Abstract:

The optimal design of impulse trajectories is essential in space-assembly and space-succor. A novel algorithm for solving general minimum-fuel N-impulsive orbit maneuver，e.g.orbit transfer and rendezvous, is proposed. The developed algorithm combines a primer vector obtained through the use of a Yamanaka-Ankersen state transition matrix and an interactive optimization approach based on an hp-adaptive pseudospctral method to calculate the N-impulse velocities directly. The approach starts from twoimpulse  calculated by the hp-adaptive pseudospctral method at initial and terminal points，and is checked by satisfying the necessary conditions for the primer vector. By the reference of the obtained primer vector magnitude information, adding initial coast, final coast or a new midimpulse is tried. Provided the number of multiple-impulse N is fixed, its numerical result of the N-impulse velocities and the time can be calculated by the hp-adaptive pseudospctral method. Through the interactive procedure, the optimal N-impulsive orbit maneuvers are designed. The simulation and outcomes demonstrate that the algorithm is fairly robust, quickly converged and able to deal with the optimal design of N-impulse trajectories efficiently and practically.