Relative navigation algorithm research of chaser spacecraft

In this paper, the relative navigation algorithm of chaser spacecraft with orbit maneuvering is investigated. Based on the relative motion dynamic model and linear relative measurement model, a robust H
_∞
filter for chaser spacecraft is proposed, which contains affine norm-bounded uncertainties, disturbances, and non-Gaussian noise. The necessary and sufficient conditions for the existence of robust H
_∞
filter are obtained in terms of a linear matrix inequality(LMI). The filter design is then cast into a convex optimization problem subject to LMI constraints. The numerical simulation results show that the relative position precision is 0.1m and the relative velocity precision is 0.02m/s when the chaser spacecraft has orbit maneuvering, which illustrates the effectiveness and advantage of the proposed navigation algorithm.