Global Launcher Trajectory Optimization for Lunar Base Settlement

The problem of a mission to the Moon to set a permanent outpost can be tackled by dividing the journey into three phases: the Earth ascent, the Earth-Moon transfer and the lunar landing. In this paper we present an optimization analysis of Earth ascent trajectories of existing launch vehicles injected into a Low Earth parking orbit. The trajectories are optimized in the neighborhood of a reference guidance profile. The optimization problem is tackled by using a global method, and a single and multiobjective Particle Swarm Optimization algorithm serve the purpose. The final LEO payload mass is the objective function of the single-objective runs. Path constraints and final orbital elements are used as constraints in the process. However, in the multi-objective optimizations, these constraints are used as objectives together with the payload mass. The launchers' mechanical and thermal constraints, and the launch-sites azimuth constraint are taken into account. It is found that the highest payload masses are achieved by Ariane-5 ESC-A, Atlas V 552 and Proton M, with 25, 24 and 23 tons respectively. Such values, together with the use of all the three launchers and a tight schedule, would permit to build a base in 4.5 years. However, a manned launch vehicle is needed in order to guarantee the assembly and sup- port during the building phase. Also, the dedicated development of a heavy-lift launcher will greatly benefit the moon-base construction