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.
|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|
- dark side of the moon
- relay microsatellite
- halo orbit
- trajectory optimisation
- hevelius mission analysis
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, .