Abstract:

A novel rapid method to design optimalfuel interplanetary trajectory for low-thrust propulsion is presented based on normal trajectory approach. A simple twopoint boundary value problem is formulated -usinga non-perturbation normal trajectory, which has the same endpoint time with low-thrust trajectory. The analytic state transition matrix is derived using three independent integrations of normal trajectory, and then the optimal solution of twopoint boundary problem is obtained.

Key words: low-thrust,  , optimal , analytic , solution,  , normal , trajectory,  , optimalfuel,  , twopoint , boundary