Earth-Affecting Solar Causes Observatory (EASCO): a mission at the Sun-Earth L5

Publication: Research - peer-reviewConference article – Annual report year: 2011

  • Author: Gopalswamy, Nat

    NASA Goddard Space Flight Center

  • Author: Davila, Joseph M.

    NASA Goddard Space Flight Center

  • Author: Auchère, Frédéric

    Universite Paris-Sud

  • Author: Schou, Jesper

    Stanford University

  • Author: Korendyke, Clarence M.

    Naval Research Laboratory

  • Author: Shih, Albert

    NASA Goddard Space Flight Center

  • Author: Johnston, Janet C.

    Naval Research Laboratory

  • Author: MacDowall, Robert J.

    NASA Goddard Space Flight Center

  • Author: Maksimovic, Milan

    Observatoire de Paris, France

  • Author: Sittler, Edward

    NASA Goddard Space Flight Center

  • Author: Szabo, Adam

    NASA Goddard Space Flight Center

  • Author: Wesenberg, Richard

    NASA Goddard Space Flight Center

  • Author: Vennerstrøm, Susanne

    Solar System Physics, National Space Institute, Technical University of Denmark, Elektrovej, 2800, Kgs. Lyngby, Denmark

  • Author: Heber, Bernd

    Christian Albrechts University

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Coronal mass ejections (CMEs) and corotating interaction regions (CIRs) as well as their source regions are important because of their space weather consequences. The current understanding of CMEs primarily comes from the Solar and Heliospheric Observatory (SOHO) and the Solar Terrestrial Relations Observatory (STEREO) missions, but these missions lacked some key measurements: STEREO did not have a magnetograph; SOHO did not have in-situ magnetometer. SOHO and other imagers such as the Solar Mass Ejection Imager (SMEI) located on the Sun-Earth line are also not well-suited to measure Earth-directed CMEs. The Earth-Affecting Solar Causes Observatory (EASCO) is a proposed mission to be located at the Sun-Earth L5 that overcomes these deficiencies. The mission concept was recently studied at the Mission Design Laboratory (MDL), NASA Goddard Space Flight Center, to see how the mission can be implemented. The study found that the scientific payload (seven remote-sensing and three in-situ instruments) can be readily accommodated and can be launched using an intermediate size vehicle; a hybrid propulsion system consisting of a Xenon ion thruster and hydrazine has been found to be adequate to place the payload at L5. Following a 2-year transfer time, a 4-year operation is considered around the next solar maximum in 2025.
Original languageEnglish
JournalProceedings of SPIE--the international society for optical engineering
Issue number1
Pages (from-to)81480Z
StatePublished - 2011
EventSolar Physics and Space Weather Instrumentation IV -


ConferenceSolar Physics and Space Weather Instrumentation IV
Period01/01/2011 → …
CitationsWeb of Science® Times Cited: 4
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ID: 5873143