A hybrid electric system for a rotorcraft can include a first thermal engine (103a), a second thermal engine (103b), and an electrical machine (105). The first thermal engine (103a) can be sized to produce a maximum first thermal engine power that is below a one-or-more-engine-inoperative (OEI) requirement power and the second thermal engine (103b) can be sized to produce a maximum second thermal engine power that is below the OEI requirement power. The electrical machine (105) can be sized to provide at least a remaining power needed to reach the OEI requirement power in an OEI state.
HYBRID ELECTRIC SYSTEMS FOR ROTORCRAFT
ELEKTRISCHE HYBRIDSYSTEME FÜR DREHFLÜGELFLUGZEUG
SYSTÈMES ÉLECTRIQUES HYBRIDES POUR GIRAVION
23.04.2025
Patent
Elektronische Ressource
Englisch