The SXC6 nanosatellite platform is a set of onboard service systems and structural elements for the development of a small satellite in the CubeSat 6U format. on-board systems (main and backup on-board computing module, main and backup power supply systems, main and backup UHF transmitter, main and backup batteries, on-board network, flywheel unit, X-band transmitter, 2 star sensors, 6 solar sensors, structure, payload development kit).
The payload development kit is a general-purpose microcontroller with an nformation interface library integrated with a platform, API and open circuitry, as well as two single-board Raspberry Pi computers. This architecture allows you to implement your own software on the computing power of the platform or to develop and integrate your own components using proven circuit solutions.
SXC6 platform allows integration of third-party developers payload. The platform provides two radio channels: UHF two-way channel (Earth-Space-Earth) and high-speed channel (Space-Earth) . UHF channel transmits digital information in the range of 430-440 MHZ at a speed of 9600 bps. The high-speed data link operates at up to 10 Mbit/s.
The average orbital power consumption of the payload in low earth orbits not higher than 600 km, while maintaining the solar orientation, is about 15 W. The capacity of available battery is not less than 30 W*h. It is possible to completely de-energize all systems by disconnecting the battery and solar panels from the power bus of the spacecraft. With the help of solar panels, the spacecraft receives at least 15 W of electricity.
Two-way communications with small spacecraft can be provided by the ground complex, f.e. "Zavitok".
Nanosatellites based on the SXC6 platform are compatible with standard automatic transport and launch containers of CubeSat 6U spacecraft.
Assembled, verified, fully tested flight unit with installed and calibrated 3-axis orientation system and GaAs solar panels.
- 6U CubeSat structure – 1 pc.
- On-board computer – 2 pcs.
- Star tracker – 1 pcs.
- Power supply unit – 2 pcs.
- GaAs solar panel (side) – 16 pcs.
- Si solar panel (edge) – 4 pcs
- UHF transceiver – 2 pcs.
- UHF antenna system with service panel and RBF – 2 pcs.
- X-Band transmitter – 1 pc.
- X-Band antenna – 1 pc.
- Reaction wheels module with 4 wheels - 1 pc.
- Sun sensors – 6 pcs.
- ADCS controller option for OBC - 1 pc.
- Payload development kit -1 pc.
- Protection side panels 6U – 4 pcs.
- Protection edge panels 6U – 2 pcs.
- Connection wires set 6U
- Transportation case
- Assembling and verification on manufacturer site
- Set of GaAs solar panels
- 3-axis orientation system including 6 Sun sensors
- Basic functional testing with protocol: PSU cycling, radio channel, electromagnetic angular velocity damping test
- Space qualification tests with approved protocol: vacuum, thermal and mechanical impact tests
- Payload development kit
*Standard modification. Can be changed for particular project.
|Mass assembled (w/o payload)||not more than 6 kg|
|Max mass allowed (w/ payload)||not more than 12 kg|
|Dimensions at rails (w/ deployment system pressed)||100х226,3x366 mm|
|Available volume for payload||not less than 3U+|
|Output voltage||5 В ±0.5 V|
|Output voltage consumption||not more than 3A|
|Available average power consumption of payload on LEO, not more than (to be precised for exact orbit)||8000 mW|
|Sun orientation using deployable solar panels Battery capacity||not less than 79 Wh|
|On-board interface||CAN2.0 B|
|Number of solar panels||28 pcs.|
|Peak capacity made by one solar panel on LEO||not less than 35 W|
|Operating temperature range||-30...+60 °С|
– Digital beacon with systems and payload status
|Radio channel frequency||435-437 MHz (amateur) or 400-401 MHz (commercial|
|Radio channel protocol||AX.25, FEC|
|Radio data||rate 9600 bit/s (default), up to 57600 bit/s|
|X-band frequency||10.3-10.55 GHz (amateur) or 8.0-8.4 GHz (commercial)|
|X-band data||rate Up to 10 Mbit/s|
|Battery type||Li-Ion 2S 5000 mAh|
|Battery rated voltage||7.4 V|
|Max. Battery Charging Current||5A|
|Orientation and Stabilization Algorithms||B-DOT, Sun orientation, nadir, Earth pointing, star pointing|
|Sensors||Star tracker, Sun sensors, GPS, Angular velocity sensor, Magnetometer, temperature sensors|
|Orientation setting accuracy on sunny side||Up to 0.1° using star tracker|
|Orientation control accuracy on sunny side||Up to 0.1° using star tracker|
|Orientation setting accuracy on shadow side||Up to 0.1° using star tracker|
|Orientation control accuracy on shadow side||Up to 0.1° using star tracker|