Two typical materials of small scale space debris in LEO were selected. On this basis, corresponding laser ablation impulse coupling models were established respectively. The velocity variation of the space debris irradiated by high-power pulsed laser was analyzed, and the orbit transfer of the small scale space debris irradiated by laser was modeled and investigated. The variations of the orbital parameters of the space debris orbit under the irradiation of laser with assumed power were simulated and analyzed, and the influence rules of the spinning angular velocity and laser with different power on debris removal efficiency were analyzed and discussed. The simulation results show that the space-based laser of assumed power can complete the mission of removing two typical materials of debris successfully by irradiating in one cycle of flight, which provides necessary theoretical basis for the application of space debris removal by using space-based laser.