Study on Proximity Operations Methods for Spacecraft in Multi-constraint Pursuit-Escort Scenarios

This study addresses the challenge of enabling a pursuing satellite to evade escort satellites and approach the target while adhering to constraints such as terminal distance, relative velocity, and solar illumination angles. Leveraging spacecraft relative dynamics, an optimization model is established for devising an optimal pulse control strategy under multiple constraints and objectives. To tackle this optimization problem, an NSGA-II algorithm with an error operator is designed, and a rolling optimization approach is adopted for the approach strategy. Additionally, a dynamic simulation environment is developed that accounts for Second Zonal Harmonic for simulation purposes. The numerical simulation results validate the effectiveness of the proposed approach method in accomplishing the approach mission.