Abstract: The models of the spinning and non-spinning space debris were established, the velocity variation of the space debris ablating by space-based laser was analyzed, and the orbit maneuver of the space debris irradiating by laser was modeled and investigated. The variations of the perigee and apogee altitudes in different locations of the space debris orbit under the irradiation of high-energy pulse laser were simulated and analyzed, and the debris removal efficiency by using laser in different irradiation angles was analyzed relatively. The simulation results show that, there is an optimal action area of removal of space debris using space-based laser. The initial true anomaly of debris for most effective de-orbiting effect is around 120° and 240°. The angle of laser irradiating debris has a great influence on removal efficiency. The removal efficiency of laser irradiating debris in different angles has the symmetry relative to the elliptical axis of debris orbit.