A method for monitoring the operation of a power plant of a rotorcraft and a rotorcraft comprising at least one lift rotor rotated by the power plant comprising at least one engine. Such a rotorcraft comprises a monitoring system comprising at least one failure sensor detecting a regulation failure affecting a regulation system of the at least one engine, a speed sensor measuring a current speed of rotation of the at least one lift rotor and a controller determining whether there is a condition of compatibility or a condition of incompatibility between a current flight phase and the speed of rotation.

A method of operating a hybrid electric powertrain (HEP) may include determining, based on a HEP torque demand and a maximum torque limit for a gas turbine engine having a mechanical output coupled to a power shaft of the HEP, a target torque for the gas turbine engine. The method may also include controlling the gas turbine engine to operate according to a target speed or the target torque. The method may also include, while operating the gas turbine engine according to the target speed or the target torque, determining, based on the HEP torque demand and the target torque, a total torque compensation demand for an electric machine having a mechanical output controllably couplable to the power shaft of the HEP, and operating the electric machine according to the total torque compensation demand.

A method of operating a hybrid electric powertrain (HEP) may include determining, based on a HEP torque demand and a maximum torque limit for a gas turbine engine having a mechanical output coupled to a power shaft of the HEP, a target torque for the gas turbine engine. The method may also include controlling the gas turbine engine to operate according to a target speed or the target torque. The method may also include, while operating the gas turbine engine according to the target speed or the target torque, determining, based on the HEP torque demand and the target torque, a total torque compensation demand for an electric machine having a mechanical output controllably couplable to the power shaft of the HEP, and operating the electric machine according to the total torque compensation demand.

There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

A power control unit for an aircraft includes a control device and an input device having an adaptive power marker. The aircraft has a first engine which generates a first drive thrust, and a second engine which generates a second drive thrust. A specified power can be input by an operator via the input device. The control device controls the first and the second drive thrust so that the first engine is first controlled at an increasing first drive thrust and, only after reaching a first upper limit thrust, the second drive thrust is also controlled to increase, until a common drive thrust corresponding to the specified power is reached. The adaptive power marker outputs an optical and/or a haptic feedback on an available common drive thrust, an available relevant maximum thrust of the first and/or the second engine, and if a malfunction exists.

A power control unit for an aircraft includes a control device and an input device having an adaptive power marker. The aircraft has a first engine which generates a first drive thrust, and a second engine which generates a second drive thrust. A specified power can be input by an operator via the input device. The control device controls the first and the second drive thrust so that the first engine is first controlled at an increasing first drive thrust and, only after reaching a first upper limit thrust, the second drive thrust is also controlled to increase, until a common drive thrust corresponding to the specified power is reached. The adaptive power marker outputs an optical and/or a haptic feedback on an available common drive thrust, an available relevant maximum thrust of the first and/or the second engine, and if a malfunction exists.

Improved aircraft, which may be configured as unmanned drones or piloted aircraft, having improved fail-operational performance. The aircraft includes a twin fan arrangement and innovative motor, propeller, driver and/or power source redundancies configured to provide fail-operational functioning in the event of failure of one or more of these aircraft components. In various optional features, the aircraft may be configured for vertical takeoff and landing. The disclosed embodiments provide an aircraft that is safer and more reliable than current multi-propeller drones, while operably more versatile in cargo delivery.