The Microsat is developed under the National Space Program of Ukraine to observe dynamic processes in Earth’s ionosphere and run technology experiments in space to test onboard instruments and components of future spacecraft.

Description
Features
Graphs

The spacecraft payload incorporates the Ionosat-Micro scientific equipment set for ionospheric research; some sensors of the Ionosat-Micro are installed on deployable booms of more than 2 meters in length.

The Microsat is developed based on the MS-2 bus that was used for the Sich-2 satellite launched in 2011. 

Satellite Basic Specifications

Mass:

Satellite, kg

Payload, kg

 

~195

~75

Orbit:

Type

Altitude, km

Inclination, deg

Orbital period, minutes

 

Circular sun-synchronous

~668

~98.1

~98.03

Attitude control:

Type

Sensors

Actuators

Attitude control accuracy, deg, not worse than

 

3-axis active

3?axis magnetometer

Magnetorquer,
reaction wheel

5

Active life, years, not less than

3

Payload Basic Specifications

Ionosat-Micro scientific payload

Wave complex MWC:

- Wave probes WP1, WP2, WP3

Measurement of current density,  magnetic field and electric potential in the 0.1 Hz — 40 kHz band

- Electric probe ЕР

Electric potential measurement in DC — 200 kHz band

- Flux gate magnetometer FGM

Magnetic field vector measurement in DC — 1 Hz band,

Dynamic range ±65000 nT,

Resolution 0.01 nT

Neutral particles sensors (NPS):

- sensor of neutral plasma component DN

Measurement of neutral-particle concentration 105 — 1011 cm-3, neutral-particle temperature 600 — 2000 K

- sensors of electronic plasma component DE

Measurement of charged-particle concentration 103 — 108 cm-3, electron temperature 0.1 —1.0 eV

Ion temperature 700 — 2500 К

- NPS electronics module

DN-DE sensor current 10-10 — 10-4 А and sensor temperature measurement

Radiofrequency analyzer RFA

Electric field spectrum measurement in 20 kHz — 15 MHz band

Full electron content meter FECM

20 channels in 1217 — 1265 MHz (L1) and 1565 — 1615 MHz (L2) frequency bands

Data collection/processing unit DCPU

Mass storage capacity 100 GB

 

Small stellar-measurement unit MAIS-B

Accuracy of sensing with reference to inertial coordinate system, sec of arc

Optical axis

About optical axis

 

6

45

Refreshment period, s

0.1

 

Strapdown stellar-inertial unit BAIB-02

Angular rate vector projection measurement range, deg/s

±10

Angular rate vector projection sensing accuracy, deg/h

0.14

Terminal velocity of orientation quaternion drift
(not corrected for MAIS-B measurements), deg/h

0.24

 

X-band high-speed radio link equipment

Data rate, Mbps

320

Modulation

OQPSK

 

Ammonia propulsion system

Thrust, N

0.049

Specific impulse, m/s:

"hot" mode

“cold” mode

 

2500

882

 

Experimental solar arrays

Cell type:

Module 1-1

Modules 1-2 and 2-1

Module 2-2

 

Single junction GaAs/Ge

Triple junction InGaP/GaAs/Ge

Triple junction InGaP/GaAs/Ge

Efficiency (for AM0 conditions), %:

Module 1-1

Modules 1-2 and 2-1

Module 2-2

 

21.5

25

27.5

Power density, W/m2:

Module 1-1

Modules 1-2 and 2-1

Module 2-2

 

263

340

374

 

Experimental battery

Battery type

Li-ion

Nominal capacity, A×h

3

 

Panels with temperature-control coatings

Temperature-control coating type:

White

Black

 

Polyurethane PU-1

Epoxy-polyuretyhane EU-1