Analytic solutions are determined for optimum correction of all 6 elements of elliptic satellite orbits with low-thrust, power-limited propulsion systems; optimum direction and magnitude of thrust are determined as functions of time so as to minimize fuel required to rendezvous in given time or to minimize fuel required for station keeping in presence of known perturbations; solutions obtained are divided into 2 classes, depending on whether rendezvous requires few or many revolutions; in latter case, simple analytic solutions are obtained by neglecting short-period perturbations.
Optimum low-thrust rendezvous and station keeping
AIAA J
AIAA Journal ; 2 , n 7
1964
6 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Optimum low-thrust rendezvous and station keeping
AIAA | 1964
|OPTIMUM LOW-THRUST RENDEZVOUS AND STATION-KEEPING
AIAA | 1963
|Optimum Low-Thrust Rendezvous and Station Keeping
AIAA | 2003
|mment on ""Optimum Low-Thrust Rendezvous""
AIAA | 1977
|