An aircraft power plant has: a hybrid propulsion system having an electric motor, an output shaft drivingly connectable to a thrust generator, a combustion engine, a compressor, and a transmission having a first transmission drive path and a second transmission drive path selectively engageable to the first transmission drive path, the electric motor and the compressor in driving engagement with the first transmission drive path, the combustion engine and the output shaft in driving engagement with the second transmission drive path.

A hybrid rotary aircraft includes a body having an inner area; a plurality of arms rigidly attached to and extending from the body; a plurality of rotor assemblies pivotally engaged with the plurality of arms; a first gas engine; and a first brushless electric generator rotatably attached to the first gas engine and conductively coupled to each of the brushless electric motors. The plurality of rotor assemblies each having a brushless electric motor; and a rotor blades rotatably attached to the brushless electric motor.

An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.

An aircraft with an aft-fuselage propulsion system comprises a thermal engine, a first electric motor coupled to a first propulsor, a second electric motor coupled to a second propulsor, and a mechanical interlink system integrating the thermal engine, the first electric motor, the second electric motor, plural battery systems and associated power electronics, and cabling elements connecting the electric machines. An aircraft has plural mirrored aft-fuselage propulsion systems, each aft-fuselage propulsion system comprising a thermal engine, an electric motor, a propulsor, and a mechanical interlink system integrating the thermal engine, electric motor, and propulsor elements.

An aircraft with an aft-fuselage propulsion system comprises a thermal engine, a first electric motor coupled to a first propulsor, a second electric motor coupled to a second propulsor, and a mechanical interlink system integrating the thermal engine, the first electric motor, the second electric motor, plural battery systems and associated power electronics, and cabling elements connecting the electric machines. An aircraft has plural mirrored aft-fuselage propulsion systems, each aft-fuselage propulsion system comprising a thermal engine, an electric motor, a propulsor, and a mechanical interlink system integrating the thermal engine, electric motor, and propulsor elements.

A propulsion system for an aircraft having a nacelle and a fuselage is provided. The nacelle has a gas flow path and a nacelle interior region. The system includes a compressor section, an intermittent IC engine, a turbine section, a fan, and an IC cooling system. A first electric motor powers the compressor section. The compressor section produces a flow of elevated pressure compressor air. The intermittent IC engine selectively intakes the compressor air flow and produces an exhaust gas flow. The turbine section powered by exhaust gas in turn powers a first electric generator. The fan is driven by a second electric motor. The IC engine cooling system has a heat exchanger disposed within the gas flow path, coolant, coolant piping, and a pump. The heat exchanger is disposed in the nacelle.

A propulsion system for an aircraft having a nacelle and a fuselage is provided. The nacelle has a gas flow path and a nacelle interior region. The system includes a compressor section, an intermittent IC engine, a turbine section, a fan, and an IC cooling system. A first electric motor powers the compressor section. The compressor section produces a flow of elevated pressure compressor air. The intermittent IC engine selectively intakes the compressor air flow and produces an exhaust gas flow. The turbine section powered by exhaust gas in turn powers a first electric generator. The fan is driven by a second electric motor. The IC engine cooling system has a heat exchanger disposed within the gas flow path, coolant, coolant piping, and a pump. The heat exchanger is disposed in the nacelle.

An aircraft power plant has a hybrid propulsion system having an electric motor, an output shaft drivingly connectable to a thrust generator, a combustion engine, a compressor, and a planetary gear train having an Auxiliary Power Unit (APU) mode in which the electric motor is in driving engagement with the compressor via the planetary gear train while the combustion engine is disengaged from the output shaft, and a propulsion mode in which the combustion engine and the electric motor are in driving engagement with the output shaft via the planetary gear train.

An aircraft power plant has: an electric motor; a compressor; a combustion engine; an output shaft drivingly engageable to a thrust generator for propelling an aircraft equipped with the aircraft power plant; and a transmission including a gearbox having a first input drivingly engaged by the electric motor, a first output drivingly engaging the compressor, a second input drivingly engageable by the combustion engine, and a second output drivingly engageable to the output shaft, wherein the transmission has: a propulsion configuration in which the output shaft and the compressor are drivingly engaged to the electric motor and to the combustion engine via the gearbox, and an auxiliary power unit configuration in which the combustion engine and the output shaft are at rest while the electric motor drivingly engages the compressor.

An aircraft power plant has: an electric motor; a compressor; a combustion engine; an output shaft drivingly engageable to a thrust generator for propelling an aircraft equipped with the aircraft power plant; and a transmission including a gearbox having a first input drivingly engaged by the electric motor, a first output drivingly engaging the compressor, a second input drivingly engageable by the combustion engine, and a second output drivingly engageable to the output shaft, wherein the transmission has: a propulsion configuration in which the output shaft and the compressor are drivingly engaged to the electric motor and to the combustion engine via the gearbox, and an auxiliary power unit configuration in which the combustion engine and the output shaft are at rest while the electric motor drivingly engages the compressor.