Analysis of Optimal Orbital Capture Maneuver Strategy to LEO Spacecraft Based on Space Debris Collision

With the increasing of multi-satellites launching mission, contradiction between operationally orbit maneuver deployment of spacecraft and collision avoidance of space target becomes prominently. In this article, a spacecraft maneuver strategy analysis for the design optimization of orbit capture with collision avoidance is presented. With the linear relationship between maneuvering pulse and spacecraft relative motion is formulated, the analytical model of trace drift nearest distance and crossing space debris time with velocity pulses is proposed. Considering the constraints of TT&C resources, orbit determination accuracy calibration, attitude and orbit control propulsion system calibration, maneuver time limit, space target avoidance and so on, the optimization process of optimal orbital maneuver pulse is designed based on synthetic error estimation. An orbit altitude capture maneuver of triple-LEO Spacecraft launching with one vehicle is designed, the simulation shows that the optimal first maneuver pulse and orbit acquisition strategy are presented, which has good engineering operability and applicability.