Università La Sapienza di Roma will present several post about Earth-Moon missions with particular emphasis on mission architecture and trajectories.

The AMALIA mission analysis design is highly affected by two major drivers:

• The amount of mass to be released on the lunar surface
• The preference for a low-cost mission

From a mission analysis perspective, the amount of mass that can be released on the Moon surface is a constraint coming from the system design process, to be satisfied with a minimum added mass of propellant to transfer the system from the Earth to the Moon surface. The mission analysis output, in terms of fuel mass, is affected by the launcher performances and the transfer and insertion selected strategies. The AMALIA mission timeline can be split in 5 different mission phases :

• Launch
• Transfer
• Lunar insertion
• Descent and Landing
• Surface operations

The trajectory optimization is considered under some mission constraints, assumed by the team as baseline assessments:

• No weak stability boundary transfer (Belbruno), because of the great duration of the mission (about 90 days) that makes the terrestrial segment (Earth telemetry and telecommand) too expensive;
• no multi staging of the spacecraft (SC), because of the design difficulties;
• Liquid propulsion engines (from 4 to 6 bipropellant engines with a nominal thrust of 400-500 N and a specific impulse of 318-325 s);
• The chosen landing site on the lunar surface is at the center of the visible side of the Moon (latitude of ).