Prototyping of orbit control software for spacecraft formation flying

The rapid increment of satellite constellations in Low Earth Orbit (LEO) has significantly increased the risk of conjunction events with orbital debris. To ensure the safety and sustainability of these missions, there is a critical need for automated flight dynamics solutions that moderate the operational burden on engineers. This thesis presents the development of an integrated flight dynamics software designed for satellite constellations, specifically focusing on orbital control and optimal Collision Avoidance (CA) maneuvers, done in collaboration with Nautilus- Navigation in Space. The research is structured into two primary functional modules. First, an orbital control framework was developed for an in-line close formation mission. This module incorporates a comprehensive Concept of Operations (ConOps) and mission’s phase logic to maintain relative dynamics against natural perturbations. Station-keeping maneuvers were implemented to correct secular drift, ensuring the constellation holds to strict mission geometry requirements. Second, a collision avoidance system was engineered to interface with cataloged and randomly generated space debris. By calculating the probability of collision and determining optimal miss distances, the software executes maneuvers that mitigate risk while minimizing propellant consumption. The software was validated through a simulated high-fidelity mission scenario, demonstrating its ability to maintain formation integrity and navigate complex conjunction environments. The results confirm that the proposed automated flight dynamics system provides a scalable and robust tool to manage close formation missions, ensuring mission longevity and orbital safety in increasingly crowded environments.