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The Solar Orbiter A high-resolution mission to the Sun
and inner heliosphere
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Concept général de la mission
1. Obtenir des résolution spatiales en imagerie 5 fois meilleures qu’auparavant (au périhélie).
1. Observations in-situ de l’Héliosphère interne d’aussi près que 45 rayons solaires (0.21 UA).
1. Observer pour le première fois la surface du soleil ainsi que la couronne à partir d’un point en quasi-corotation avec le soleil.
1. Obtenir des images des régions polaires du Soleil jusqu’à des latitudes de 38° (en fin de mission).
1. Mesures simultanées in-situ et à distance.
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1 AU
0.2-0.3 AU (S. Orb.)
3 RS
extrapolation à partir de l’événement du 03/06/82
N. Vilmer
Mesure du flux de neutrons de basse énergie
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observation mode
data-dump mode
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Les différentes activités à l’ESA:
• « Assessment Study Report » (J.-L. Bougeret, J.-C. Vial) Juillet 2000.
• Payload Working Groups (N. Vilmer, A. Gabriel, M.
Maksimovic) , version finale en prépa.
• ESTEC « Integrated Science & Payload study », dont une étude industrielle par EADS-Astrium, prés. finale le 29 juin 2004
• « Science Definition Team » (A. Gabriel, L. Klein), version de Déc. 2003, rapport final ?
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At the SPC meeting 8 June 2004 :“Solar Orbiter reconfirmed as integral part of Cosmic Vision 2003 – 2013 with a target launch in
Oct 2013 (and no later than May 2015).
The SPC stressed the importance of maintaining a close technological synergy between Solar Orbiter
and Bepi Colombo.”
Réunion du 29 juin 2004 à l’ESTEC
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Conclusions de l’Etude EADS-Astrium
• Study demonstrates that 150 kg payload can be achieved– Pending size reduction of remote sensing instruments and key effect on mass & thermal– Thanks to relaxation of resolution to 150 km @ 0.21 AU– Size reduction and mass containment pave the way for the shortest cruise «ESA Flexible» mission
• The main system issue is the management of the data volume– Manageable at spacecraft level– Critical at system level due to space to ground telemetry bottleneck
• Study allows to clearly highlight and recommend– Instruments interfaces for accommodation on spacecraft– Instruments issues resulting from overall system environment
• Study should be seen as a way – To get a common understanding ESA/science team/industry of
• Instruments requirements • Mission, environment constraints
– To better prepare spacecraft and system design• Avoid overdesign• Issue required level of interface information
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Recommandations du « Science Definition Team »
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4ième version du « Payload definition Document » (15 avril 2005)
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En résumé: il n’y a pas de « point de blocage » pour la mission