Adaptive Output Feedback Control of Spacecraft Relative Translation

We address the problem of tracking relative translation in a leader-follower spacecraft formation using position feedback and under parameter uncertainty (spacecraft mass) and uncertainty in the leader variables (true anomaly rate and rate of change). We only assume boundedness of orbital perturbations and the leader control force but with unknown bounds. Under these conditions we propose a controller that renders the closed-loop system delta-weakly uniformly semiglobally practically asymptotically stable. In particular, the domain of attraction can be made arbitrarily large by picking convenient gains, and the state errors in the closed-loop system are proved to converge from any initial condition within the domain of attraction to a ball in close vicinity of the origin in a stable way; moreover, this ball can be diminished to a maximum precision by increasing the gains in the control law. Simulation results of a leader-follower spacecraft formation using the proposed controller are presented