The removal of disabled satellites requires the chaser satellite to perform approach tasks. The uncertainties of chaser inertial parameters and thruster output force affect the control accuracy, which may lead to a collision. In this paper, a modified least square method is proposed to refine the model of the chaser satellite, and then the identified parameters are then applied to the controller to reduce control error. Firstly, an optimal trajectory is planned and then performed in space, after which the state sequences are transmitted to the ground. Next, in order to refine the satellite model, a modified least square method is carried out to identify the modification ratio of thrusters, in which two extra limits are introduced to enhance convergence. One is the maximum fix value per step, the other is the total fix upper limit. Finally, the chaser controller is integrated with the modification value. Simulation results indicate that the proposed method enhances the process of convergence and significantly reduces the remaining error.
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