Optimization of low thrust trajectories for a synchronous satellite is studied. The payload is at first on an equatorial parking orbit and is to be transferred to an equatorial stationary orbit. The criterion of the optimization is the maximization of payload ratio in a certain transfer time. Technique used is as follows. First, small changes of orbital elements in one revolution are treated with perturbation technique. Second, large changes of them in whole transfer time are given by adding small changes. Third, optimization of trajectories is performed with the variational method. Results show that as a parking orbit an elliptic has the advantage of a circle and that optimal transfer from a circle to a circle is accomplished keeping the orbit circular.
静止衛星打上げのための低推力飛しょう径路の最適化
SA0125072.pdf
(704.96KB)
