Electric Propulsion for the Euroluna Nanosatellite
- Paper number
IAC-11,C4,6,7,x11873
- Author
Dr. Carsten Scharlemann, University of Applied Science Wiener Neustadt, Austria
- Coauthor
Mr. Nembo Buldrini, Austria
- Coauthor
Mr. Ivanhoe Vasiljevich, Austria
- Coauthor
Dr. Soeren Rasmussen, Sweden
- Coauthor
Dr. Tor Mortensen, Sweden
- Year
2011
- Abstract
In the context of the Google Lunar X PRIZE competition, aiming for a private team to put a small rover on the Lunar surface, and return video and images from the lunar surface, Euroluna has developed a nanosatellite designed to fulfill such a demanding mission scenario. Since the mission requires several radical new technology concepts Euroluna has opted for a stepwise approach. In the first step Euroluna developed a ~2 kg nanosatellite (double CubeSat) in order to validate several core technologies. One of those is the propulsion system necessary to provide the required ∆v for a transfer from LEO to the Moon. Since no commercially available propulsion system exists which is capable to deliver the required ∆v within the stringent mass, volume, and power limitations of a nanosatellite Euroluna has commissioned the Austrian Institute of Technology (AIT) GmbH to adapt one of their FEEP based propulsion systems for the present task and provide a fully functional system ready for lunch in early 2011. The adapted AIT propulsion system is capable of delivering a constant thrust range of 0.03 – 0.1 mN with an average specific impulse of >4000s and a mass efficiency of ~40%. The development was driven by the mass, volume and power limitations due to its application on a nanosatellite. The PPU was developed by Euroluna and a commercially available neutralizer has been implemented into the nanosatellite in order to prevent electrical biasing of the nanosatellite. The present paper provides an overview of the Euroluna efforts as well as a discussion of the development of the propulsion system. Furthermore, the paper aims at providing a first assessment of the in-space operation of the Euroluna nanosatellite and an assessment of the thruster performance and comparison with its operation during ground testing.
- Abstract document
- Manuscript document
(absent)