A hybrid-electric or all-electric powertrain may include a power control unit electrically coupled to an energy storage system. The power control unit may determine a power level command based at least in part on a power level request for the powertrain, and a power level-UCL and/or a power level-LCL. The power level-UCL and/or the power level-LCL may be based at least in part on an aggregate obverse power level request representing a requested power level for one or more obverse powertrains electrically coupled to the energy storage system. The power level commands may be limited by the power level-UCL and/or the power level-LCL. The power level-UCL may be set equal to either an available discharge power capacity or an apportionate discharge power capacity. The power level-LCL may be set equal to either an available storage power capacity or an apportionate storage power capacity.

A system is provided for an aircraft. This aircraft system includes a propulsor, a powerplant and a control system. The powerplant is configured to output mechanical power to drive rotation of the propulsor. The powerplant includes a heat engine and an electric machine. The heat engine is configured to provide a first portion of the mechanical power. The electric machine is configured to provide a second portion of the mechanical power. The control system is configured to operate the powerplant to control a rotational speed of the propulsor by adjusting the second portion of the mechanical power.

Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and/or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.

A method for determining at least one minimum power margin of a hybrid drive train for a transport vehicle, each drive element being associated with at least one power source and at least one power consumer. The method including a step of acquiring measurements of power parameters, a step of comparing each measurement with at least one limitation threshold, so as to deduce therefrom at least one gross margin, a step of converting the gross margins into refined margins expressed according to the same common magnitude, a step of transposing into standardised margins at least at one reference point, a step of determining a source power margin and a consumer power margin at said reference point and a step of determining the minimum power margin by selecting the lowest power margin.

Methods and systems for operating an aircraft power plant including an electric motor configured to propel an aircraft are provided. The methods and systems are used to mitigate a fault associated with the electric motor. The method includes receiving a power request from a power lever of the aircraft and using a controller to control the electric motor according to the power request. After a fault associated with the electric motor has been detected, the method includes receiving a deactivation request from the power lever. After receiving the deactivation request, the electric motor is deactivated independently of the controller.

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 electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an electric motor configured to drive the propulsor. A controller is in signal communication with the gas turbine engine and the electric propulsion system. The controller operates the gas turbine engine based on an on-board engine model (OEM), monitors electrical parameters of the electric propulsion system, and updates the OEM in response to changes to the electrical parameters.

A craft comprises at least one hull, a main wing coupled to the hull and configured to facilitate airborne operations of the craft, a plurality of propellers that include one or more electric motor propellers and one or more combustion motor propellers arranged along each of a port side and a starboard side of the main wing and configured to generate lift on the craft by blowing air over the main wing, and a control system. The control system comprises data storage having instruction code stored thereon that, when executed by one or more processors of the control system, causes the control system to: after receiving a takeoff indication, increase thrust generated by the electric motor propellers to cause the craft to transition from a hull-borne mode of operation to an airborne mode of operation, and after a thrust adjustment condition occurs, increase thrust generated by the combustion motor propellers.

A hybrid-electric propulsion system is provided that includes a thermal engine, an electric motor, a battery, a battery management unit (BMU), an electrical distribution bus, an artificial intelligence (AI) model, and a monitoring system (MS) controller. The electrical distribution bus electrically connects the electric motor and the BMU. The MS controller is in communication with the AI model, the electric motor, the BMU, and a memory storing instructions. The instructions when executed cause the MS controller to: receive a first operational parameter from the BMU unit; control the AI model to produce a predicted first operational parameter utilizing at least one electric motor operating parameter; and determine the presence of series arcing within the electrical distribution bus using the first operational parameter and the predicted first operational parameter.