The present disclosure provides an aircraft propulsion system (5) including a propeller (12), a motor (28), and a reduction gearbox (16) coupled at an input side to a prime mover (28) and at an output side to the propeller (12). The reduction gearbox (16) is configured to provide a reduction ratio between an input and an output. The reduction gearbox is configured such that the input side rotates in a direction opposite the output side, and the prime mover (28), the motor (28), the propeller (12) and the reduction gearbox (16) are configured such that gyroscopic forces generated by the propeller, the motor, the prime mover and the reduction gearbox during aircraft maneuver and/or propulsion system failures are substantially eliminated.

    本公开提供了一种飞行器推进系统(5),该飞行器推进系统包括推进器(12)、马达(28)和减速齿轮箱(16),该减速齿轮箱在输入侧处联接到原动机(28),并且在输出侧处联接到该推进器(12)。该减速齿轮箱(16)被配置为提供输入与输出之间的减速比。该减速齿轮箱被配置为使得该输入侧沿着与该输出侧相反的方向旋转,并且原动机(28)、马达(28)、推进器(12)和减速齿轮箱(16)被配置为使得该推进器、该马达、该原动机和该减速齿轮箱在飞行器操纵和/或推进系统故障期间所产生的陀螺力基本上被消除。


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    Titel :

    Aircraft propulsion system


    Weitere Titelangaben:

    飞行器推进系统


    Beteiligte:

    Erscheinungsdatum :

    2023-05-23


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

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



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