Abstract

Context.To meet the scientific objectives of the mission, the Solar Orbiter spacecraft carries a suite of in-situ (IS) and remote sensing (RS) instruments designed for joint operations with inter-instrument communication capabilities. Indeed, previous missions have shown that the Sun (imaged by the RS instruments) and the heliosphere (mainly sampled by the IS instruments) should be considered as an integrated system rather than separate entities. Many of the advances expected from Solar Orbiter rely on this synergistic approach between IS and RS measurements.Aims.Many aspects of hardware development, integration, testing, and operations are common to two or more RS instruments. In this paper, we describe the coordination effort initiated from the early mission phases by the Remote Sensing Working Group. We review the scientific goals and challenges, and give an overview of the technical solutions devised to successfully operate these instruments together.Methods.A major constraint for the RS instruments is the limited telemetry (TM) bandwidth of the Solar Orbiter deep-space mission compared to missions in Earth orbit. Hence, many of the strategies developed to maximise the scientific return from these instruments revolve around the optimisation of TM usage, relying for example on onboard autonomy for data processing, compression, and selection for downlink. The planning process itself has been optimised to alleviate the dynamic nature of the targets, and an inter-instrument communication scheme has been implemented which can be used to autonomously alter the observing modes. We also outline the plans for in-flight cross-calibration, which will be essential to the joint data reduction and analysis.Results.The RS instrument package on Solar Orbiter will carry out comprehensive measurements from the solar interior to the inner heliosphere. Thanks to the close coordination between the instrument teams and the European Space Agency, several challenges specific to the RS suite were identified and addressed in a timely manner.

Highlights

  • Coordination within the remote sensing payload on the Solar Orbiter mission(Affiliations can be found after the references) Received 31 October 2019 / Accepted 22 January 2020

  • Two transits of Mercury in front of the corona will be observable by FSI. These events may become grazing or disc transits depending on the exact launch date and trajectory, in which case they would be observable by Polarimetric and Helioseismic Imager (PHI)/FDT and the highresolution telescopes (SPICE, Extreme Ultraviolet Imager (EUI)/HRI174, EUI/HRILyα)

  • The stars will be observed by Metis before and/or after off-points, provided enough time for repointing to disc centre before the end of the transit through the Metis FOV. It is possible for EUI/HRI174 and EUI/FSI174 to be cross-calibrated with SPectral Imaging of the Coronal Environment (SPICE) using the 102.8 nm line of Fe x

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Summary

Coordination within the remote sensing payload on the Solar Orbiter mission

(Affiliations can be found after the references) Received 31 October 2019 / Accepted 22 January 2020

FOV detector
Instrument EUI Metis PHI SoloHI SPICE STIX
Planet transit
PHI SPICE SoloHI Metis STIX
Instrument and observation configuration
Solar ephemeris data
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