Control on the spacecraft hovering based on hybrid systems

Based on the dynamical principle of spacecraft orbits, the hybrid system model was used to study the hovering problems and a hybrid system model of hovering orbits was established. Based on this model, in the case that the target satellite orbit is elliptic, an equidistant hovering orbit control scheme and an elliptical hovering orbit control scheme were proposed, and the corresponding forces exerted on the hovering satellite for these two schemes were derived respectively. Numerical simulation results showed that hovering movement can be realized by exerting the corresponding forces on the hovering satellite.