Airbus Helicopters

Airbus Helicopters Deutschland Gmbh

Guillaume Dumur

Marc Gazzino

Regis Rossotto

Hilario Vieira

Michel Jamot

Jean-François Logeais

Jérémy Camus

Mikaël Henaff

Stephane Bailly

François-Xavier Gaulmin

Stephane Cerqueira

Olivier Delecroix

Ivan Chassagne

Régis Rossotto

Anthony Leonard

Benoit Domingo

Léonard Boudier

Didier Delsalle

Damien Piger

Laurent Berger

Carl Ockier

Francois-Xavier Gaulmin

Stéphane Cerqueira

Stéphane Bailly

Benoît Domingo

A method for controlling a hybrid power plant of a vehicle provided with a heat engine and at least one electrical unit comprising an electric machine, an electrical energy source, and a power management unit, the heat engine and the at least one electric machine being mechanically connected to input shafts of a gearbox. After acquiring parameters of the at least one electrical unit, and receiving a mechanical power requirement of the vehicle, a usable electrical power that can be used by the electrical unit and at least one operating setpoint of the electrical unit are determined as a function of the parameters and the mechanical power requirement. Finally, the heat engine and the electrical unit are controlled as a function of the at least one operating setpoint in order to meet the mechanical power requirement.

Method for controlling a hybrid power plant for a vehicle and control architecture for such a hybrid power plant

A rotorcraft flight training method for a rotorcraft comprising at least two engines and at least one rotor providing lift helping to keep the rotorcraft in the air. The method comprises at least the following steps: flying the rotorcraft in a mode wherein each engine supplies driving power to the rotor; and activating a first command to start a training phase simulating asymmetric flight, the training phase comprising a first flight phase comprising a first control operation, with a controller, controlling the at least two engines and a first display operation for displaying, with a display, information carrying at least two simulated powers.

Rotorcraft flight training method, associated system and rotorcraft

A method for testing a hybrid power plant equipping a rotary-wing aircraft comprising at least one lift rotor, the hybrid power plant being configured to rotate the at least one lift rotor, the hybrid power plant comprising at least one heat engine configured to rotate the at least one lift rotor; and at least one electric motor supplied with electrical energy by at least one electrical power source, the at least one electric motor being configured to rotate the at least one lift rotor at least when at least one of the at least one heat engine fails.

Method for testing a hybrid drive system on an aircraft, associated computer program and aircraft

A device for monitoring an available thrust margin of an anti-torque member of a rotorcraft as a function of flight conditions, said rotorcraft comprising a power plant driving at least one main rotor participating at least in the lift of said rotorcraft, said anti-torque member participating in the control of the yaw movements of said rotorcraft.

Thrust margin monitoring device for rotorcraft, rotorcraft and corresponding method

A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.

Method and a device for assisting the piloting of a hybrid rotorcraft having a lift rotor and at least one propulsion rotor generating thrust

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the 'speed of rotation'. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the 'current derivative and automatically stopping the engine when the current derivative changes sign.

Method for stopping an engine in overspeed, and associated system and rotorcraft

A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Method of driving a main rotor of a rotorcraft in the context of simulating a failure of one of the engnes of the rotorcraft

A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a 'ready to engage' state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.

Device and a method of controlling engagement between the engine and a main power transmission gearbox of an aircraft

A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch maneuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Method of driving a main rotor of a rotorcraft in the context of simulating a failure of one of the engines of the rotorcraft

A method of stopping an overspeeding engine () of a rotorcraft (). A protection device stops the overspeeding engine () on condition of a comparison between a mechanical power requirement () of the rotorcraft () and a predefined power threshold (). Stopping of the overspeeding engine () is authorized by the protection device () on condition that said mechanical power requirement () is identified as being less than or equal to the predefined power threshold (). The mechanical power requirement () of the rotorcraft () is calculated on the basis of at least one current or anticipated value for the opposing torque () of a main rotor () of the rotorcraft.

Growing community of inventors

Salon de Provence, France

Guillaume Dumur