Abstract: The orbit injection of allelectric propulsion satellite is a typical low thrust multirevolution orbit optimal problem. Due to the small acceleration and the large number of revolutions, it is difficult to solve the optimal theoretical solution. In order to solve this problem, the indirect method model of allelectric propulsion satellite orbit optimization was established by using the optimal control theory, and the problem of the orbital optimization was transformed into the twopoint boundary value problem which can be solved by guessing the initial costate variable. A large thrust problem was solved by combining the evolutionary algorithm and the sequential quadratic programming. With the help of homotopic approach, the small thrust problem was solved by gradually reducing the thrust. The simulation shows that the thrust homotopic method can effectively solve the trajectory optimal of geostationary allelectric propulsion satellites with up to hundreds of revolutions by dozens of thrust reductions.

Key words: allelectric propulsion satellite, low thrust, orbit optimization, homotopic approach, covariate variable