Using Fourier shape-based method for the construction of Moon to Mars transfer orbit

This paper studies the design and optimization method of Moon-Mars transfer trajectory with mixed propulsion technology. Previous researches imply that dividing the mission into three phases according to different three body dynamic system the explorer suffers sequentially can facilitate this design problem. Halo orbits about the Earth-Moon L2 and the Mars-Sun L1 points are chosen to insert to the transfer route, and the associated invariant manifolds are used to decrease the combustion. In the phases of Moon departure and Mars insertion, impulse jet is applied to reduce the required maneuver velocity pulse. In the heliocentric transferring phase, Fourier series are employed as the shape function to approximate the transfer trajectory with low thrust technology. Genetic algorithms with fuel consumption mass ratio as objective function are applied to seek out a less fuel consumption trajectory after sweeping the initial and final time of the interplanetary transfer. Simulation shows Moon-Mars transfer trajectory achieved by above methods consumes less fuel.