A satellite attitude control system is usable in the absence of any inertial yaw attitude reference, such as a gyroscope, and in the absence of a pitch bias momentum. Both the roll-yaw rigid body dynamics and the roll-yaw orbit kinematics are modelled. Pitch and roll attitude control are conventional. The model receives inputs from a roll sensor, and roll and yaw torques from reaction wheel monitors. The model produces estimated yaw which controls the spacecraft yaw attitude.


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    Titel :

    Gyroless yaw control system for a three axis stabilized, zero-momentum spacecraft


    Beteiligte:

    Erscheinungsdatum :

    27.04.1993


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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