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

被引:10
|
作者
Gopalswamy, Nat [1 ]
Davila, Joseph M. [1 ]
Auchere, Frederic [2 ]
Schou, Jesper [3 ]
Korendyke, Clarence [4 ]
Shih, Albert [1 ]
Johnston, Janet C. [5 ]
MacDowall, Robert J. [1 ]
Maksimovic, Milan [6 ]
Sittler, Edward [1 ]
Szabo, Adam [1 ]
Wesenberg, Richard [1 ]
Vennerstrom, Suzanne [7 ]
Heber, Bernd [8 ]
机构
[1] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA
[2] Univ Paris 11, CNRS, Inst Astrophys Spatiale, F-91405 Orsay, France
[3] Stanford Univ, Ctr Space Sci & Astrophys, Stanford, CA 94305 USA
[4] Naval Res Lab, Washington, DC 20375 USA
[5] Air Force Res Lab, Hanscom AFB, MA 01731 USA
[6] Univ Paris Meudon, LESIA, Paris, France
[7] Tech Univ Denmark, Natl Space Inst, DK-2100 Copenhagen, Denmark
[8] Univ Kiel, D-24118 Kiel, Germany
关键词
Coronal mass ejections; corotating interaction regions; Sun-Earth L5; solar electric propulsion; helioseismology; coronagraph; heliospheric imager; EASCO mission design;
D O I
10.1117/12.901538
中图分类号
P1 [天文学];
学科分类号
0704 ;
摘要
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.
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页数:12
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