Spacecraft de-tumbling constitutes a pivotal post-deployment process essential for mitigating the destabilizing effects of tumbling. This research delves into the intricate dynamics of spacecraft de-tumbling, employing mathematical models that systematically account for system nonlinearities and the influence of external perturbations. Through numerical simulations, an in-depth analysis of the satellite's behavior is conducted, with a specific focus on the consequential impact of control systems. The study underscores the significance of these control systems in shaping the satellite's orientation, stability, and control. The results reveal the efficacy of a meticulously designed control system model, showcasing its profound influence on the satellite's dynamics. This success underscores the imperative nature of considering such control systems in the design and operational phases of spacecraft in orbit. Furthermore, the paper delves into the systematic evaluation of various perturbations and their effects on the stability of the satellites. These insights derived from the simulations furnish valuable considerations for future satellite missions, enriching the understanding of the intricate interplay between control systems and external influences.