Voltaero

Airbus Group Sas

European Aeronautic Defence and Space Company Eads France

Didier Esteyne

Emmanuel Joubert

Hichem Smaoui

Jean Botti

Bruno Rechain

Charles Nespoulous

Hichem Smaou

An engine () is provided with a powertrain including a heat engine () and an output shaft (A), an electric motor (), a battery () for supplying the electric motor () and a propeller propulsion system including a propeller () and a propeller shaft (A), to which the propeller () is coupled. The powertrain includes a system of clutches (E, E, E, E) designed for different configurations to selectively drive the propeller using the heat engine without transmission of the rotation of the electric motor to the propeller; using the electric motor without transmission of the rotation of the heat engine to the propeller; using combined transmission of the rotation of the heat engine and the rotation of the electric motor to the propeller. The electric motor includes a stator and a rotor mounted for rotation about a shaft rigidly connected, or capable of being coupled, to the propeller shaft.

Machine comprising a hybrid powertrain and corresponding control method

The machine, such as an aircraft, is provided with a powertrain which comprises a vaned propulsion system (), and a thermal drive system (), including a first thermal engine (A) and a second thermal engine (B), which is configured to allow the vaned propulsion system () to be driven. The powertrain also includes an electric drive system () which allows the vaned propulsion system () to be driven, an electrical power supply system () including a battery () which allows the electric drive system () to be supplied with power. A clutch system () allows any or each of the thermal engines (A,B) to be engaged in order to drive the vaned propulsion system (), the clutch system () also being configured to allow any or each of the thermal engines (A,B) to be disengaged from the vaned propulsion system ().

An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

Electrical power supply device for aircraft with electric propulsion

Growing community of inventors

Saujon, France

Didier Esteyne