为了研究小尺度空间碎片的降轨特性, 建立了空间碎片自旋与非自旋模型, 理论分析了地基激光作用下碎片速度的变化规律, 在此基础上研究了激光辐照作用下空间碎片的变轨模型。采用理论仿真的方法, 分析了在高能脉冲激光作用下空间碎片的近地点与远地点高度、半长轴及偏心率随初始真近角的变化规律。结果表明, 地基激光清除空间碎片存在最佳作用区域, 自旋碎片在初始真近角86°~151°范围内降轨效果最佳, 非自旋碎片在初始真近角130°~162°范围内降轨效果最佳。自旋空间碎片降轨效果明显优于非自旋空间碎片。

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.