The invention 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 assignedto each of the subsystems such that both subsystems can be supplied with electrical energy from the common electrical machine. If a defect occurs in one of the subsystems, the drive system can be designed such that electrical energy from a battery of the non-defective subsystem can be transferred into the defective subsystem by utilising the two stator winding systems.

    本发明涉及一种用于空中行驶工具的具有两个最大程度地彼此独立的子系统的混电驱动系统。所述子系统中的每个配属有共同的电机的定子绕组,从而这两个子系统能够由所述共同的电机以电能进行供给。在所述子系统中的一个中出现故障情况时,所述驱动系统能够如下地设立,使得电能能够从没有故障的子系统的电池通过充分利用这两个定子绕组系统转移到有故障的子系统中。


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    Title :

    AIRCRAFT DRIVE SYSTEM


    Additional title:

    空中行驶工具驱动系统


    Contributors:

    Publication date :

    2021-03-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / F02D CONTROLLING COMBUSTION ENGINES , Steuern oder Regeln von Brennkraftmaschinen / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES



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