Abstract
A technology reference study for a displaced Lagrange point space weather mission is presented. The mission builds on previous concepts, but adopts a strong micro-spacecraft philosophy to deliver a low mass platform and payload which can be accommodated on the DLR/ESA Gossamer-3 technology demonstration mission. A direct escape from Geostationary Transfer Orbit is assumed with the sail deployed after the escape burn. The use of a miniaturized, low mass platform and payload then allows the Gossamer-3 solar sail to potentially double the warning time of space weather events. The mission profile and mass budgets will be presented to achieve these ambitious goals.
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Abbreviations
- a :
-
sail acceleration vector
- n :
-
sail normal vector
- r :
-
sail position vector relative to barycenter (rotating frame)
- r 1 :
-
sail position vector relative to Sun (rotating frame)
- r 2 :
-
sail position vector to Earth (rotating frame)
- U:
-
augmented 3-body potential field
- \( \upalpha \) :
-
sail pitch angle
- \( \upbeta \) :
-
sail lightness number
- \( \eta \) :
-
sail reflectivity
- \( \theta \) :
-
sail cone angle
- \( \upmu \) :
-
three-body mass ratio
- \( \phi \) :
-
sail center-line angle
- \( \varvec\upomega \) :
-
angular velocity of rotating frame of reference
References
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Acknowledgments
CRM and JH acknowledge support from the European Research Council VISIONSPACE project (ERC project 227571).
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© 2014 Springer-Verlag Berlin Heidelberg
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McInnes, C.R. et al. (2014). Gossamer Roadmap Technology Reference Study for a Sub-L1 Space Weather 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_16
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DOI: https://doi.org/10.1007/978-3-642-34907-2_16
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