Relative Orbital Motion Control of Spacecraft Based on Multi-Objective Optimization

In this paper, we consider the relative motion of a follower spacecraft orbiting Earth in near circular orbit with respect to leader spacecraft. The orbital motion-control problem is studied here. order allow succeed its target maneuver, proposed multi-objective optimization method solve problem. Firstly, Hill–Clohessy–Wiltshire equation was used describe continuous system. Then, system discretized into discrete using numerical methods. Next, model formulated. model, two objectives, i.e., error and energy consumption, were minimized simultaneously. Furthermore, ε-constraint Pareto front, which demonstrates that trade-off between objectives can be achieved. Finally, experiments carried out validate effectiveness approach.