Airbus Helicopters

Eurocopter

Marc Gazzino

Guillaume Dumur

Christian Mercier

Michel Jamot

Jérémy Camus

Jean-François Logeais

Christophe Mouton

Mikaël Henaff

Matthieu Connaulte

Jean-Victor Lapeyre

Pierre-Bertrand Lancelevee

Marie-Laure Hopdjanian

Bernard Faure

Pierre Bertrand Lancelevee

Léonard Boudier

Antonin Prevost

Florian Binard

Hervé Routin

Samuel Certain-Chambault

Jean-Philippe Velayguet

Mathieu Connaulte

An aircraft provided with a power plant provided with at least one combustion engine mechanically connected to a drive system, the drive system comprising two electric machines each connected to the combustion engine by a kinematic chain, the two electric machines being electrically connected to at least one electrical power source. The aircraft comprises a management system controlling at least a mechanical power or an engine torque delivered by each of the two electric machines as a function of a current operating mode, the management system being configured, during a superior operating mode, to control the two electric machines in order for the two electric machines to deliver different and non-zero mechanical powers or engine torques.

Method and aircraft provided with at least one combustion engine and a drive system with at least two electric machines

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

The present invention relates to an aircraft provided with a rotary airfoil, a power plant and an assistance system having an electric motor. The power plant comprises a power transmission box and at least one heat engine. The aircraft includes at least one accessory which is set in motion by a secondary output shaft of the power transmission box. The assistance system is provided with a mechanical connection module having a connection shaft which is connected to the secondary output shaft. A first connection member is connected to said at least one accessory and is connected by a first mechanical link internal to the connection shaft, a second connection member being connected to the electric motor and connected by a second mechanical link internal to the connection shaft.

Rotary wing aircraft provided with a transmission system comprising an emergency electric motor

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 method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation device a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation device, followed by a regulating step for regulating an internal voltage of the electrical power generation device as a function of the first power delivered by the rechargeable electrical energy storage device.

Method of electrically powering an electricity network, and an electrical architecture

A method and system of preparing a drone for takeoff are disclosed. The drone has at least one first control member and at least one second control member that are suitable for being actuated manually by at least one person in charge of preparing the drone for takeoff. The drone also includes a navigation light and at least one anticollision light for generating various mutually different light signals in a predetermined switch-on sequence.

Method of preparing a drone for takeoff, and an associated drone and preparation system

An aircraft of a modular type including: at least one rotor suitable for providing in full or in part propulsion and/or lift for the aircraft; at least one power plant of the combustion engine type or of the electric motor type; a main gearbox, for mechanically transmitting drive torque generated by the at least one power plant to the at least one rotor; and an avionics system for assisting in piloting the aircraft. In accordance with the invention, the avionics system is configured for automatically providing the assistance in piloting the aircraft when the aircraft has a first power plant only or when the aircraft has a first power plant and a second power plant.

Aircraft of a modular type, and a method of preparing such an aircraft for a specific mission

A method and to a device for managing energy of a hybrid power plant of a multi-rotor aircraft during a flight. The hybrid power plant comprises a thermal engine, an electricity generator, and a plurality of electric motors, together with a plurality of electrical energy storage devices. The aircraft has a plurality of rotors driven in rotation by respective electric motors. The flight of the aircraft comprises a takeoff stage, a cruising stage, and a landing stage, the takeoff stage and the landing stage being performed solely while consuming electrical energy. The method enables an electrification ratio Rof the flight to be calculated as a function of the amounts of electrical and thermal energy that are consumed during the takeoff, landing, and cruising stages, thereby limiting the use of the thermal engine to the least possible amount during the cruising stage, and consequently reducing the associated nuisance.

Method and a device for managing the energy of a hybrid power plant of a multi-rotor aircraft

A hybrid power plant () for an aircraft () comprises at least: a hybrid drive system () having a main on-board electricity network () and an auxiliary electricity network (); and a selective adaptation interface () arranged to enable electrical energy to be exchanged selectively between the main and auxiliary electricity networks (). At least one engine and a hybrid drive auxiliary electrical machine () are mechanically connected to a transmission (); said machine () being electrically connected to at least one auxiliary electrical bus () in parallel with at least one auxiliary device for delivering electric charge.

Electrical architecture for a rotary wing aircraft with a hybrid power plant

The invention provides a device and a method for starting at least one turbine engine () fitted to a helicopter. A starter () is fed with electrical energy from an electricity network () including at least one battery () and/or an electrical energy generator member. Discharge members () suitable for providing the starter () with a short-term boost of electrical energy in the form of a high-power pulse are incorporated in the network (). The current pulse is delivered at a determined instant T starting from when the starter () is itself started, and/or from a determined threshold S for the speed and/or the variation in the speed with which the compressor () of the turbine engine () is driven, and/or from detecting D the ignition stage of the turbine engine (), and/or from a manual control.

Device and a method for starting a turbine engine fitted to a helicopter, making use of an electrical energy source that includes discharge booster members

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Marseilles, France

Marc Gazzino