Electric propulsion systems, specifically ion thrusters, operate on the principle of electrostatic acceleration of ions to generate thrust. Gridded ion thrusters utilize grids to ionize propellant, typically xenon, and accelerate ions through a potential difference, while Hall-effect thrusters employ a magnetic field to enhance ionization efficiency and thrust generation. Electrostatic ion thrusters, on the other hand, utilize electrostatic fields to accelerate ions, often employing multiple stages of ionization for increased efficiency. Additionally, innovations in power processing units and propellant feed systems have led to increased power efficiency and enhanced propellant utilization. Despite these advancements, challenges remain, including the need for high-power electrical systems, efficient thermal management to dissipate waste heat, and strategies to mitigate spacecraft charging effects during operation. Continued research efforts are focused on addressing these challenges to further optimize the performance and reliability of ion thrusters for rocket propulsion applications.