Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45 diameter) footprint.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45 diameter) footprint.

To control charging of a battery without applying an overload by power feed of a generator based on a state of charge of the battery. A charge control system includes an engine and a motor generator for supplying generated power to two motors of a VTOL rotor and a cruising rotor, a plurality of batteries including two batteries for storing the electrical power generated by the generator and supply the stored electrical power to each of the two motors, a switch for connecting or disconnecting each of the batteries to or from the generator, and a control section for controlling the switch based on a state of charge of each of the batteries to disconnect one battery with a larger charge amount out of the two batteries from the generator and connect the other battery with the smaller charge amount out of the two batteries to the generator.

To control charging of a battery without applying an overload by power feed of a generator based on a state of charge of the battery. A charge control system includes an engine and a motor generator for supplying generated power to two motors of a VTOL rotor and a cruising rotor, a plurality of batteries including two batteries for storing the electrical power generated by the generator and supply the stored electrical power to each of the two motors, a switch for connecting or disconnecting each of the batteries to or from the generator, and a control section for controlling the switch based on a state of charge of each of the batteries to disconnect one battery with a larger charge amount out of the two batteries from the generator and connect the other battery with the smaller charge amount out of the two batteries to the generator.

A thrust generator for a rotorcraft includes: a support part detachably mounted to a base provided in the rotorcraft; a rotor shaft rotatably supported by the support part; multiple rotating blades joined to the rotor shaft; and a drive unit detachably mounted to the support part or the base, wherein an output shaft of the drive unit is detachably connected to the rotor shaft.

A thrust generator for a rotorcraft includes: a support part detachably mounted to a base provided in the rotorcraft; a rotor shaft rotatably supported by the support part; multiple rotating blades joined to the rotor shaft; and a drive unit detachably mounted to the support part or the base, wherein an output shaft of the drive unit is detachably connected to the rotor shaft.

An assembly for a propulsion system of an aircraft includes a gearbox, at least one accessory load assembly, a propulsor, and an electric motor. The gearbox module includes a gear assembly and an output shaft. The gear assembly is connected to the output shaft. The at least one accessory load assembly includes at least one accessory load coupled to the output shaft. The propulsor is coupled to the output shaft. The electric motor includes a rotor. The rotor is coupled to the gear assembly to drive rotation of the output shaft about a rotational axis. The rotation of the output shaft drives rotation of the propulsor and the at least one accessory load for each accessory load assembly of the at least one accessory load assembly.

An assembly for a propulsion system of an aircraft includes a gearbox, at least one accessory load assembly, a propulsor, and an electric motor. The gearbox module includes a gear assembly and an output shaft. The gear assembly is connected to the output shaft. The at least one accessory load assembly includes at least one accessory load coupled to the output shaft. The propulsor is coupled to the output shaft. The electric motor includes a rotor. The rotor is coupled to the gear assembly to drive rotation of the output shaft about a rotational axis. The rotation of the output shaft drives rotation of the propulsor and the at least one accessory load for each accessory load assembly of the at least one accessory load assembly.

In a first aspect, described herein is a direct drive electric aircraft propulsion wherein the propulsion rotor torque is decoupled from the primary proprotor mast moment forces. A hub shaft locates the propulsion proprotor assembly in space relative to the aircraft nacelle, while a motor torque coupler transfers torque from the electric motor to the propulsion rotor while resolving a negligible amount of mast moment through the electric motor.

In a first aspect, described herein is a direct drive electric aircraft propulsion wherein the propulsion rotor torque is decoupled from the primary proprotor mast moment forces. A hub shaft locates the propulsion proprotor assembly in space relative to the aircraft nacelle, while a motor torque coupler transfers torque from the electric motor to the propulsion rotor while resolving a negligible amount of mast moment through the electric motor.