Achievement of high-accuracy indication of deviation of satellite vehicle from orbit plane about vertical by gyrocompassing techniques requires either extremely tight vehicle control or data handling in stabilized coordinates; paper develops mathematical model and error relationships for latter approach; two configurations, vertical and horizontal damping, are described, and it is shown that former emphasizes LF horizon sensor and gyro errors, whereas latter emphasizes their HF characteristics; systematic error due to earth's oblateness, if uncompensated, may be dominant and can produce over 0. 1° of error of satellite altitudes of 250 nautical mi.


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    Title :

    Orbital gyrocompass heading reference for satellite vehicles


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1965


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :