Control system is unique in that neither rate gyros nor inertial platform are used for payload de-spin or sun acquisition; direction cosines to solar vector and to earth's magnetic vector are measured by solar cells and two-axis magnetometer; attitude errors and vehicle rates are electronically computed from sensors and used as inputs for control system; analog simulation indicates that limit cycle errors of approximately plus or minus 1 arcsec about solar vector are achievable.


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    Titel :

    Gyroless solar pointing attitude control system for aerobee sounding rocket


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Hansen, Q.M. (Autor:in) / Gabris, E.A. (Autor:in) / Pearson, M.D. (Autor:in) / Leonard, B.S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1967


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    A Gyroless Solar Pointing Attitude Control System for the Aerobee Sounding Rocket

    Gabris, E. A. / Hansen, Q. M. / Leonard, B. S. et al. | NTRS | 1967



    A GYROLESS SOLAR POINTING ATTITUDE CONTROL SYSTEM FOR THE AEROBEE SOUNDING ROCKET

    HANSEN, Q. / GABRIS, E. / PEARSON, M. et al. | AIAA | 1967


    A Gyroless Solar Pointing Attitude Control System for the Aerobee Sounding Rocket

    Gabris, E. A. / Hansen, Q. M. / Leonard, B. S. et al. | NTRS | 1967