The goal of this project was to develop a solution for the overheating of CubeSat systems. In the technology RRI is developing, components in the CubeSat will need to be kept in cryogenic temperatures. A cooling solution which meets the size constraints before deployment and the environmental conditions of low earth orbit was required. The final design demonstrates a solution for the cooling of CubeSat components using a deployable radiator. The design meets the size constraints before deployment by stowing away inside the dimensions of the CubeSat. The deployment of the radiator considers the environmental conditions presented by low earth orbit and it expands out to a large surface area for better heat dissipation through radiation.