№ |
Specification |
Modification 1 (truncated configuration) |
Modification 2 (full set) |
1 |
Assembled weight (without a payload), kg |
1,8 |
2,3 |
2 |
Maximum weight of a payload, kg |
4.2 kg |
3.7 kg |
3 |
Maximum weight including а payload, kg |
6 kg |
4 |
Dimensions folded (with separation system locked), mm |
100х100х340,5
(100x100x376,5 with Tuna Can) |
5 |
Available volume for a payload, mm |
95х95х180 (~2U) |
6 |
Radiation protection |
aluminum sheet 1.2 mm |
7 |
Available supply for a payload |
stabilized 3,3…12 В / 2 А,
unstabilized 7…8,4 В / 2А |
8 |
Payload average power at LEO (specified for a specific orbit), W |
2 |
9 |
Available maximum output of a payload (specified for a specific orbit), W |
15 |
10 |
Storage battery capacity, W*h |
50 |
11 |
Battery type |
Li-ion 2S 7200 mAh |
12 |
Number of solar panels, pcs. |
up to 12 (silicon) |
13 |
Peak output produced on 1 solar panel in LEO, W |
at least 1 |
14 |
Onboard interface |
CAN |
15 |
Payload interface |
CAN / UART / SPI, others on request |
16 |
Low-speed radio channel frequency, MHz |
435-438 |
17 |
Data transmission speed through low-speed radio channel, bit/s |
2400, 9600, 57600 |
18 |
High-speed transmitter frequency, GHz |
- |
10,45-10,5 |
19 |
High-speed radio channel data rate, Mbit/s |
- |
up to 250 |
20 |
Radio command channel signal modulation type |
frequency |
21 |
Type of modulation of a high-speed radio channel signal |
- |
phase |
22 |
Antenna type of low-speed radio channel |
turnstile |
23 |
Antenna type of high-speed radio channel |
- |
antenna array |
24 |
Maximum transmitter power, dBm |
30…32 |
25 |
Orientation system |
magnetometers,
solar sensors,
horizon sensor,
inertial module |
magnetometers,
solar sensors,
horizon sensor,
inertial module GNSS receiver |
26 |
Attitude support system |
magnetic coils |
magnetic coils,
flywheels |
27 |
Stabilization modes |
B-Dot |
B-Dot
triaxial orientation:
- in the sun,
- at nadir,
- to a point on Earth |
28 |
Orientation accuracy |
up to 1˚ |
29 |
Attitude system accuracy |
- |
up to 1˚ |
30 |
Additionally |
2 MP technology camera,
Software update via low-speed radio channel,
Management of small spacecraft for 1 year after launch |
31 |
Documentation |
Passport,
Manual |