Abstract: Based on the relative motion dynamic model described by C-W equations, and by considering parameter uncertainties characterized by the norm-bounded method and the control input constraints in practice, a robust orbit design approach is proposed for the spacecraft rendezvous engineering. By introducing a Lyapunov function, the design problem is cast into a convex optimization problem subject to linear matrix inequalities. By solving this optimization problem, the robust controllers satisfying the requirements can be designed.

Key words: spacecraft rendezvous, uncertainty, thrust-limited, linear matrix inequality, robust controller