Solar-C (EUVST) is the next Japanese solar physics mission to be developed with significant contributions from US and European countries. The mission carries an EUV imaging spectrometer with slit-jaw imaging system called EUVST (EUV High-Throughput Spectroscopic Telescope) as the mission payload, to take a fundamental step towards answering how the plasma universe is created and evolves and how the Sun influences the Earth and other planets in our solar system. In April 2020, ISAS (Institute of Space and Astronautical Science) of JAXA (Japan Aerospace Exploration Agency) has made the final down-selection for this mission as the 4th in the series of competitively chosen M-class mission to be launched with an Epsilon launch vehicle in mid 2020s. NASA (National Aeronautics and Space Administration) has selected this mission concept for Phase A concept study in September 2019 and is in the process leading to final selection. For European countries, the team has (or is in the process of confirming) confirmed endorsement for hardware contributions to the EUVST from the national agencies. A recent update to the mission instrumentation is to add a UV spectral irradiance monitor capability for EUVST calibration and scientific purpose. This presentation provides the latest status of the mission with an overall description of the mission concept emphasizing on key roles of the mission in heliophysics research from mid 2020s.
Solar-C EUVST (EUV High-Throughput Spectroscopic Telescope) is a solar physics mission concept that was selected as a candidate for JAXA competitive M-class missions in July 2018. The onboard science instrument, EUVST, is an EUV spectrometer with slit-jaw imaging system that will simultaneously observe the solar atmosphere from the photosphere/chromosphere up to the corona with seamless temperature coverage, high spatial resolution, and high throughput for the first time. The mission is designed to provide a conclusive answer to the most fundamental questions in solar physics: how fundamental processes lead to the formation of the solar atmosphere and the solar wind, and how the solar atmosphere becomes unstable, releasing the energy that drives solar flares and eruptions. The entire instrument structure and the primary mirror assembly with scanning and tip-tilt fine pointing capability for the EUVST are being developed in Japan, with spectrograph and slit-jaw imaging hardware and science contributions from US and European countries. The mission will be launched and installed in a sun-synchronous polar orbit by a JAXA Epsilon vehicle in 2025. ISAS/JAXA coordinates the conceptual study activities during the current mission definition phase in collaboration with NAOJ and other universities. The team is currently working towards the JAXA final down-selection expected at the end of 2019, with strong support from US and European colleagues. The paper provides an overall description of the mission concept, key technologies, and the latest status.
Solar-C is a mission designed to answer some of the most important questions in solar physics. Recent progress from missions like Hinode has revealed that the different parts of the solar atmosphere are coupled in fundamental ways and has defined the spatial scales and temperature regimes that need to be observed in order to achieve a comprehensive physical understanding of this coupling. Solar-C will deploy a carefully coordinated suite of three complementary instruments: the Solar Ultra-violet Visible and IR Telescope (SUVIT), the high-throughput EUV Spectroscopic Telescope (EUVST), and an X-ray Imaging Telescope (XIT). The science of Solar-C will greatly advance our understanding of the Sun, of basic physical processes operating throughout the universe, and of how the Sun influences the Earth and other planets in our solar system.
Two mission concepts (plan A: out-of-ecliptic mission and plan B: high resolution spectroscopic mission) have been
studied for the next Japanese-led solar mission Solar-C, which will follow the scientific success of the Hinode mission.
The both mission concepts are concluded as equally important and attractive for the promotion of space solar physics. In
the meantime we also had to make efforts for prioritizing the two options, in order to proceed to next stage of requesting
the launch of Solar-C mission at the earliest opportunity. This paper briefly describes the two mission concepts and the
current status on our efforts for prioritizing the two options. More details are also described for the plan B option as the
first-priority Solar-C mission. The latest report from the Solar-C mission concept studies was documented as "Interim
Report on the Solar-C Mission Concept."
J. Culhane, G. Doschek, T. Watanabe, A. Smith, C. Brown, H. Hara, L. Harra, A. James, K. al Janabi, B. Kent, C. Korendyke, J. Lang, J. Mariska, S. Myers, J. Seely, G. Simnett, J. Tandy, R. Thomas, D. Windt
The ISAS/JAXA Solar-B mission includes an Extreme-UV Imaging Spectrometer (EIS). It detects
photons in the wavelength ranges 17 - 21 nm and 25 - 29 nm which include emission lines from several
highly ionised species that exist at temperatures log T = 4.7, 5.6, 5.8, 5.9 and 6.0 - 7.3 K. Instrument
throughput is increased substantially by the use of multilayer coatings optimized for maximum
reflectance in the two selected wavelength bands. The use of back-illuminated CCDs provides
significantly enhanced quantum efficiency over that previously available from microchannel plate
systems. In this paper we will describe the design and operation of the instrument and present its
performance parameters e.g. spectral and spatial resolution and sensitivity. Preliminary results of recent
calibration measurements will be described. The role of EIS in the Solar-B mission will be illustrated
with reference to the anticipated observing strategy for the first three months of the mission which will be
outlined.
The Extreme-ultraviolet Imaging Spectrometer combines, for the first time, high spectral, spatial and temporal resolution in a satellite based, solar extreme ultraviolet instrument. The instrument optical design consists of a multilayer-coated off- axis paraboloid mirror telescope followed by a toroidal grating spectrometer. The instrument includes thin film aluminum filters to reject longer wavelength solar radiation and employs CCD detectors at the focal plane. The telescope mirror is articulated to allow sampling of a large fraction of the solar surface from a single spacecraft pointing position. Monochromatic images are obtained either by rastering the solar image across the narrow entrance slit or by using a wide slit or slot in place of the slit. Monochromatic images of the region centered on the slot are obtained in a single exposure. Half of each optic is coated to maximize reflectance at 195 angstrom; the other half is coated to maximize reflectance at 270 angstrom. The two EUV wavelength bands were selected to optimize spectroscopic plasma diagnostic capabilities. Particular care was taken to choose wavelength ranges with relatively bright emission lines to obtain precision line of sight and turbulent bulk plasma velocity measurements from observed line profiles. The EIS spectral range contains emission lines formed over a temperature range from approximately 105 - 107 K. The wavelength coverage also includes several density sensitive emission line pairs. These line pairs provide spatial resolution independent density diagnostics at nominal coronal temperatures and densities. Each wavelength band is imaged onto a separate CCD detector. The main EIS instrument characteristics are: wavelength bands -- 180 - 204 angstrom and 250 - 290 angstrom; spectral resolution -- 0.0223 angstrom/pixel (23 - 34 km/second-pixel); slit dimensions -- 4 slits: 1 X 1024 arc- seconds and 50 X 1024 arc-seconds with two positions unspecified as of this writing; fine raster range -- >6 arc-minutes on the sun; coarse raster range -- > 1600 arc- seconds on the sun; largest spatial field of view in a single exposure -- 50 X 1024 arc-seconds; nominal time resolution for active region velocity studies -- 3.4s. The Solar-B satellite is scheduled for launch in August 2005 into a nominal 600 km sun-synchronous orbit.
We report a series of polymers with linear, macrocyclic and hyperbranched structures for electroluminescent (EL) applications. The polymers are polycarbazoles (PC) containing different substituents. The polymers are amorphous and are soluble in common organic solvents such as chloroform, and tetrahydrofuran (THF). High optical quality films were obtained by spin-coating from the polymer solutions of chloroform or THF. All these polymers show strong photoluminescence under a UV-lamp illumination. Single and bilayer EL devices consisting of anode/hole transfer layer/electron transfer layer/cathode have been fabricated and characterized. The effects of polymer structures on the energy levels and EL properties are discussed. The results indicated that macrocyclic oligomers and hyperbranched polymers are new candidates for EL devices.
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