An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.

Embodiments are directed towards hybrid power supply that provides electric power to a multirotor rotorcraft to extend range or flying time. In one embodiment, an internal combustion engine and fuel tank are provided that interoperate with a battery provided by a commercial multirotor rotorcraft to substantially extend flying time or flying distance.

An aircraft propulsion system capable of reducing a rotational load of an engine shaft is provided. An aircraft propulsion system includes a plurality of engines (60-1 and 60-2) and a controller (100). When a flight state is a first state, the controller (100) causes some of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine. At least one engine (60-1) of the plurality of engines (60-1 and 60-2) includes a bleed air hole (71-1), a bleed air pipe (72-1), and a bleed air valve (73-1). When causing the engine (60-2) which has stopped to start up again, the controller (100) opens a bleed air valve (73-1) in the engine (60-1) which is in operation and supplies compressed air of the compressor (62-1) to the compression chamber (64-2) of the engine (60-2) which has stopped.

A hybrid propulsion system for an aircraft comprising: an engine disposed within a fuselage of the aircraft, two electrical generators disposed within the fuselage and connected to the engine, and two nacelles. Each nacelle comprises a proprotor, and two electric motors connected to the proprotor. Each electrical generator is connected to the two electric motors in each nacelle. The proprotors provide lift for vertical takeoff and landing in a helicopter mode. A fan is coupled to the fuselage and connected to two additional electric motors. Each additional electric motor is connected to one of the two electric generators.

An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

The hybrid aircraft power plant can have an output shaft connectable to a load, the output shaft rotatable about an axis; a thermal engine having a thermal engine shaft coaxial with the output shaft; an electric motor having a rotor shaft coaxial with the output shaft; a first clutch operable to engage the thermal engine shaft with the output shaft; a second clutch operable to engage the rotor shaft with the output shaft; a third clutch operable to engage the thermal engine shaft with the rotor shaft; the first clutch, second clutch and third clutch disposed axially between the electric motor and the thermal engine, relative to the axis.

A roadable VTOL flying vehicle having a road-configuration and a flight-configuration. The roadable VTOL flying vehicle includes a roadable vehicle; at least one rotor having at least one blade, the rotor is rotatably attached to an upper section of the roadable vehicle of the flying vehicle; at least one motor configured to operatively rotate the least at least one rotor; at least one angular position sensor configured to detect the angular position of each of the at least one rotor; and a vehicle control sub-system configured to affect automatic transformation of the flying vehicle from the road-configuration to the flight-configuration and from the flight-configuration to the road-configuration, wherein the vehicle control sub-system is configured bring the at least one rotor into a parking state, when in road-configuration.

A roadable VTOL flying vehicle having a road-configuration and a flight-configuration. The roadable VTOL flying vehicle includes a roadable vehicle; at least one rotor having at least one blade, the rotor is rotatably attached to an upper section of the roadable vehicle of the flying vehicle; at least one motor configured to operatively rotate the least at least one rotor; at least one angular position sensor configured to detect the angular position of each of the at least one rotor; and a vehicle control sub-system configured to affect automatic transformation of the flying vehicle from the road-configuration to the flight-configuration and from the flight-configuration to the road-configuration, wherein the vehicle control sub-system is configured bring the at least one rotor into a parking state, when in road-configuration.

An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.