The disclosure relates to a hybrid-electrical drive system for an aircraft having two subsystems that are largely independent of each other. A stator winding of a common electrical machine is assigned to each of the subsystems such that both subsystems may be supplied with electrical energy from the common electrical machine. If a defect occurs in one of the subsystems, the drive system may be configured such that electrical energy from a battery of the non-defective subsystem may be transferred into the defective subsystem by utilizing the two stator winding systems.
Aircraft drive system
2023-02-21
Patent
Electronic Resource
English
IPC: | H02P CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS , Steuern oder Regeln von elektrischen Motoren, elektrischen Generatoren, dynamoelektrischen Umformern / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / F02B INTERNAL-COMBUSTION PISTON ENGINES , Brennkraftmaschinen mit innerer Verbrennung mit Verdrängerwirkung / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02D CONTROLLING COMBUSTION ENGINES , Steuern oder Regeln von Brennkraftmaschinen |