This thesis investigates the design of a deployable and retractable solar panel mechanism intended for CubeSat platforms. Developed in the framework of the ESA in orbit demonstration mission SROC (Space Rider Observer Cubesat), this equipment aims to allow in-orbit reconfiguration of the solar panels in order to enable docking and retrieval operations. The work focuses on the development of an integrated mechanical and electrical solution capable of providing reliable deployment and retraction within the constraints imposed by small satellite architectures. The study begins with the identification of suitable deployment and retraction principles through a comparative assessment of existing mechanisms, leading to the selection of a motorised, spring-assisted architecture.