A hybrid-electric aircraft system (401) is provided and includes first and second hybrid-electric engines (410, 420), each of which includes an electric motor to drive operations thereof, and a supplemental power unit (SPU (430)). The SPU (430) is configured as a thermal engine paired with a generator and is configured to generate electrical power. The first and second hybrid-electric engines (410, 420) are operable normally and off, respectively, with electrical power generated by the SPU (430) being diverted to the electric motor (421) of the second hybrid-electric engine (420).
POWER MANAGEMENT IN A HYBRID-ELECTRIC PROPULSION SYSTEM DURING SINGLE ENGINE FAILURE AT DESCENT
ENERGIEMANAGEMENT BEI AUSFALL EINES TRIEBWERKS IM SINKFLUG FÜR EIN HYBRID-ELEKTRISCHES ANTRIEBSSYSTEM
GESTION DE PUISSANCE D'UNE PROPULSION HYBRIDE-ÉLECTRIQUE EN CAS DE DÉFAILLANCE D'UN MOTEUR PENDANT DESCENTE
2023-05-03
Patent
Elektronische Ressource
Englisch
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