The disclosure relates to an electric drive system for an aircraft and to a corresponding operating method. The electric drive system includes a multiplicity of electric thrust generators, wherein each electric thrust generator has an electric motor, and a subsystem group including a multiplicity of subsystems. The thrust generators are apportioned unambiguously between the subsystems so that eachsubsystem includes two or more of the thrust generators. Furthermore, a control system for operating the drive system is provided, wherein the control system is configured to operate the drive systemin such a way that, at least in the event that one of the subsystems of the subsystem group is faulty, an overall yawing moment which is composed of the sum of the yawing moments of the thrust generators of each non-faulty subsystem of the subsystem group essentially disappears.

    本发明涉及用于飞机的电驱动系统以及相应的运行方法,其中,所述系统包括多个电推力产生器SZ,其中,每个电推力产生器具有电动马达以及具有多个子系统SUB的子系统组。所述推力产生器被明确地分配给子系统,从而每个子系统包括所述推力产生器中的两个或更多个推力产生器。此外,设置有控制系统用于运行所述驱动系统,所述控制系统设立成,如下地运行所述驱动系统,使得至少对于所述子系统组的子系统中的一个出错的情况,由所述子系统组的每个没有出错的子系统的推力产生器的偏航转矩的总和组成的总偏航转矩基本上消失。


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    Title :

    ELECTRIC DRIVE SYSTEM FOR AN AIRCRAFT WITH A MINIMAL YAWING MOMENT


    Additional title:

    用于具有最小的偏航转矩的飞机的电驱动系统


    Contributors:

    Publication date :

    2020-10-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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