A system comprising a connection device having a first shaft and a second shaft, the connection device comprising a free-wheel interposed between the first shaft and the second shaft that can only transmit engine torque from the first shaft to the second shaft when a motor mode is activated. The connection device comprises a coupler, the coupler being provided with a fusible section, the connection device comprising a dog clutch connection that can only transmit engine torque from the coupler to the first shaft when an electrical power generation mode is activated.

A monitoring system for monitoring a hybrid power plant of a rotorcraft comprising at least one rotor. The hybrid power plant has an electric motor comprising a first drive shaft, a heat engine comprising a second drive shaft and a gearbox. The monitoring system includes at least one first sensing device measuring a first item of torque information representative of a first engine torque C1 transmitted by the first drive shaft to a first input shaft of the gearbox and a controller comparing the first engine torque C1 with a first limit value VL1.

A monitoring system for monitoring a hybrid power plant of a rotorcraft comprising at least one rotor. The hybrid power plant has an electric motor comprising a first drive shaft, a heat engine comprising a second drive shaft and a gearbox. The monitoring system includes at least one first sensing device measuring a first item of torque information representative of a first engine torque C1 transmitted by the first drive shaft to a first input shaft of the gearbox and a controller comparing the first engine torque C1 with a first limit value VL1.

Provided are a vertical takeoff and landing aircraft using a hybrid propulsion system and a control method therefor, the aircraft including: a thrust propeller for generating thrust in an aerial vehicle; a lift propeller for generating lift in the aerial vehicle; an engine which is installed in the aerial vehicle and burns fuel to produce power; a clutch device for transmitting the power of the engine to the thrust propeller; a first power generator that generates electrical power by means of the rotational force of the thrust propeller when the thrust propeller rotates as the aerial vehicle descends or flies into a headwind; a second power generator that generates electrical power by means of the rotational force of the lift propeller when the lift propeller rotates as the aerial vehicle descends or flies into a headwind; a battery management system in which the electricity generated from the first and second power generators is charged; and a control unit that controls the first and second power generators to operate as motors when the aerial vehicle ascends or flies with a tailwind.

Provided are a vertical takeoff and landing aircraft using a hybrid propulsion system and a control method therefor, the aircraft including: a thrust propeller for generating thrust in an aerial vehicle; a lift propeller for generating lift in the aerial vehicle; an engine which is installed in the aerial vehicle and burns fuel to produce power; a clutch device for transmitting the power of the engine to the thrust propeller; a first power generator that generates electrical power by means of the rotational force of the thrust propeller when the thrust propeller rotates as the aerial vehicle descends or flies into a headwind; a second power generator that generates electrical power by means of the rotational force of the lift propeller when the lift propeller rotates as the aerial vehicle descends or flies into a headwind; a battery management system in which the electricity generated from the first and second power generators is charged; and a control unit that controls the first and second power generators to operate as motors when the aerial vehicle ascends or flies with a tailwind.

An electric motor drive system for a propulsion device. The system includes a battery stack having an earth terminal and an end terminal and an electric motor electrically connected to be powered by the battery stack. The motor is configured to be connected to drive the propulsion device, The system also includes: a power converter electrically connected between the battery stack and the electric motor; and a switch between the power converter and the battery stack. The switch is arranged to switch between a first state electrically connecting the end terminal of the battery stack to the power converter to provide a maximum battery voltage to the power converter, and a second state electrically connecting a tap point from one or more intermediate nodes, intermediate the earth terminal and the end terminal, of the battery stack, to provide a voltage less than the maximum battery voltage to the power converter.

An electric motor drive system for a propulsion device. The system includes a battery stack having an earth terminal and an end terminal and an electric motor electrically connected to be powered by the battery stack. The motor is configured to be connected to drive the propulsion device, The system also includes: a power converter electrically connected between the battery stack and the electric motor; and a switch between the power converter and the battery stack. The switch is arranged to switch between a first state electrically connecting the end terminal of the battery stack to the power converter to provide a maximum battery voltage to the power converter, and a second state electrically connecting a tap point from one or more intermediate nodes, intermediate the earth terminal and the end terminal, of the battery stack, to provide a voltage less than the maximum battery voltage to the power converter.

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.

A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.

A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.