Abstract: This paper studies the mission of space debris removal with spacebased laser debris from the two aspects of spacebased laser technology parameters and space debris removal demand. Based on the transmission mechanism of laser supported detonation wave, the change rule of laser ablation thrust is analyzed, the principle that the short pulse width laser is suitable for the task of debris removal is revealed, and the thrust model of laser ablating debris is 〖JP2〗derived. The typical laser parameters affecting the thrust are studied. The general solution〖JP〗 model of laser power density and light spot diameter are comparing summarized. The mathematical model among debris velocity increment and impulse coupling coefficient and the pulse number is built for the optimum coupling condition. From two aspects of debris size and orbital area, the necessity that the sun synchronous orbit 1~10 cm debris will be as the removal object is analyzed. The operation model under the condition of the encounter of spacebased laser and debris is proposed based on the rationality of removal mission. The removal distance and time window is proposed. The evaluation model of the debris removal effect with spacebased laser is established based on the high increment of perigee by the orbital dynamics knowledge. The case analysis shows the feasibility with the spacebased laser to remove debris. The research results can provide reference for relevant technical research and mission design.

Key words: spacebased laser, space debris removal, mission analysis, velocity increment, pulse width