Trajectory optimization for the Hevelius-lunar microsatellite mission

Camilla Colombo, Matteo Ceriotti, Ettore Scarì, Massimiliano Vasile

Research output: Contribution to conferencePaper

1 Citation (Scopus)

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.
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

Fingerprint

trajectory optimization
Lunar missions
microsatellites
Trajectories
Moon
moon
hard landing
low Earth orbits
maneuvers
relay
Landing
payloads
halos
Orbits
orbits
optimization

Keywords

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

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, .
Colombo, Camilla ; Ceriotti, Matteo ; Scarì, Ettore ; Vasile, Massimiliano. / Trajectory optimization for the Hevelius-lunar microsatellite mission. Paper presented at 56th International Astronautical Congress, Fukuoka, Japan, .10 p.
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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.",
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Colombo, C, Ceriotti, M, Scarì, E & Vasile, M 2005, 'Trajectory optimization for the Hevelius-lunar microsatellite mission' Paper presented at 56th International Astronautical Congress, Fukuoka, Japan, 17/10/05 - 21/10/05, pp. IAC-05-C1.5.05.

Trajectory optimization for the Hevelius-lunar microsatellite mission. / Colombo, Camilla; Ceriotti, Matteo; Scarì, Ettore; Vasile, Massimiliano.

2005. IAC-05-C1.5.05 Paper presented at 56th International Astronautical Congress, Fukuoka, Japan, .

Research output: Contribution to conferencePaper

TY - CONF

T1 - Trajectory optimization for the Hevelius-lunar microsatellite mission

AU - Colombo, Camilla

AU - Ceriotti, Matteo

AU - Scarì, Ettore

AU - Vasile, Massimiliano

PY - 2005/10/17

Y1 - 2005/10/17

N2 - 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.

AB - 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.

KW - dark side of the moon

KW - relay microsatellite

KW - halo orbit

KW - trajectory optimisation

KW - hevelius mission analysis

M3 - Paper

SP - IAC-05-C1.5.05

ER -

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