Preliminary Design of the Radiation Protection for the small satellite ROMEO in the lower Medium Earth Orbit
- Paper number
IAC-22,B4,IP,46,x73564
- Author
Mr. Thorben Löffler, Germany, IRS, University of Stuttgart
- Coauthor
Mr. Jonas Burgdorf, Germany, IRS, University of Stuttgart
- Coauthor
Mr. Jérôme Hildebrandt, Germany, IRS, University of Stuttgart
- Coauthor
Mr. Alexandros Vikas, Germany, IRS, University of Stuttgart
- Coauthor
Mrs. Susann Pätschke, Germany, Institute of Space Systems, University of Stuttgart
- Coauthor
Mrs. Lena Bötsch-Zavřel, Germany, IRS, University of Stuttgart
- Coauthor
Mr. Cedric Holeczek, Germany, KSat e.V.
- Coauthor
Mr. Patrick Largent, Germany, University of Stuttgart
- Coauthor
Ms. Marlin Kanzow, Germany, University of Stuttgart
- Coauthor
Mr. Jona Petri, Germany, Institute of Space Systems, University of Stuttgart
- Coauthor
Dr. Michael Lengowski, Germany, Institute of Space Systems, University of Stuttgart
- Coauthor
Prof. Sabine Klinkner, Germany, IRS, University of Stuttgart
- Year
2022
- Abstract
The Medium Earth Orbit regimes, characterized by harsh radiation environments, are a target of the University of Stuttgart’s Institute of Space Systems satellite “Research and Observation in Medium Earth Orbit” ROMEO. The aim of the ROMEO mission is to demonstrate a cost-efficient solution to access and operate in the lower MEO. Utilizing MEO can help to reduce the growing density of LEO spacecraft. Additionally, satellites in higher orbits achieve prolonged visibility times over targets and ground-stations, which lowers the overall number of satellites necessary in constellations. However, in contrast to the relatively protected lower Earth orbits, the MEO environment is particularly dangerous for electronic components, because of high-energetic protons and electrons, which are trapped in the Van Allen Radiation Belts. In comparison to LEO missions, this leads to a multiple of the annual Total Ionizing Dose (TID) levels received, and a significant higher probability of Single Event Effects (SEE). As the demonstration spacecraft’s apogee will be raised up to 3000 km altitude, the platform has the chance to demonstrate radiation tolerant systems including commercial off-the-shelf (COTS) and NewSpace components. This paper sums up the radiation mitigation strategies used for the small satellite platform on mission-, system-, and component-level. The goal of those strategies is to increase the reliability of the satellite bus. Suitable NewSpace components with increased radiation protection are selected by a market study. Additionally, a budget for shielding mass is analysed. This paper suggests a system design with single failure tolerance and independent redundant power distribution systems. \\
- Abstract document
- Manuscript document
IAC-22,B4,IP,46,x73564.pdf (🔒 authorized access only).
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