Trajectory optimization for the Hevelius-lunar microsatellite mission

Camilla Colombo, Matteo Ceriotti, Ettore Scarì, Massimiliano Vasile

Research output: Contribution to conferencePaper

1 Citation (Scopus)
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Abstract

In this paper trajectory optimisation for the Hevelius mission is presented. The Hevelius-Lunar Microsatellite Mission - is a multilander mission to the dark side of the Moon, supported by a relay microsatellite, orbiting on a Halo orbit around L2. Three landers, with miniaturized payloads, are transported by a carrier from a LEO to the surface of the Moon, where they perform a semi-hard landing with an airbag system. This paper will present the trajectory optimisation process, focusing, in particular, on the approach employed for Δv manoeuvre optimization. An introduction to the existing methods for trajectory optimization will be presented, subsequently it will be described how these methods have been exploited and originally combined in the Hevelius mission analysis and design.
Original languageEnglish
PagesIAC-05-C1.5.05
Number of pages10
Publication statusPublished - 17 Oct 2005
Event56th International Astronautical Congress - Fukuoka, Japan
Duration: 17 Oct 200521 Oct 2005

Conference

Conference56th International Astronautical Congress
CityFukuoka, Japan
Period17/10/0521/10/05

Keywords

  • dark side of the moon
  • relay microsatellite
  • halo orbit
  • trajectory optimisation
  • hevelius mission analysis

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  • Cite this

    Colombo, C., Ceriotti, M., Scarì, E., & Vasile, M. (2005). Trajectory optimization for the Hevelius-lunar microsatellite mission. IAC-05-C1.5.05. Paper presented at 56th International Astronautical Congress, Fukuoka, Japan, .