地基激光驱动空间碎片降轨特性研究

摘要

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.