The Microsat-M spacecraft is designed for dynamic processes observation in the earth's ionosphere, as well as technological experiments in the space environment.
The spacecraft payload incorporates the Ionosat-Micro scientific equipment complex 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, kg: | |
| - satellite | 195 |
| - payload | 75 |
|
Orbit: - type - orbital altitude , km - inclination, deg |
circular sun-synchronous ~668 ~98.1 |
|
Attitude control: - type - sensors - actuators Orientation accuracy, deg, no worse than
|
3-axis active 3-axis magnetometer magnetorquers, 5 |
|
Design life, years |
3 |
PAYLOAD BASIC SPECIFICATIONS
Ionosat-Micro Scientific Equipment Complex
|
Wave complex MWC: |
|
|
- wave probes WP1, WP2, WP3 |
Measurement of electric current density, magnetic field and electrical potential within frequency range 0.1 Hz — 40 kHz |
|
- electric probe ЕР |
Measurement of electrical potential within frequency range DC — 200 kHz |
|
- fluxgate magnetometer FGM |
Measurement of magnetic field vector within frequency range DC — 1 Hz , Dynamic range ±65000 nT, Resolution 0.01 nT |
|
Particle density analyzer (PDA): |
|
|
- plasma neutral component sensor DN |
Measurement of neutral particle concentration 105…1011 cm-3, neutral particle temperature 600…2000 К |
|
- plasma electronic component sensors DE |
Measurement of charged particle concentration 103 — 108 cm-3, electron temperature 0.1 —1.0 eV Ion temperature 700 — 2500 К |
|
- PDA electronics module |
Measurement of currents in sensors DN-DE 10-10 — 10-4 А and their temperature |
|
Radio frequency analyzer RFA |
Measurement of electric field spectrum within frequency range 20 kHz — 15 MHz |
|
Ionic driftmeter ID-2 |
|
|
Scientific data collection system SDCS |
Mass memory capacity is 100 Gbytes |
Small astromeasuring system SAMS-B
|
Orientation accuracy relative to inertial coordinate system, arcsec: - optical axis - about optical axis |
6 45 |
|
Information updating period, s |
0.1 |
Gimballess stellar inertial unit GSIU-02
|
Angular velocity vector projections measurement range, deg/s |
±10 |
|
Angular velocity vector projections accuracy, deg/h |
0.14 |
|
Maximum orientation quaternion drift rate (without |
0.24 |
X-band high-speed radio link equipment
|
Data transmission rate, Mbit/s |
320 |
|
Modulation type |
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 Three-junction InGaP/GaAs/Ge Three-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 |
|
Specific power, 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 thermal control coatings
|
Type of thermal control coating: - white - black |
Polyurethane PU-1 Epoxy-polyurethane EU-1 |
