1st ACT global trajectory optimization competition: Results found at GMV

Abstract We expose the rationale and methods that our team used to design the trajectory presented to the subject competition, and discuss our results. We identified a candidate EEVEEJSA trajectory that was comprised of (1) a priming EEV phase, (2) a VEE tour to prepare the departure to Jupiter, and (3) a EJSA phase that ended with an almost head-on collision at target perihelion. For every phase, a trajectory was designed that consisted in coast and thrust arcs, and swings by a planet. The design started with the final EJSA phase, and proceeded backwards to the other phases, with terminal conditions imposed by the initial conditions of the next phase. The merging of the three phases produced a feasible mission, which was refined with a local optimizer. The short mission duration (17 years) made possible to add one extra revolution in the Saturn-asteroid orbit to improve slightly the impact conditions and still satisfy the mission duration constraint. The resulting trajectory would impact the target on June 15th, 2039, at a closing speed of 49.1 km/s, after consuming 193.8 kg propellant.