Several laws are designed for simultaneous control of the orientation of an Earth-pointing spacecraft, the energy stored by counter-rotating flywheels, and the angular momentum of the flywheels and control moment gyroscopes used together as an integrated set of actuators for attitude control. General, nonlinear equations of motion are presented in vector-dyadic form, and used to obtain approximate expressions which are then linearized in preparation for design of control laws that include feedback of flywheel kinetic energy error as a means of compensating for damping exerted by rotor bearings. Two flywheel 'steering laws' are developed such that torque commanded by an attitude control law is achieved while energy is stored or discharged at the required rate. Using the International Space Station as an example, numerical simulations are performed to demonstrate control about a torque equilibrium attitude, and illustrate the benefits of kinetic energy error feedback. Control laws for attitude hold are also developed, and used to show the amount of propellant that can be saved when flywheels assist the CMGs. Nonlinear control laws for large-angle slew maneuvers perform well, but excessive momentum is required to reorient a vehicle like the International Space Station.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Dynamics and Control of Attitude, Power, and Momentum for a Spacecraft Using Flywheels and Control Moment Gyroscopes


    Beteiligte:
    C. M. Roithmayr (Autor:in) / C. D. Karlgaar (Autor:in) / R. R. Kumar (Autor:in) / H. Seywald (Autor:in) / D. M. Bose (Autor:in)

    Erscheinungsdatum :

    2003


    Format / Umfang :

    91 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Dynamics and Control of Attitude, Power, and Momentum for a Spacecraft Using Flywheels and Control Moment Gyroscopes

    Roithmayr, Carlos M. / Karlgaard, Christopher D. / Kumar, Renjith R. et al. | NTRS | 2003



    Integrated Power and Attitude Control with Spacecraft Flywheels and Control Moment Gyroscopes

    Carlos Roithmayr / Christopher Karlgaard / Renjith Kumar et al. | AIAA | 2004


    Integrated Power and Attitude Control for a Spacecraft With Flywheels and Control Moment Gyroscopes (AAS 03-124)

    Roithmayr, C. M. / Karlgaard, C. D. / Kumar, R. R. et al. | British Library Conference Proceedings | 2003