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2012 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis

Abstract [en] : As an orbiter cruising to Jupiter will encounter different plasma environments, variety of spacecraft surface charging is expected. This surface potential can lead to inaccurate and wrong in-situ plasma measurements of on-board sensors, which explain the interest in simulating the charging.In this thesis the spacecraft-plasma interactions for a future mission to Jupiter are modelled with the help of the Spacecraft Plasma Interaction System, taking the case of a Jupiter Ganymede Orbiter (JGO) and a Jupiter Europa Orbiter (JEO) as an archetype for a future mission.It is shown that in solar wind at Earth and Jupiter, spacecraft potentials of about 8 V for the JEO, and 10 V to 11 V for the JGO are expected. Furthermore, at a distance of 15 Jupiter radii from Jupiter, the JGO is expected to charge to an electric potential of 2 V, except in the planetary shadow, where it will charge to a high negative potential of -40 V. Moreover, close to the orbit of Callisto, JGO will charge to 12 V in the sun and to 4.6 V in eclipse, due to a high secondary electron emission yield.

Place, publisher, year, edition, pages: 2012. , 89 p.

Keyword [en] : Physics Chemistry Maths, spacecraft charging, Jupiter Ganymede Orbiter, Jupiter Europa Orbiter, Europa Jupiter System Mission - Laplace, Spacecraft Plasma Interaction System, Jupiter Icy Moon Explorer

Keyword [sv] : Fysik, Kemi, Matematik

Identifiers: URN: urn:nbn:se:ltu:diva-48367Local ID: 5d20be98-d03a-47ea-9449-b025932224acOAI: diva2:1021709

Subject / course: Student thesis, at least 30 credits

Educational program: Space Engineering, master's level

Supervisors : André, NicolasGénot, Vincent

Examiners : Ejemalm, Johnny

Note: Validerat; 20120115 (anonymous)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

Autor: Rudolph, Tobias


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