Solar orbiter mission and system assessment

Paper number

IAC-06-A3.2.08

Author

Dr. Charles Koeck, EADS Astrium, France

Coauthor

Mr. Frédéric Faye, EADS Astrium, France

Coauthor

Mr. Pascal Régnier, EADS Astrium, France

Coauthor

Mr. Romain Peyrou-Lauga, EADS Astrium, France

Year

2006

Abstract

In the context of parallel competitive assessment studies for the ESA Science Directorate, EADS Astrium was awarded a contract in 2004 to investigate mission and system concepts for the Solar Orbiter Mission, with the objectives to demonstrate the mission technical feasibility, optimise the system design and assess the mission programmatic (planning and costs).
The Solar Orbiter mission (SolO) is part of ESA’s Cosmic Vision science program. The Solar Orbiter spacecraft will explore the innermost regions of the heliosphere from high heliopsheric latitudes. It will reach a distance of 0.23 AU from the Sun and achieve an inclination of 35 degrees with respect to the Sun’s equator. In these areas a series of in-situ and remote sensing measurements will be performed, providing first time in-situ measurements of regions so close to the Sun and at the same time provide arcsec resolution imagery. Additionally, the Solar Orbiter will provide the first ever out-of-the-ecliptic imaging and spectroscopic observations of the Sun’s poles.  More details are provided in the article on the science objectives and the straw man science payload assumed for the spacecraft design.
This paper describes the Solar Orbiter mission and system investigations performed by EADS Astrium in the frame of this 18-month ESA study that ended last year. Two mission profiles have been studied during the assessment; one using solar electric propulsion and one using chemical propulsion. The two scenarios are discussed in this paper together with the respective spacecraft design, but more emphasis is given to the ballistic mission profile which proved to be more attractive with lower technical risks and mission costs. A specific focus is provided on the spacecraft thermal architecture and the interfaces with the science instruments, which are of course essential to the mission success. The strong link to BepiColombo mission through reuse of components will be outlined and specific technology development needs for the Solar Orbiter will be described.

Abstract document

IAC-06-A3.2.08.pdf

Manuscript document

IAC-06-A3.2.08.pdf (🔒 authorized access only).

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