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– Ukrainian input in ILWS programO. FEDOROV
Institute of Space Research, Kyiv, UkraineV. KOREPANOV
Lviv Centre of Institute of Space Research, Lviv, UkraineG. LIZUNOV
Institute of Space Research, Kyiv, UkraineYU. YAMPOLSKY
Institute of Radio Astronomy, Kharkiv, Ukraine
Contact: (vakor@isr.lviv.ua / Phone: +380-322-639163)
““Ionosat”. HistoryIonosat”. History
Environment ISS 2008 Space weather, plasma flow around super large body
Potential Remote sensing satellite “Sich-2”
2009 Neutral atmosphere and ionosphere parameters registration
Radioastron Satellite 2009 Radio astronomy, plasma physics
Chibis Microsatellite 2009 Lightning activity
Phobos-Grunt Interplanetary station
2009 Phobos study, space plasma physics
Ionosat 3 microsatellites 2012 Ionosphere, space weather, seismo-ionospheric coupling
Resonance 4 satellite 2012 Mazer effects in magnetosphere
Interball Satellites 1995 Waves in the magnetosphere
Variant Satellite “Sich-1M”
2004 Fields and currents in the inonosphere
Kompas-2 Microsatellite 2005 Ionospheric earthquake precursors
SPACE EXPERIMENTS IN UKRAINE
GMES – oriented ionospheric multi-satellites mission
National Space Agency of Ukraine proposal for First European Space Program
GMES – oriented ionospheric multi-satellites mission
National Space Agency of Ukraine proposal for First European Space Program
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.
1.1. Orbit group is the cluster of three satellites with Orbit group is the cluster of three satellites with identical payload compositionidentical payload composition–– multipoint multipoint measurementsmeasurements
2.2. Satellite group is at the orbit with ~Satellite group is at the orbit with ~ 400 400 kmkm perigeeperigee–– ionospheric projectionospheric project
3.3. The orbit of satellite group is polar but is not solar-The orbit of satellite group is polar but is not solar-synchronous onesynchronous one–– covering of all the Globecovering of all the Globe at all at all range of local timerange of local time
4.4. Mutual distance between satellites changed in the Mutual distance between satellites changed in the range 50 – 3000 kmrange 50 – 3000 km–– multipoint diagnostics of multipoint diagnostics of medium- and big-scale disturbancesmedium- and big-scale disturbances
““IonosatIonosat””:: Main featuresMain features
““IonosatIonosat””:: Orbital clusterOrbital cluster
IIо-1о-1
IIо-2о-2
IoIo-1:-1:liftetimeliftetime = 2 = 2 yearsyears,,perigeeperigee = 400 = 400 kmkm,,apogeeapogee = 780 = 780 kmkm,,inclinationinclination = 82.5 = 82.5
IoIo-2:-2:The sameThe same,,Moving off fromMoving off from IIо-1 о-1 increase up toincrease up to 2000 2000 kmkm
Basic orbit for two space vehicles (SV)Basic orbit for two space vehicles (SV)
““IonosatIonosat””:: Orbital clusterOrbital cluster
Iо-1
Iо-2
IIо-3о-3
has the same operational orbit as Iо-1 and Iо-2, but with another argument of a latitude: ~~ 22
ThirdThird SV:SV:
IIо-1о-1
IIо-2о-2
IIо-3о-3
Group lifetimeGroup lifetime = 2 = 2 yearsyears
ForFor highhigh solarsolar activity periodactivity period::perigeeperigee = 400 = 400 kmkm,,apogeeapogee = 780 = 780 kmkm
Orbit inclinationOrbit inclination = 82.5 = 82.5
Moving off ofMoving off of IIо-1 – о-1 – IIо-2:о-2:up toup to 2000 2000 kmkmIIо-1 – о-1 – IIо-3: о-3: up toup to 3000 3000 kmkm
SV SV positioningpositioning accuracy accuracy – – less thanless than 20 20 mmSV attitude accuracySV attitude accuracy – – less thanless than 10 10SV attitude determination accuracySV attitude determination accuracy – – less thanless than 0.1 0.1
““IonosatIonosat””:: Orbital clusterOrbital cluster
““IonosatIonosat”. ”. Scientific tasksScientific tasks
This is an ionospheric projectThis is an ionospheric project
magnetosphere
DEMETER
hmaxF2
Concentration (cm-3)
Hei
gh
t,
IONOSAT
EXPECTED PARAMETERS OF ELECTROMAGNETIC AND PLASMA DISTURBANCES AT HEIGHTS ~ 400 KM
Particles
Maximal disturbances of neutral particles concentration and temperature
nn ~ 107 cm-3 nn ~ 105 cm-3, Tn ~ 103 К
Maximal disturbances of ion and electron concentration and temperature
ni ~ 105 cm-3
ni ~ 104 cm-3, Te ~ Ti ~ Tn ~103 K
Level of non-isothermicity Te / Ti = 1-4
Fields
Electric field:Quasi-stationary fields, ionic sound,
MHD structuresWhistlers, wide-band electrostatic noise
1- 1000 mV/m, DC-40 kHz
10-100 V/Hz1/2m, 1-200 kHz
Magnetic field:MHD structures
Whistlers:0,1 - 100 nT, DC-100 Hz 10-1 – 10-4 nT,100 Hz-40 kHz
Electric current
Quasi-stationary structures:Whistlers:
1 – 10 A/m2, DC-100 Hz 1 – 200 mV/m, 100 Hz-40 kHz
IDEAL COMPOSITION OF ELECTROMAGNETIC SATELLITESensorsSensors
Neutral gas concentration
Neutral gas temperature (pressure)
Plasma concentration and temperature
Supra-thermal electrons
DC magnetic and electric fields (< 10 Hz)
AC magnetic field. (1 Hz -100 k Hz )
AC electric field (1 Hz-200 kHz)
… and ions
Radio frequency analyzer(100 kHz-15 МHz)
ParametersParameters
Gas kinetic:N, T, Ne, Te, Ti
Distribution function and precipitating particles flux
DC electric and magnetic fields,
field aligned currents E, B, J
ULF-VLF waveforms E, B and total spectrum of plasma waves
I()
ProcessesProcesses
GPS TEС
TasksTasks
CALIBRATION OF MODELS: of upper atmosphere, ionosphere, EMF
Space Weather Terragenic effects EQ precursors
Plasma waves: generation, structure, turbulence
ATMOSPHERE-IONOSPHERE INHOMOGENEITIES: АGW, coherency, turbulence
Magnetic hydrodynamics
of upper atmosphere
Regular course of atmospheric ionospheric parameters
EMF and geomagnetic
activity
Ionospheric emissions and propagation of
radiowaves
Special requirements
• Satellite orientation error ~ 10Satellite orientation error ~ 10• Precision of satellite orientation Precision of satellite orientation
determination determination ~ 0~ 0.1.1• Precision of satellite position determination Precision of satellite position determination
~~ 20 20 mm• Very high requirements to the measurement Very high requirements to the measurement
synchronization at all three satellitessynchronization at all three satellites• Wide range of sampling frequencies: from Wide range of sampling frequencies: from
100 Hz (100 Hz ( minmin = 160 m) in monitoring = 160 m) in monitoring mode to 100 kHz in burst modemode to 100 kHz in burst mode
Minimized payload model structureSENSOR MEASURED VALUE DESIGNERS
WAVE PROBES
Electric current density J Magnetic field В Electric potential
LC ISR, Lviv
ELECTRIC PROBES Electric potential
LC ISR, Lviv
FLUXGATE MAGNETOMETER
Magnetic field vector B
LC ISR, Lviv
RADIO FREQUENCY ANALYZER RFA
Frequency spectrum of electric field component
CKB PAN
KINETIC PLASMA PARAMETERS SENSOR DN-DE
Neutral component pressure (Pn) Concentration of neutral particles (Nn) Concentration of charged particles (Ni, Ne) Ion and electron temperature (Ti,Te) Temperature of heavy particles (Tz) Velocity of heavy particles (Vz)
ІТМ, Dnipropetrovsk
ENERGETIC PARTICLES SENSOR STEP-E
Flow density and energetic spectrum of superheat particles
Kharkiv University
DATA COLLECTION/ PROCESSING UNIT
LC ISR, Lviv
FGM
G PS
RFA
W P
EP
W P
W PТМ
DN-DE
STEP
IONOSAT on МС2- 8 platform Tentative sensors layout
STEP – energetic particles sensorDN-DE – neutral particles sensorEP – electric probe FGM – flux-gate magnetometerWP – wave probe ТМ – telemetric antennaRFA – radio frequency analyzerradio frequency analyzer GPS – for TEC monitoring
DevicesDevices WeightWeight Power Power cons.cons.
3 3 wave probeswave probes WPWP 0.7 kg0.7 kg 0.5 0.5 WW
Electric probeElectric probe EPEP 0.2 0.2 kgkg 0.2 0.2 WW
Flux-gate magnetometerFlux-gate magnetometer FGMFGM 0.7 kg0.7 kg 0.0.66 WW
Radio frequencyRadio frequency analyzer analyzer RFA RFA 33 kgkg 3 W3 W
Sensor of kinetic parametersSensor of kinetic parameters DN-DE DN-DE 1.07 1.07 kgkg < 2 < 2 WW
EEnergetic particles nergetic particles sensorsensor STEPSTEP--EE 22 kg kg 66 W W
DCPUDCPUBoomsBooms
2 2 kgkg
~ 12 kg~ 12 kg
44 WW
--
TotalTotal:: ~ 22~ 22 kgkg ~ ~ 1166 WW
““IonosatIonosat”. ”. Scientific payloadScientific payload
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
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)
2008-20092008-2009 20092009-20-201010 20201111-2012-2012Decision-making, Decision-making,
sending of sending of invitations, feasibility invitations, feasibility
study. (Stage study. (Stage АА))
Development and manufacturing of the devices, autonomous tests. (Stage (Stage BB))
Assembling, full- scale test and launch. (Stage (Stage CC))
““IonosatIonosat”. ”. Working sheduleWorking shedule
PARTICIPATION PROPOSALS ARE WELCOME
Georgy LizunovGeorgy Lizunov:: liz@ikd.kiev.ualiz@ikd.kiev.ua
Valery KorepanovValery Korepanov:: vakor@isr.lviv.uavakor@isr.lviv.ua
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