A method for assisting the piloting of a rotorcraft comprising a first engine and a second engine, each capable, in the absence of a failure, of transmitting engine torque to at least one rotor providing at least lift keeping the rotorcraft in the air. The rotorcraft has aerodynamic members for piloting the rotorcraft. The method has these steps: controlling the first engine and the second engine asymmetrically, the first engine alone providing driving power to the rotor(s), the second engine operating at a standby speed; identifying an engine failure in the first engine by a failure monitor; and in the event of failure in the first engine, accelerating the second engine to a synchronization speed.

A hybrid engine includes a gas turbine engine having at least one compressor rotor connected to be driven by at least one turbine rotor. A combustor is connected to receive compressed air from the at least one compressor rotor, and to receive fuel. At least one electric motor is connected to drive the at least one compressor rotor to supplement drive in combination with the at least one turbine rotor. A hybrid engine controller includes processing circuitry and a memory storing instructions that, when executed cause the processing circuitry to control a flow of the fuel to the combustor, control the at least one electric motor. Feedback is received on an operating condition of the hybrid engine indicative of a failure of the at least one electric motor. The at least one compressor is controlled in a first mode to operate at a compressor pressure ratio spaced from a stall pressure ratio that could result in a stall of the at least one compressor based on the operating condition not indicating a potential failure of the at least one electric motor. The at least one compressor is controlled to move to a second mode where the compressor pressure ratio is closer to the stall pressure ratio than in the first mode based on the hybrid engine controller determining that a failure of the at least one electric motor failure occurred. A method is also disclosed.

A hybrid engine includes a gas turbine engine having at least one compressor rotor connected to be driven by at least one turbine rotor. A combustor is connected to receive compressed air from the at least one compressor rotor, and to receive fuel. At least one electric motor is connected to drive the at least one compressor rotor to supplement drive in combination with the at least one turbine rotor. A hybrid engine controller includes processing circuitry and a memory storing instructions that, when executed cause the processing circuitry to control a flow of the fuel to the combustor, control the at least one electric motor. Feedback is received on an operating condition of the hybrid engine indicative of a failure of the at least one electric motor. The at least one compressor is controlled in a first mode to operate at a compressor pressure ratio spaced from a stall pressure ratio that could result in a stall of the at least one compressor based on the operating condition not indicating a potential failure of the at least one electric motor. The at least one compressor is controlled to move to a second mode where the compressor pressure ratio is closer to the stall pressure ratio than in the first mode based on the hybrid engine controller determining that a failure of the at least one electric motor failure occurred. A method is also disclosed.

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 method of operation is provided during which an electric motor of an aircraft is powered using a power supply. The power supply includes a plurality of power strings electrically coupled in parallel. The powering includes: outputting string electricity from each of the power strings; and outputting supply electricity from the power supply. A plurality of string parameters are measured using a sensor system. Each of the string parameters is indicative of an electrical parameter of the string electricity from a respective one of the power strings. The string parameters are added together to provide a total string parameter. A supply parameter is measured using the sensor system indicative of the electrical parameter of the supply electricity. Operability of the sensor system is evaluated based on the total string parameter and the supply parameter.

A method of operation is provided during which an electric motor of an aircraft is powered using a power supply. The power supply includes a plurality of power strings electrically coupled in parallel. The powering includes: outputting string electricity from each of the power strings; and outputting supply electricity from the power supply. A plurality of string parameters are measured using a sensor system. Each of the string parameters is indicative of an electrical parameter of the string electricity from a respective one of the power strings. The string parameters are added together to provide a total string parameter. A supply parameter is measured using the sensor system indicative of the electrical parameter of the supply electricity. Operability of the sensor system is evaluated based on the total string parameter and the supply parameter.

An assistance system and method for assisting with the restart of at least one engine of an aircraft includes determining that at least one engine of the aircraft has flamed out and controlling an automated descent of the aircraft down to a predefined target altitude below which the altitude of the aircraft is conducive to at least one attempt to restart the at least one stopped engine.

An assistance system and method for assisting with the restart of at least one engine of an aircraft includes determining that at least one engine of the aircraft has flamed out and controlling an automated descent of the aircraft down to a predefined target altitude below which the altitude of the aircraft is conducive to at least one attempt to restart the at least one stopped engine.

Methods and systems for detecting a torque transmission failure in an aircraft power plant are provided. The system comprises a hydrostatic transmission for transmitting torque between a first shaft and a second shaft using hydraulic fluid, an a failure detector including a sensor configured to detect a pressure change in the hydraulic fluid. The failure detector is configured to generate an output indicative of the torque transmission failure in response to the pressure change having crossed a threshold.