Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

A powerplant can include a first prime mover configured to turn a propulsor, and a second prime mover operatively connected in parallel with the first prime mover to turn the propulsor together with or separately from the first prime mover. The powerplant can include a firewall disposed around at least one of the first prime mover or the second prime mover to create a first prime mover fire zone and a second prime mover fire zone separate from the first prime mover fire zone such that the first prime mover is protected against a second prime mover fire, and vice versa.

A method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation device a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation device, followed by a regulating step for regulating an internal voltage of the electrical power generation device as a function of the first power delivered by the rechargeable electrical energy storage device.

A power source for an aircraft having an engine, the power source including: a fuel cell assembly configured to be integrated into the engine, the fuel cell assembly including: a first fuel cell group; and a second fuel cell group, wherein during a first operating condition of the power source the fuel cell assembly is configured to provide a first power output from the first fuel cell group and the second fuel cell group and during a second operating condition is further configured to provide a second power output from the first fuel cell group, the second power output being different than the first power output.

An engine system for an aircraft includes a gas turbine engine and a control system. The control system is configured to motor the gas turbine engine, absent fuel burn, during a taxi mode of the aircraft. The control system is further configured to accelerate a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode. The control system is configured to decrease the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position.

A hybrid powertrain system and method includes a prime mover driving a generator/motor to produce an AC power output. The AC power output is applied to a rectifier which is controlled to transform the applied AC power to DC power to supply a DC Power bus at a selected voltage and current. An energy storage device is also connected to the DC power bus and the current flow between the energy storage device and the DC power bus is monitored and compared to preselected values and the results of that comparison are used to alter the operation of the rectifier to increase or decrease, as needed, the current provided to the DC power bus as electrical loads on the DC power bus change.

A hybrid system for drones and other modes of transport. A combustion engine provides range and/or lifting capacity for drones while electric motors/generators provide both control and maneuverability. One or more combustion engines, in conjunction with one or more electric motors/generators form a propulsion system whereby each is connected to and drives its own driving pinion in one or more planetary gear sets, and provide continuously variable transmission for driving propellers or driveshafts. The combustion engine may be connected directly to one of the planetary gear's driving pinions, or can drive one of the planetary gear's driving pinions. If the propellers are only driven by either a combustion engine, or an electric motor/generator, the other engine/motor will be kept at rest by a braking device for a combustion engine or a braking device for an electric motor/generator.

An aircraft propulsion system is disclosed that includes at least one hybrid-electric powerplant for delivering power to an air mover for propelling the aircraft, wherein the at least one hybrid-electric powerplant includes a heat engine and an electric motor arranged in a parallel drive configuration or an in-line drive configuration.