The invention relates to the technical field of aircrafts, in particular to a small electric actuating mechanism for aircraft attitude control, which comprises a shell, and an input motor, an output shaft and an angle sensor which are mounted on the shell, the input motor drives the output shaft after being decelerated by the straight gear speed reducing mechanism, the bevel gear speed reducing mechanism and the small-tooth-difference planetary speed reducing mechanism in sequence; and the angle sensor is mounted at the tail part of the output shaft. In the invention, the straight gear speed reducing mechanism is arranged in front of the bevel gear speed reducing mechanism, so that the mounting position of the input motor is closer to the center of the actuating mechanism along the direction of the output shaft, and the axial length of the actuating mechanism is obviously reduced, so that the actuating mechanism can meet the mounting requirement of a smaller cylinder under the same output torque.

    本申请涉及飞行器技术领域领域,尤其是涉及一种用于飞行器姿态控制的小型电动执行机构,包括壳体以及安装于壳体上的输入电机、输出轴、角度传感器;且输入电机依次经直齿轮减速机构、锥齿轮减速机构以及少齿差行星减速机构进行减速后驱动输出轴;所述角度传感器安装于输出轴尾部。在本申请中,由于在锥齿轮减速机构前设置了直齿轮减速机构,使输入电机的安装位置更接近执行机构沿输出轴方向的中心,显著地减小了执行机构的轴向长度,以在相同输出扭矩下可以适应更小圆柱形的安装需求。


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    Titel :

    Small electric actuating mechanism for aircraft attitude control


    Weitere Titelangaben:

    一种用于飞行器姿态控制的小型电动执行机构


    Beteiligte:
    TIAN SHENGLI (Autor:in)

    Erscheinungsdatum :

    08.08.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    F16H Getriebe , GEARING / B64C AEROPLANES , Flugzeuge



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