Abstract
This paper provides a mission analysis and systems design of a pole-sitter mission, i.e. a spacecraft that is continuously above an Earth Pole, and can provide real-time, continuous and hemispherical coverage of the polar regions. Two different propulsion strategies are proposed: solar electric propulsion (SEP) and SEP hybridized with a solar sail. For both, minimum-propellant pole-sitter orbits and transfers are designed, assuming Soyuz and Ariane 5 launch options. A mass budget analysis allows for a trade-off between mission lifetime and payload mass capacity (up to 7 years for 100 kg), and candidate payloads for a range of applications are investigated.
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Acknowledgments
This work was funded by the European Research Council, as part of project 227571 VISIONSPACE. The authors thank Dr. Victor M. Becerra, of the School of Systems Engineering, University of Reading, Reading, UK for providing the software PSOPT freely, as well as advices on its use.
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Ceriotti, M., Heiligers, J., McInnes, C.R. (2014). Design and Trade-offs of a Pole-Sitter Mission. In: Macdonald, M. (eds) Advances in Solar Sailing. Springer Praxis Books(). Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-34907-2_20
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DOI: https://doi.org/10.1007/978-3-642-34907-2_20
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