地基激光驱动空间碎片降轨特性研究

Research on de-orbiting mechanism of space debris driven by ground-based laser

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,semimajor 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.