Mission analysis of Hevelius-lunar microsatellite mission

Ettore Scarì, Matteo Ceriotti, Camilla Colombo, Massimiliano Vasile

Research output: Contribution to conferencePaperpeer-review

36 Downloads (Pure)


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.
Original languageEnglish
Number of pages10
Publication statusPublished - 17 Oct 2005
Event56th International Astronautical Congress - Fukuoka, Japan
Duration: 17 Oct 200521 Oct 2005


Conference56th International Astronautical Congress
CityFukuoka, Japan


  • net-lander
  • far side of the moon
  • microsatellite orbiter
  • halo orbit
  • frozen orbit


Dive into the research topics of 'Mission analysis of Hevelius-lunar microsatellite mission'. Together they form a unique fingerprint.

Cite this