– 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)

William Liu,

IONOSAT

““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

THANK YOUFOR ATTENTION!

THANK YOUFOR ATTENTION!