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.
Perturbation solutions for low-thrust rocket trajectories
AIAA J
AIAA Journal ; 3 , n 10
1965
3 pages
Aufsatz (Zeitschrift)
Englisch
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