Abstract:

The methods for the optimization of timeenergy in the orbit maneuvering of spacecraft under two indexes, with emphasis on the optimization of near range orbit, are explored. By means of the CW equations, the characteristic velocity is derived for the onorbit servicing spacecraft using a twoimpulse orbit. The numerical calculation shows that EDA can accelerate the convergence of the algorithm, and has good optimal capability. It can also build a macro model for the entire group, getting time and energy relations under the mixed indicators. As a result, an accurate numerical simulation of the optimal indexes in the near range is realized. From the numerical results and comparison between these results, some conclusions of significance are drawn, which  provides reference for future research.

Key words: onorbit servicing spacecraft;time and energy;two impulses orbit maneuver;EDA