Three-Impulse Model for Spacecraft to Avoid Space Debris and Return to the Original Orbit

This paper studies the formidable challenges posed by space debris during spacecraft operations, specifically focusing on the potential threats arising from the disintegration of a proximate satellite. The disintegration of a satellite could spawn debris fragments that may acquire diverse velocities, markedly complicating the avoidance maneuvers essential for the active spacecraft to sustain its original orbit. To address this issue, the principle of maneuvering reachable domain is introduced to model the debris swarm incorporating uncertainties in both velocity and trajectory following disintegration. Based on this model, a 3-impulse maneuver strategy is proposed to facilitate the active spacecraft through the debris swarm, enabling its safe return to the original orbit. To demonstrate the efficacy of this approach, 2 distinct types of orbital scenarios are simulated: one with a short rendezvous period and the other characterized by an extended hovering duration. These simulation results indicate that the propagation model of debris swarm with the maneuver strategy enables the active spacecraft to maneuver through the debris swarm along with an optimal evasion trajectory, thereby ensuring its safe return to the original orbit.