# Presentation: 035242

## – 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) 

**– ****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)**** **

## William Liu,

## SPACE EXPERIMENTS IN UKRAINE 

| 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**

*IONOSAT*
* **experiment*

## 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.**

## Orbit group is the cluster of three satellites with identical payload composition– multipoint measurements

- Orbit group is the cluster of three satellites with identical payload composition*–**** ******multipoint measurements***
- Satellite group is at the orbit with ~ 400 km perigee*–**** ******ionospheric project***
- The orbit of satellite group is polar but is not solar-synchronous one*–**** ******covering of all the Globe****** ******at all range of  local time***
- Mutual distance between satellites changed in the range 50 – 3000 km*–**** ******multipoint diagnostics of medium- and big-scale disturbances***

**“****Ionosat****”****:**** ****Main features**

## “Ionosat”: Orbital cluster 

**“****Ionosat****”****:**** ****Orbital cluster**** **

- Iо-1

- Iо-2

- Io-1:
- liftetime = 2 years,
- perigee = 400 km,
- apogee = 780 km,
- inclination = 82.5
- Io-2:
- The same,
- Moving off from Iо-1 increase up to 2000 km

**Basic orbit for two space vehicles (SV)**

## “Ionosat”: Orbital cluster 

**“****Ionosat****”****:**** ****Orbital cluster**

- Iо-1

- Iо-2

**I****о-3**

- has the same operational orbit as Iо-1 and Iо-2, but with another argument of a latitude:
************* ******~***** ****2******

**Third**** ****SV:**

## Group lifetime = 2 years

**I****о-1**

**I****о-2**

**I****о-3**

- Group lifetime = 2 years
- For high solar activity period:
- perigee = 400 km,
- apogee = 780 km
- Orbit inclination = 82.5
- Moving off of Iо-1 – Iо-2:
- up to 2000 km
- Iо-1 – Iо-3: up to 3000 km

- SV positioning accuracy – less than 20 m
- SV attitude accuracy – less than 10
- SV attitude determination accuracy – less than 0.1

**“****Ionosat****”****:**** ****Orbital cluster**

## “Ionosat”. Scientific tasks 

**“****Ionosat****”. ****Scientific tasks**** **

* **This is an ionospheric project*

- magnetosphere

**DEMETER**

*h**max**F*2

**Concentration (cm****-3****)**

**Height,**

**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 structures
Whistlers, 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  SATELLITE

**Sensors**

**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 М****Hz****)**

**Parameters**

**Gas kinetic****:**
***N, T, N******e******, T******e******, T******i***

**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*****(********)**

**Processes**

**GPS**

**TE****С**

**Tasks**

**CALIBRATION OF MODELS****:**
** ****of upper atmosphere****,**
** ****ionosphere****,**
** ****EMF**

** ****Space Weather**
** ****Terragenic  effects**
** ****EQ precursors**

**Plasma waves****:**
** ****generation****,**
** ****structure****,**
** ****turbulence**

**ATMOSPHERE-IONOSPHERE INHOMOGENEITIES****:**
** ****А****GW****,**
** ****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 ~ 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**

## Minimized payload model structure

## IONOSAT on МС2- 8 platform Tentative sensors layout

**IONOSAT**** ****on**** МС2-**** ****8**** platform**** ****Tentative 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**

## “Ionosat”. Scientific payload

| Devices | Weight |  | Power cons. |
| --- | --- | --- | --- |
| 3 wave probes WP |  | 0.7 kg |  0.5 W |
| Electric probe EP |  |  0.2 kg |  0.2 W  |
| Flux-gate magnetometer FGM |  |  0.7 kg |  0.6 W |
| Radio frequency analyzer RFA  |  | 3 kg | 3 W |
| Sensor of kinetic parameters DN-DE  |  | 1.07 kg | < 2 W |
| Energetic particles sensor STEP-E |  | 2 kg | 6 W |
| DCPU
Booms |  | 2 kg
~ 12 kg | 4 W
- |
| Total: |  | ~ 22 kg | ~ 16 W |

**“****Ionosat****”. ****Scientific payload**

## DATA COLLECTION AND PROCESSING UNIT 

-  ***MAIN PARAMETERS******:***
-   **SciWay interface with data transmission rate up to **** 50 М****b****/****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)**

## Georgy Lizunov: liz@ikd.kiev.ua

| 2008-2009 | 2009-2010 | 2011-2012 |
| --- | --- | --- |
| Decision-making, sending of invitations, feasibility study.  (Stage А)  | Development and manufacturing of the devices, autonomous tests. (Stage B) 
 | Assembling, full- scale test and launch. (Stage C) 
 |

**“****Ionosat****”. ****Working shedule**

**PARTICIPATION PROPOSALS ARE WELCOME**
*Georgy Lizunov**:*** **_**liz@ikd.kiev.ua**_
*Valery Korepanov**:*** **_**vakor@isr.lviv.ua**_

## THANK YOUFOR ATTENTION!