A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to receive a torque command and split output power between the electric motor system and the heat engine system. Additionally and/or alternatively, the ECU can be configured to balance a total torque against a second total torque of a second aircraft powerplant.
TORQUE BALANCING FOR HYBRID ELECTRIC PROPULSION SYSTEMS AND AIRCRAFT UTILIZING HYBRID ELECTRIC PROPULSION SYSTEMS
2020-09-03
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
European Patent Office | 2020
|European Patent Office | 2025
|European Patent Office | 2020
|European Patent Office | 2025
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