Conclusion
Space Trajectories. Orbital Rendezvous

The linearized Hill-Clohessy-Wiltshire equations can be used to develop a simple rendezvous scenario in circular orbit. This scenario needs to be recalibrated by simulations, taking into account the actual dynamics of the vehicle and target. The precise optimization of maneuvers is based on specific commands such as linear quadratic, proportional navigation or velocity to gain. These control laws, compatible with on-board guidance, are used for rendezvous, interception or landing missions. They offer the robustness needed to take account of uncertainties, particularly those linked to dynamic models and orbit determination.