Problem considered is that of finding perturbation solutions of differential equations of motion of vehicle moving under constant low-thrust acceleration; vehicle is initially moving in circular Kepler orbit; second-order perturbation theory is derived for vehicle departing from circular orbit; trajectory is produced by thrust vector maintained at constant, but arbitrarily chosen, angle with respect to radius vector; graphical results of second-order theory are presented which show representative low-thrust trajectories.


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    Title :

    Perturbation solutions for low-thrust rocket trajectories


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 3 , n 10


    Publication date :

    1965


    Size :

    3 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English