Skip entry trajectory tracking with consideration of the rotation of the Earth

This paper mainly considers a lunar return skip entry trajectory tracking problem. The flight range and duration time of lunar return entry are rather long, so the effect of the rotation of the Earth should be considered. The guidance dynamics have more nonlinearities and couplings considering the rotation of the Earth, which make the trajectory tracking more difficult. In the existing literature, the rotation of the Earth is usually ignored in the guidance design and characteristics of dynamics and closed-loop system lack theoretical analysis. Considering the above problems, the longitudinal reentry dynamics are analyzed in detail first. The relative degree of the motion equations is calculated as 2 while the states of the motion are chosen as the drag, the first derivative of drag and velocity, with drag as the output and bank angle as the input and the map from original states to the new ones is proved as a diffeomorphism. The velocity equation is proved as bounded-input-bounded-state stable. Then, ADRC(Active Disturbance Rejection Control) method is adopted to design the guidance, and the principles of choosing control parameters are also given. Moreover, the drag tracking error boundedness is proved in theory. The method proposed without the need of linearization or simplification of the dynamics, has higher precision, wider scope of application and reduced conservation. The dynamics properties and closed-loop analysis presented in this paper could provide a reference to the hypersonic vehicle reentry guidance, lunar or Mars reentry guidance or feedback linearization control design. Finally, the effectiveness of the guidance is illustrated through simulation.