The invention discloses a split rotor gyroscope stability hysteresis propeller, and relates to the technical field of airspace engines. According to the thought of the invention, the stability and precession of the split rotor gyroscope are different from those of a common gyroscope, when a rotor motor (10) rotates along with a connecting rod (5), generated precession torque acts on a pendulum bob (9), so that the rotating surface of the pendulum bob (9) is separated from the rotating surface of a rotor base (8) to generate an included angle, and the rotor base (8) rotates along with the rotor motor (10); the precession moment firstly acts on the pendulum bob (9) to consume a part and then is transmitted to the rotating shaft of the rotor motor (10), and the precession moment borne by the rotating shaft of the rotor motor (10) is delayed and reduced, so that when the connecting rod (5) rotates in the axial stage (16), a large force is needed to overcome the stability of the gyroscope, and a large upward counter-acting force is generated.

    本发明公开了分体式转子陀螺仪稳定性迟滞推进器,涉及航天发动机技术领域。本发明的思路是分体式转子陀螺仪的稳定性和进动性与普通陀螺仪的稳定性和进动性有差异,当转子电机(10)跟随连杆(5)一起旋转时,产生的进动力矩作用在摆锤(9)上,使摆锤(9)的旋转面与转子基座(8)的旋转面分开,产生夹角,进动力矩先作用在摆锤(9)上消耗一部分,然后才传递到转子电机(10)的旋转轴上,转子电机(10)的旋转轴受到的进动力矩出现延迟和变小,使连杆(5)在轴向阶段(16)旋转时需要较大的力克服陀螺仪的稳定性,从而产生一个较大的向上的反作用力。


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    Title :

    Split type rotor gyroscope stability delaying propeller


    Additional title:

    分体式转子陀螺仪稳定性迟滞推进器


    Contributors:
    ZHANG JING (author)

    Publication date :

    2025-04-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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