Airbus Helicopters

Jean-François Logeais

Michel Jamot

Marc Gazzino

Guillaume Dumur

Jérémy Camus

Mikaël Henaff

Damien Mariotto

Léonard Boudier

Emmanuelle Roggemans

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 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

An electrical architecture for an aircraft having a primary three-phase electrical network powering a transformer-rectifier unit serving to power two secondary DC electrical networks. Each of the two secondary electrical networks includes a contactor electrically connected to a generator-starter. The contactors are linked in pairs to prevent them from being closed simultaneously. The second secondary network powers the generator-starter to start a fuel-burning engine. The first secondary network can be powered by the generator-starter to power electrical components. A secondary voltage of the second secondary electrical network is greater than the voltage of the first secondary electrical network, thus making it possible to optimize the weight of the electrical architecture. The two secondary electrical networks may also be powered from autonomous sources of electricity as a replacement for the primary network to power the generator-starter and the electrical components.

Electrical architecture with paired secondary electrical networks for starting engines of an aircraft

An architecture for a hybrid power plant for driving a rotorcraft rotor (). The rotorcraft is fitted with an electrical energy distribution network () for distributing electrical energy from a management network () that is interposed between the distribution network () and electrical energy sources (). A management computer () takes account of information about the working of a combustion engine () for driving the rotor (), about the working of the electrical energy sources () fitted to the rotorcraft and including an energy store (), a reversible electric machine (), and an electricity generator () engaged with the combustion engine, and about the electrical energy needs of the electricity distribution network (). Electrical energy is distributed selectively by the management computer () via the management circuit () and to the distribution circuit () depending on priorities of maintaining safe flight of the rotorcraft and providing drive assistance to the engine () as produced by the reversible electric machine ().

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Marseilles, France

Jean-François Logeais