A STUDY ON THE OPTIMAL LOW-THRUST ORBIT MANEUVER OF LUNAR SATELLITE

The minimum fuel consumption problem of low thrust orbit maneuver from a hyperbolic orbit to a circular orbit is studied. At first, the problem is divided into two parts: orbit maneuver from a hyperbolic orbit to an elliptic orbit and orbit maneuver from an elliptic orbit to a circular orbit. Then, a genetic algorithm is used to solve the optimization problem in the cases of impulse assumption, low thrust orbit maneuver from a hyperbolic orbit to an elliptic orbit, and low thrust orbit maneuver from an elliptic orbit to a circular orbit with transfer time constraint.