Abstract: In order to solve the problem of large elliptical inclined orbit satellite's high fuel consumption in the acquisition of space debris from different planes, an orbital acquisition strategy using electric thruster to adjust the orbital plane is designed. The whole orbit acquisition process is designed in three stages. In the first stage, an apsidal rotation maneuver is executed. Subsequently, a single- or dual-elliptic transfer strategy is employed, applying finite thrust control at either the perigee or apogee. This approach enables adjustment to the target orbit using minimal impulses within a shorter timeframe, thereby achieving partial phase chasing. In the second stage, the continuous low-thrust electric thruster is used to exert continuous control at the intersection of the orbital plane, adjust the orbital plane, and enter the orbital plane of the target space debris. In the third stage, phase terminal correction is performed at the apsis, and the semi-major axis deviation adjusted in the first phase is corrected. The control timing and corresponding speed increment of the whole orbit acquisition strategy are given through detailed theoretical derivation, and particle swarm optimization is used to optimize the number of orbit changes in the second stage. Finally, numerical simulations validate the strategy's effectiveness, demonstrating that the fuel consumption for electric propulsion-based out-of-plane orbital transfer under identical conditions is only 3.56% of that required by chemical propulsion. This approach significantly enhances fuel efficiency while maintaining mission precision.

Key words: large elliptical inclined orbit, space debris, capture of skew orbits, electric thruster, bi-elliptic transfer