An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and 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 at least one of the one or more electrical busses.

An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and 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 at least one of the one or more electrical busses.

An aircraft power plant, comprising: a fan for providing power to an aircraft; a gas turbine engine located on a first axial side of the fan, the gas turbine engine having a compressor drivingly engaged by a turbine via an engine shaft; an electric motor powered by a power source, the electric motor driving a motor shaft; and a gearbox located on a second axial side of the fan opposite the first axial side, the gearbox in driving engagement with the engine shaft, the motor shaft, and the fan, the gearbox defining a first load path between the gas turbine engine and the fan and a second load path between the electric motor to the fan, the fan in continuous driving engagement with both of the gas turbine engine and the electric motor along the first load path and the second load path.

An aircraft power plant, comprising: a fan for providing power to an aircraft; a gas turbine engine located on a first axial side of the fan, the gas turbine engine having a compressor drivingly engaged by a turbine via an engine shaft; an electric motor powered by a power source, the electric motor driving a motor shaft; and a gearbox located on a second axial side of the fan opposite the first axial side, the gearbox in driving engagement with the engine shaft, the motor shaft, and the fan, the gearbox defining a first load path between the gas turbine engine and the fan and a second load path between the electric motor to the fan, the fan in continuous driving engagement with both of the gas turbine engine and the electric motor along the first load path and the second load path.

A flying apparatus includes an airframe, a rotor attached to the airframe, and an engine to supply a driving force to rotate the rotor. The rotor overlaps the engine when viewed in an up-down direction.

A flying apparatus includes an airframe, a rotor attached to the airframe, and an engine to supply a driving force to rotate the rotor. The rotor overlaps the engine when viewed in an up-down direction.

A method of regenerating an electric power storage unit for an aircraft hybrid electric propulsion (HEP) system is provided. The HEP system includes a thermal engine, an electric motor, an electric power storage unit, a primary gearbox, and a propulsion unit. The electric motor is configured to selectively provide rotational drive to the propulsion unit. The method includes: controlling the electric motor to operate as the generator; controlling the primary gearbox to be in an output disengaged configuration, wherein in the output disengaged configuration the primary gearbox is disengaged from driving the propulsion unit and the primary gearbox is transfers rotational drive produced by the thermal engine to the electric motor; operating the thermal engine to drive the primary gearbox in the output disengaged configuration; and regenerating the electric power storage unit by providing electrical energy produced by the electric motor to the electric power storage unit.

A method of regenerating an electric power storage unit for an aircraft hybrid electric propulsion (HEP) system is provided. The HEP system includes a thermal engine, an electric motor, an electric power storage unit, a primary gearbox, and a propulsion unit. The electric motor is configured to selectively provide rotational drive to the propulsion unit. The method includes: controlling the electric motor to operate as the generator; controlling the primary gearbox to be in an output disengaged configuration, wherein in the output disengaged configuration the primary gearbox is disengaged from driving the propulsion unit and the primary gearbox is transfers rotational drive produced by the thermal engine to the electric motor; operating the thermal engine to drive the primary gearbox in the output disengaged configuration; and regenerating the electric power storage unit by providing electrical energy produced by the electric motor to the electric power storage unit.

Systems and techniques for controlling a power distribution of a hybrid powertrain system using magnetorheological (MR) clutches. In embodiments, MR clutches may be used to control the power transfer from a mechanical power source to a plurality of loads. For example, mechanical power produced by a mechanical power source (e.g., an internal combustion engine (ICE)) may be transferred to each load of the plurality of loads using an MR clutch respectively connected to each load. In this example, the amount of mechanical power transferred from the mechanical power source to each of the loads of the plurality of loads may be controlled and/or managed using the MR clutch connected to each respective load. In embodiments, a load may be engaged or disengaged from the mechanical power source gradually, such as by ramping up or ramping down the amount of mechanical power transferred via the MR clutch to the load.

Systems and techniques for controlling a power distribution of a hybrid powertrain system using magnetorheological (MR) clutches. In embodiments, MR clutches may be used to control the power transfer from a mechanical power source to a plurality of loads. For example, mechanical power produced by a mechanical power source (e.g., an internal combustion engine (ICE)) may be transferred to each load of the plurality of loads using an MR clutch respectively connected to each load. In this example, the amount of mechanical power transferred from the mechanical power source to each of the loads of the plurality of loads may be controlled and/or managed using the MR clutch connected to each respective load. In embodiments, a load may be engaged or disengaged from the mechanical power source gradually, such as by ramping up or ramping down the amount of mechanical power transferred via the MR clutch to the load.