A low-thrust efficient strategy for orbit circularization of small satellites

Low-thrust propulsion strategies for orbit circularization of small satellites have gained significant attention in recent years due to their potential to reduce propellant consumption and improve maneuverability. This study investigates the application of continuous low-thrust propulsion for achieving orbit circularization in small satellites. The spacecraft's dynamics are modeled using the Lagrange Planetary Equations, and an optimal control law is developed based on a Hamiltonian formulation. The control strategy includes optimal thrust integration, targeting changes in both the semi-major axis and eccentricity. The proposed control law is validated through highfidelity numerical simulations using STK Astrogator. Propagation is carried out with the High Precision Orbit Propagator (HPOP), which accounts for realistic environmental disturbances. The simulation results demonstrate that the designed low-thrust strategy effectively reduces both maneuver time and the required propellant while achieving successful orbit circularization. This work contributes to the development of efficient, accurate, and operationally feasible low-thrust guidance techniques for future small satellite missions.