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IONOSAT

IONOSAT. – Ukrainian input in ILWS program O. FEDOROV Institute of Space Research, Kyiv, Ukraine V. KOREPANOV Lviv Centre of Institute of Space Research, Lviv, Ukraine G. LIZUNOV Institute of Space Research, Kyiv, Ukraine YU. YAMPOLSKY Institute of Radio Astronomy, Kharkiv, Ukraine

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IONOSAT

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  1. IONOSAT – Ukrainian input in ILWS program O. FEDOROV Institute of Space Research, Kyiv, Ukraine V. KOREPANOV Lviv Centre of Institute of Space Research, Lviv, Ukraine G. LIZUNOV Institute of Space Research, Kyiv, Ukraine YU. YAMPOLSKY Institute of Radio Astronomy, Kharkiv, Ukraine Contact: (vakor@isr.lviv.ua / Phone: +380-322-639163)

  2. IONOSAT William Liu,

  3. “Ionosat”. History SPACE EXPERIMENTS IN UKRAINE

  4. IONOSAT experiment GMES – oriented ionospheric multi-satellites mission National Space Agency of Ukraine proposal for First European Space Program

  5. IONOSAT project main tasks • Scientific and methodological substantiation of the efficiency of the LEO satellites use for SW monitoring, corresponding technological realization development and tests. • Systematic study of the dynamic response of the ionosphere to the influences “from above” (solar and geomagnetic activity) and “from below” (meteorological, seismic and technologic processes), seismo-ionospheric coupling. • Synchronous operation with the existing sub-satellite electromagnetic and meteorological polygons. • Calibration of modern prognostic models of quiet and disturbed ionosphere.

  6. “Ionosat”:Main features • Orbit group is the cluster of three satellites with identical payload composition–multipoint measurements • Satellite group is at the orbit with ~ 400 kmperigee–ionospheric project • The orbit of satellite group is polar but is not solar-synchronous one–covering of all the Globeat all range of local time • Mutual distance between satellites changed in the range 50 – 3000 km–multipoint diagnostics of medium- and big-scale disturbances

  7. “Ionosat”:Orbital cluster Basic orbit for two space vehicles (SV) Io-1: liftetime = 2 years, perigee = 400 km, apogee = 780 km, inclination = 82.5 Io-2: The same, Moving off fromIо-1 increase up to 2000 km Iо-1 Iо-2

  8. “Ionosat”:Orbital cluster ThirdSV: has the same operational orbit as Iо-1 andIо-2, but with another argument of a latitude:  ~2 Iо-1 Iо-3 Iо-2

  9. “Ionosat”:Orbital cluster Group lifetime = 2 years Forhighsolaractivity period: perigee = 400 km, apogee = 780 km Orbit inclination = 82.5 Moving off ofIо-1 – Iо-2: up to 2000 km Iо-1 – Iо-3: up to 3000 km Iо-1 Iо-3 Iо-2 SV positioning accuracy – less than 20 m SV attitude accuracy – less than 10 SV attitude determination accuracy – less than 0.1

  10. “Ionosat”. Scientific tasks • This is an ionospheric project magnetosphere DEMETER IONOSAT hmaxF2 Height, Concentration (cm-3)

  11. EXPECTED PARAMETERS OF ELECTROMAGNETIC AND PLASMA DISTURBANCES AT HEIGHTS ~ 400 KM

  12. IDEAL COMPOSITION OF ELECTROMAGNETIC SATELLITE Sensors Parameters Processes Tasks Neutral gas concentration • CALIBRATION OF MODELS: • of upper atmosphere, • ionosphere, • EMF Gas kinetic: N, T, Ne, Te, Ti Regular course of atmospheric ionospheric parameters Neutral gas temperature (pressure) Distribution function and precipitating particles flux Plasma concentration and temperature Magnetic hydrodynamics of upper atmosphere ATMOSPHERE-IONOSPHERE INHOMOGENEITIES: • АGW, • coherency, • turbulence Supra-thermal electrons … and ions DC electric and magnetic fields, field aligned currents E, B, J EMF and geomagnetic activity DC magnetic and electric fields (< 10 Hz) AC magnetic field. (1 Hz -100 k Hz ) • Space Weather • Terragenic effects • EQ precursors ULF-VLF waveforms E, Band total spectrum of plasma waves I() Ionospheric emissions and propagation of radiowaves AC electric field (1Hz-200 kHz) Radio frequency analyzer (100 kHz-15 МHz) Plasma waves: • generation, • structure, • turbulence GPS TEС

  13. Special requirements • Satellite orientation error ~ 10 • Precision of satellite orientation determination ~ 0.1 • Precision of satellite position determination ~ 20 m • Very high requirements to the measurement synchronization at all three satellites • Wide range of sampling frequencies: from 100 Hz ( min= 160 m) in monitoring mode to 100 kHz in burst mode

  14. Minimized payload model structure

  15. IONOSATon МС2-8 platformTentative sensors layout STEP – energetic particles sensor DN-DE – neutral particles sensor EP – electric probe FGM– flux-gate magnetometer WP – wave probe ТМ – telemetric antenna RFA –radio frequency analyzer GPS – for TEC monitoring

  16. “Ionosat”. Scientific payload

  17. DATA COLLECTION AND PROCESSING UNIT • MAIN PARAMETERS: • SciWay interface with data transmission rate up to 50 Мb/s, • 3 ports, • Up to 32 requesters at each port, • 4 GB memory, • consumed power 4 W, • weight < 2kg

  18. EXPECTED INTERNATIONAL COLLABORATION Space support: • CSES (China) • Mazowie (Poland) • Vulkan or Kanopus (Russia) • Other ? Ground support • Ukraine (Kharkiv and Antarctica) • Russia (Kamchatka polygon) • Japan (EMSEV community) • Swiss (COGEAR project) • Norway (University of Tromso)

  19. “Ionosat”. Working shedule PARTICIPATION PROPOSALS ARE WELCOME Georgy Lizunov:liz@ikd.kiev.ua Valery Korepanov:vakor@isr.lviv.ua

  20. THANK YOUFOR ATTENTION!

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