A Modular AOCS Simulator for the 3U CubeSat ELECTRA: Modeling CubeSat Propulsion Demonstrations

The rapid evolution of CubeSat platforms, particularly within academic and research contexts, requires simulation tools that are modular, intuitive, and adaptable to diverse mission requirements. In the framework of the ELECTRA mission, developed by the CubeSat Team at Politecnico di Torino, the Attitude and Orbit Control Subsystem (AOCS) team has implemented a Matlab/Simulink-based simulator to support system-level design choices and investigate advanced navigation and control algorithms tailored for small satellites. The simulator architecture emphasizes modularity and high-fidelity modeling, enabling accurate representation of orbital dynamics and attitude behavior. Special attention is given to the selection of dynamic models and the integration of guidance, navigation, and control (GNC) algorithms, with a particular focus on orbital maneuvering capabilities. This work presents the simulator configuration and preliminary behavior results, such as in detumbling and inertial pointing phases. These outcomes lay the groundwork for future validation campaigns and rapid prototyping, with the long-term goal of using code-generation to enable the transition from simulation to flight-ready software for onboard implementation.