A law is 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 all 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 it means of compensating for damping exerted by rotor bearings. Two flywheel 'steering laws' are developed such that torque commanded by all 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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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



    Conference:

    13th AAS/AIAA Space Flight Mechanics Meeting ; 2003 ; Ponce, Puerto Rico


    Publication date :

    2003-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    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

    C. M. Roithmayr / C. D. Karlgaard / R. R. Kumar et al. | NTIS | 2003


    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