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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    Title :

    Gyroless solar pointing attitude control system for aerobee sounding rocket


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Hansen, Q.M. (author) / Gabris, E.A. (author) / Pearson, M.D. (author) / Leonard, B.S. (author)

    Published in:

    Publication date :

    1967


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    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

    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