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In this paper, the flight motion model for near-space vehicle with an oblique wing is presented, and the flight control system is developed using dynamic inversion method. Firstly, based on its asymmetry configuration and special aerodynamic characteristic, the six-degree-of-freedom nonlinear equations of flight motion are derived using Newton's second law and law of inertia via considering the influence...
Formation control using feedback linearization is developed in this paper. The purpose of the work is that the relative trajectory between follower and leader is linearized in velocity coordinate system in order to accurately control its dynamic process. Considering not all states of the leader which are necessary for complete linearization can be measured in some cases, both full state feedback and...
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