US 11,814,163 B2
Electric tiltrotor aircraft with tilting coaxial motors and gearbox
Jonathan Andrew Knoll, Burleson, TX (US); George Matthew Thompson, Lewisville, TX (US); Charles Hubert Speller, Flower Mound, TX (US); and Grant Michael Beall, Arlington, TX (US)
Assigned to TEXTRON INNOVATIONS INC., Providence, RI (US)
Filed by Bell Textron Inc., Fort Worth, TX (US)
Filed on Jan. 13, 2021, as Appl. No. 17/148,307.
Prior Publication US 2022/0219817 A1, Jul. 14, 2022
Int. Cl. B64C 29/00 (2006.01); B64D 27/24 (2006.01); B64D 29/02 (2006.01); B64D 35/02 (2006.01); B64D 35/04 (2006.01); H02K 7/108 (2006.01); F16D 41/00 (2006.01); H02K 7/116 (2006.01)
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
OG exemplary drawing
 
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.