CPC B64C 27/08 (2013.01) [B64C 27/00 (2013.01); B64C 27/20 (2013.01); B64C 27/82 (2013.01); B64C 2027/8281 (2013.01)] | 20 Claims |
14. A rotorcraft comprising:
a fuselage;
a tailboom extending from the fuselage;
a tail rotor rotatably coupled to an aft portion of the tailboom and configured to provide yaw control for the rotorcraft; and
a propulsion system coupled to the fuselage, the propulsion system comprising:
a first fan assembly including a central fan and a mast, the central fan including a plurality of first fan blades;
a plurality of second fan assemblies each including a plurality of second fan blades, the second fan assemblies radially symmetric about the mast of the central fan assembly; and
a drive system adapted to provide torque to the first and second fan blades;
wherein, the first fan blades have a larger rotational inertia than the second fan blades;
wherein, the central fan forms a rotor disk and the second fan assemblies are disposed outboard of the rotor disk of the central fan;
wherein, the second fan blades are formed from a different and lighter material than the first fan blades; and
wherein, the second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.
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