An attitude control system includes one or more control moment gyro pairs, with gyros of individual of the pairs being counter-rotated to rotate the rotation axes of flywheels of the gyros of a gyro pair in opposite direction. The flywheels of a gyro pair may be in paddle configuration, with the rotation axes of the flywheels rotating in the counter-rotation through separate planes as the gyros are rotated. The rotation of the gyros of a gyro pair may be accomplished by coupling both of the gyros to a servo motor with suitable coupling gears, or by using independent servos for each gyro. The counter-rotation of gyros of an individual pair produces a resultant torque about a fixed global axis, such as the axis of a flight vehicle of which the attitude control system is a part. Further control may be accomplished for example by varying rotation speeds of the flywheels.


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    Titel :

    GYROSCOPIC ATTITUDE CONTROL SYSTEM


    Weitere Titelangaben:

    GYROSKOPISCHES LAGEREGELUNGSSYSTEM
    SYSTÈME GYROSCOPIQUE DE CONTRÔLE D'ATTITUDE


    Beteiligte:
    ALA EERO H (Autor:in) / OWAN CHRISTOPHER P (Autor:in)

    Erscheinungsdatum :

    29.12.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64G Raumfahrt , COSMONAUTICS



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