Moon 2016 - Technology Platform for Extraterrestrial Investigations

Abstract

AURORA is ESA’ long term technology program devoted to prepare human exploration missions within the solar system, primarily Mars, the Moon and asteroids. To achieve this goal, it is necessary previously to acquire knowledge and to improve existing European technology level through robotic missions. To accomplish this European road map the Moon appears as attractive platform for first stations, technology test field, experiments and in general for collecting experience. In particular, the German Aerospace Center, DLR, as the biggest engineer center in Germany with a primary role to develop aerospace technologies, is motivated to be prepared also for the AURORA vision. Concentrating on the Moon as a first goal is a middle course to test the palette of technologies defined in ESA’ technology matrix for AURORA. The present paper discuses a flexible concept, which enables to prove and validate different technological goals at a reasonable cost. The proposed reference mission includes a Space-Tug-Vehicle in Moon orbit, transfer the surveillance/relay satellite into low lunar orbit, landing on the Moon with a lander equipped with a rover for miscellaneous challenges and automated return with samples to the Earth. As a path-breaking in this concept, which should guaranties low mission costs, it is intended the application of several technologies like: arc-jet propulsion for lunar satellite attitude control; combined chemical-electrical propulsion for service module of the super orbital velocity automated reentry vehicle; selection of low impulse trajectories; broad Ka–band/ X–band communication system for data transmission; advanced ATJ solar arrays with total surface of 100 m2 as primary energy source and automated rendezvous-docking system, among others. The analysis includes first global mass budgets for the Lunar-Space-Tug-Vehicle and its component modules; energy budgets for subsystems like electric power supply and propellants and delta-velocity budgets for the complete trajectory and its segments. Also are defined the propulsion properties for the different modules. As an option against conventional Earth re-entry with super orbital velocity, it is here analyzed a reentry option with aerobraking maneuver in upper Earth atmosphere.