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In this paper, in order to control the relative motion for spacecraft formation flying, an optimal sliding mode controller has been proposed. This controller is designed based on the linearized equations of relative motion under two-body dynamics or Hill's equations and applied to nonlinear system that is subjected to external disturbances. Firstly, an augmented system composed of the original system...
The main purpose of the paper is to present sophisticated means to implement Q-guidance scheme in satellite injection missions. Optimality and simplicity of Q-guidance approach makes it appropriate for practical settings of a wide range of launch systems. Calculation of required velocity as a fundamental and inherent concept of Q-guidance implementation for orbital injection missions has been proposed...
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