This system is a stand-alone flight computer and radio pair for small satellite missions, as well as an accompanying ground station. It is designed to be integrated into the standard CubeSat form factor but is not limited to CubeSats, and has an estimated maximum reference mission of a 1000 km orbit. This system enables small satellite development teams to reduce their engineering time costs and focus more on their mission payload. This also enables more people to get into spacecraft development as it lowers the monetary cost of entry and the complexity of building a completely new satellite system. This system has performance and design targets that enable teams to use this system for a variety of missions. The system can downlink telemetry collected from a suite of onboard sensors at a minimum refresh rate of 2 Hz and downlink images taken from an onboard camera at a minimum data rate of 16 kbaud. The flight computer provides ample expansion opportunities for other systems that teams may want to integrate onto their satellite that include serial communication buses, ADCs and DACs, GPIO signals, and voltage rails. This system is able to regulate its own voltage rails, decreasing the dependence on a complicated and discrete power board, and consumes under 10 W under maximum load. This system features two radios, one omnidirectional antenna operating in the UHF band and one directional antenna operating in the S-band. This enables telemetry downlink in any satellite orientation and image downlink when the satellite is pointing at the ground station. This system also features a suite of sensors, including temperature sensing, acceleration sensing, gyroscopic rate sensing, and magnetic field strength sensing to enable the spacecraft to determine, correct, and downlink its spatial orientation, as well as detect hardware faults. It also features a camera which can be used for sun pointing maneuvers or to take pictures of the Earth.