2020-12-24
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Transition Performance of Tilt Propeller Aircraft
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