A hybrid/electric propulsion architecture for a multi-rotor rotary wing aircraft, including an electricity generator driven by an internal combustion engine, and configured to operate in motor mode, a rectifier configured to convert an alternating current delivered by the electricity generator into direct current, an electrical network including a high voltage direct current (HVDC) bus, electrical energy storage means connected to the electrical network, during electrical energy regeneration on the HVDC bus, depending on the state of charge of the storage means: the storage means are configured to recover electrical energy, the storage means and the rectifier are configured to recover electrical energy, and the electricity generator operating in motor mode is configured to recover electrical energy.
ARCHITECTURE PROPULSIVE HYBRIDE-ÉLECTRIQUE ET PROCÉDÉ DE DISSIPATION D'ÉNERGIE ÉLECTRIQUE DANS UNE TELLE ARCHITECTURE
HYBRID/ELECTRIC PROPULSION ARCHITECTURE AND METHOD FOR DISSIPATING ELECTRICAL ENERGY IN SUCH AN ARCHITECTURE
HYBRIDE/ELEKTRISCHE ANTRIEBSARCHITEKTUR UND VERFAHREN ZUR ABLEITUNG ELEKTRISCHER ENERGIE IN EINER SOLCHEN ARCHITEKTUR
2022-01-05
Patent
Electronic Resource
French
European Patent Office | 2021
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|European Patent Office | 2017
|ARCHITECTURE PROPULSIVE HYBRIDE ET AÉRONEF COMPORTANT UNE TELLE ARCHITECTURE
European Patent Office | 2021
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