This paper describes the mission analysis and design of the 'Hevelius - Lunar Microsatellite Mission'. The main goal of the overall mission is to place a net-lander on the far side of the Moon to perform some scientific experiments. Two different satellites have been designed to achieve this objective: a microsatellite orbiter to support the net-lander and a carrier spacecraft to transport the net-lander. An L2 Halo orbit has been selected for the orbiter in order to have a constant communication link between the landers and the Earth. The invariant manifolds of the Earth-Moon system have been used to design a low cost transfer trajectory to the L2 Halo orbit. Prior to the beginning of landing operations the carrier is parked into a frozen orbit after a WSB transfer. Finally the descent and landing phases have been designed in order to accomplish the final goals. The whole mission analysis and design process has been driven by the need for a low cost and low risk mission.
|Number of pages||10|
|Publication status||Published - 17 Oct 2005|
|Event||56th International Astronautical Congress - Fukuoka, Japan|
Duration: 17 Oct 2005 → 21 Oct 2005
|Conference||56th International Astronautical Congress|
|Period||17/10/05 → 21/10/05|
- far side of the moon
- microsatellite orbiter
- halo orbit
- frozen orbit
Scarì, E., Ceriotti, M., Colombo, C., & Vasile, M. (2005). Mission analysis of Hevelius-lunar microsatellite mission. IAC-05-B.5.2. Paper presented at 56th International Astronautical Congress, Fukuoka, Japan, .