CubeSat Main Bus Unit "SatBus 2C1"

CubeSat Command & Service Modules
CubeSat Main Bus Unit "SatBus 2C1"

Main Bus Unit “SatBus 2C1”

Basic Price € 4950

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

  • on-board computer (OBC)
  • attitude determination & control system (ADCS)

It is tailored for small sized spacecrafts and complies with the CubeSat standard. Architecture is based on a high-performance, low power consumption ARM 32-bit Cortex™ M4 CPU core which is implemented in each of the 2 subsystems.

System features a Floating Point Unit (FPU) and a full set of DSP instructions, software package includes a FreeRTOS Kernel and necessary software libraries.

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Features

  • Clock speed up to 168 MHz (configurable)
  • 192 KB of RAM
  • 1 MB FLASH memory
  • 128 MB of external NOR-flash for mission data storage (two separate chips of 64 MB each)
  • FreeRTOS operating system
  • Board support package with all device drivers and USB Virtual COM
  • RFS – record based file system
  • Cubesat Space Protocol (CSP) and CSP KISS protocol support
  • RTC – real time clock
  • Debug interfaces: USB/SWD
  • 104-pin SAMTEC stack and PicoBlade™ 1.25 mm pitch interfacing connectors
  • Main system bus: CAN (ISO 11898-2:2003 compliant)
  • Temperature tolerance: -40 °C to 85 °C
  • PCB: Gold plated FR-4 (IPC-6012B)
  • IPC – A600H class 3 assembly, soldering per ESA specification ECSS-Q-70-08
  • Dimensions: 95.9 x 90.2 x 14 mm
  • Mass: 50 g

OBC

  • 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

ADCS

  • External interfaces: I2C, UART, SPI, CAN
  • PWM H-Bridge 3.3V/5V power outputs with current measurement
  • On-board sensors: 3 axis magnetometer, 3 axis gyroscope, 3 axis 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