CPC B64C 29/0033 (2013.01) [B64D 27/24 (2013.01); B64D 29/02 (2013.01); B64D 35/02 (2013.01); B64D 35/04 (2013.01); H02K 7/108 (2013.01); H02K 7/116 (2013.01); F16D 41/00 (2013.01)] | 10 Claims |
1. A rotor system for an aircraft, the rotor system comprising:
a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and
a drive system for providing rotational energy to the rotor assembly via the rotor mast, the drive system comprising:
at least one electric motor for providing rotational energy to a drive shaft; and
a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; and
an adapter having a first interface connected to the at least one motor and a second interface connected to the at least one gear box;
wherein the drive system is tiltable relative to the wing about a tilt axis located on the adaptor between the at least one motor and the gearbox.
|