CubeSat Main Bus Unit "SatBus 3C1"

CubeSat Command & Service Modules
CubeSat Main Bus Unit "SatBus 3C1"

Main Bus Unit “SatBus 3C1”

Basic Price € 9450

Is a highly integrated small satellite main bus unit containing advanced functionality combining:

  • an on-board computer (OBC)
  • attitude determination & control system (ADCS) and
  • communication system (COMM)

Unit is optimized for small sized spacecrafts and complies with the CubeSat standard. It is designed to save customer’s time and budget, minimize required integration effort and effectively increase volume for payload as well as overall system reliability through harmonized hardware.

SatBus 3C1 architecture is based on a high-performance, low power consumption ARM 32-bit Cortex™ M4 CPU core. All subsystems are provided with standard software package that includes a FreeRTOS Kernel and necessary software libraries for peripherals.

Separate combinations coupling individual subsystems are available for optimal design of the spacecraft.

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  • FreeRTOS operating system
  • Board support package with all device drivers
  • RFS – record based file system
  • Cubesat Space Protocol (CSP) and CSP KISS protocol support
  • RTC – real time clock
  • Debug interfaces: USB/SWD
  • Main system bus: CAN (ISO 11898-2:2003 compliant)
  • Temperature tolerance: -40 to 85 °C
  • PCB: Gold plated FR-4 (IPC-6012B)
  • IPC – A600H class 3 assembly, soldering per ESA specification ECSS-Q-70-08
  • 104 pin SAMTEC stack and PicoBlade™ 1.25 mm interfacing connectors
  • Dimensions: 95.9 x 90.2 x 17.1 mm
  • Mass: 55 g


  • Clock speed up to 168 MHz (configurable)
  • 192 KBytes of RAM
  • 1 MB FLASH memory
  • 128 MB of external NOR-flash for mission data storage (two separate chips of 64 MB each)
  • USB Virtual COM
  • External interfaces: I2C, UART, CAN, GPIO/ADC
  • Switchable power supply outputs with voltage and current measurement functions
  • In-orbit firmware update function
  • Mission planner with time scheduled script/task execution support
  • Telemetry logging


  • Clock speed up to 168 MHz (configurable)
  • 192 KB of RAM
  • 1 MB FLASH memory
  • 64 MB of external NOR-flash for mission data storage
  • 256 KB of radiation tolerant Ferromagnetic RAM up 180 KB/s write speed
  • External interfaces: I2C, UART, SPI, CAN
  • PWM H-Bridge 3.3V/5V power outputs with current measurement
  • On-board sensors: magnetometer, gyroscopes, accelerometer
  • Unscented Kalman Filter for attitude estimation
  • SGP4 orbit propagator, magnetic field and sun reference vector modelling
  • De-tumbling, nadir and inertial pointing control modes
  • Attitude estimation accuracy is ± 1° when using external NanoAvionics sun sensors
  • In-orbit firmware update function


  • Clock speed up to 72 MHz (configurable)
  • 48 KB of RAM
  • 256 KB FLASH memory
  • 64 MB of external NOR-FLASH for data storage connected over SPI
  • External interfaces: UART and CAN
  • Frequency range: 433-440 MHz (Half Duplex)
  • Baud rate: 9600
  • Rx sensitivity in 9600 baud: -120 dBm
  • Maximum RF output power: +33 dBm (2 W)
  • Supported modulations: 2-FSK (including G3RUH subtype), 2-GFSK, 4-FSK, 4-GFSK, MSK, OOK
  • Compatibility with AX.25 radio packet protocol
  • Transmitter over-temperature protection
  • In-orbit re-configuration

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