Contemporary research is improving techniques to maneuvers control in the area of spacecraft. In the aspect of further development of investigations, a high-performance strategy of maneuvers control is proposed in the present research to be applicable to deal with a class of the aforementioned spacecrafts. In a word, the main subject behind the research is to realize a high-performance three-dimensional orbital maneuvers to transfer the system under control from the initial orbit to the corresponding final ones, in finite burn, while the referenced trajectories are provided through an optimization approach. It is shown that two sets of actuators such as the reaction thrusters should be handled through the proposed control strategy, as long as the x in connection with the y, z axes are dealt with through low and high-thrust control channels, respectively. It aims the strategy to manage the orbital parameters to be accurately varied with respect to time, in order to complete the procedure of transferring, in finite burn. A series of experiments in association with a number of benchmarks are considered to verify the performance of control strategy, tangibly. The contribution of the research is to organize an integration of the trajectory optimization and the new structure of the control scheme to deal with the orbital maneuvers, in finite burn, where the low and the high-thrust controls are synchronously compounded to present high-performance of the investigated outcomes.
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