• Sensor must utilize a photovoltaic (PV) cell to detect strikes
  • Sensor must utilize an amplifier chain that conditions the transient response of the PV cell
  • Sensor must digitize the amplifier signal to interface with the microprocessor
  • Sensor microcontroller must be a PIC24FJ256GB210
  • Sensor microcontroller must count radiation strikes and send count to avionics stack via UART
  • Sensor must be within power budget
  • Sensor power supply must be regulated from an unregulated 8.7V supply
  • Sensor PCB must mechanically interface with existing satellite stack
  • Sensor must fit within 3U CubeSat form factor alongside additional satellite components