Abstract: In order to stuy the de-orbiting mechanism of small scale space debris, the models of spinning and non-spinning space debris were established. The variation of space debris velocity ablating by ground-based laser was analyzed theoretically. Orbit maneuver mode of space debris irradiating by laser was investigated. The variations of perigee and apogee altitudes, semi-major axis and eccentricity with the change of initial true anomaly of the space debris under the irradiation of high-energy pulse laser were simulated and analyzed. The simulation results show that there is an optimal action area of removal of space debris using ground-based laser. The de-orbiting effect of spin debris is the best with initial true anomaly in the range of 86°~151°. The de-orbiting effect of non-spinning debris is the best with initial true anomaly in the range of 130°~162°. The de-orbiting effect of spinning debris is superior to non-spinning debris.