Satellite, with inertia properties within specific range of values, is assumed to be in orbit of small eccentricity; cold-gas jets that are bounded in thrust level supply torques for attitude control; performance criterion in minimum-fuel consumption for reaching desired attitude in given time; Pontryagin's maximum principle is employed to determine characteristics of minimum-fuel, optimal control for linearized motion, and suboptimal, feedback, attitude-control system is developed that is simple and efficient.


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    Title :

    Attitude control of satellite in elliptic orbit


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1967


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Attitude control of a satellite in an elliptic orbit.

    Busch, R. E. / Fluegge-Lotz, I. | NTRS | 1967


    Attitude control of a satellite in an elliptic orbit.

    BUSCH, R. E. / FLUEGGE-LOTZ, I. | AIAA | 1967


    The Attitude Control of a Satellite in an Elliptic Orbit

    R. A. Busch / I. Fluegge-lotz | NTIS | 1966


    The attitude control of a satellite in an elliptic orbit

    Busch, R. A. / Fluegge-Lotz, I. | NTRS | 1966