In recent years, devices that augment the effective drag area of a satellite have been investigated to shorten a satellite’s residual lifetime after mission operations are completed, removing it from the debris population. With the rising amount of orbital debris around Earth, the risk of impact with operational and defunct satellites significantly increases. Safe navigation in the low Earth orbit environment is becoming increasingly threatened as the number of in-orbit spacecraft continues to grow. The simulations confirm the superiority of the EPF engine based on its significant reduction of the structural mass and validate the application feasibility to orbital maneuvers in LEO. For the continuous thrust, the orbital control problem has been turned into an optimization problem and the optimal fuel consumption is obtained using the combinatorial numerical optimization. For impulsive thrust, the limitation of the battery performance with regard to the effectiveness of the Hohmann transfer is given. The optimal transfer trajectories considering the charging processes of the battery involved in orbital maneuvers are demonstrated. Impulsive and continuous control strategies are considered based on the EPF engine limited by the light/umbra condition and charge time. Besides, the applications of the trajectory-battery integrated design to the specific orbital maneuvers are investigated. The performances of four typical battery cells are assessed to select the suitable cell for the application cases. Based on the mass model that comprises the main components of the engine, the advantages of the electric pump system in terms of the structural mass, addition of total impulse and change in velocity that the engine can provide are demonstrated compared with those of the traditional pressure-gas system. ![]() ![]() This paper proposes a trajectory-battery integrated design of the electric pump-fed (EPF) engine and demonstrates its application feasibility to orbital maneuvers in low-Earth orbit (LEO).
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