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基于光滑粒子流体动力学(SPH)方法,对低轨卫星与某空间物体的超高速碰撞问题进行了数值模拟。通过确立航天器轨道高低判定准则及判定方法,分析了碰撞角度、碰撞速度对碰撞碎片散布的影响情况。仿真结果表明,低轨卫星与空间物体碰撞产生的大部分空间碎片所处轨道高度位于原卫星轨道周围;碰撞碎片的散布情况与碰撞方式密切相关,相比于上升式碰撞,下压式碰撞产生的下降碎片个数较多,上升碎片个数较少;低轨卫星与空间物体碰撞产生的空间碎片总数与碰撞相对速度密切相关,碰撞相对速度越大,碎片数量越多;随着碰撞相对速度的增大,上升碎片、下降碎片及双曲碎片的个数逐渐增加;在不改变碰撞总动量数量级的条件下,改变空间物体的速度大小对空间碎片散布的影响并不明显。
Based on the smooth particle hydrodynamics (SPH) method, the numerical simulation of the high-speed collision between a LEO satellite and a space object is carried out. By establishing the criterion of determining orbiting height of spacecraft and analyzing the influence of collision angle and impact velocity on the distribution of collision fragments, The simulation results show that the orbital height of most of the space debris produced by the collision of LEO satellites with space objects is located around the original orbit of the original satellite. The distribution of collision fragments is closely related to the collision mode. Compared with the ascending collision, the downward collision occurs The number of descending fragments is larger and the number of ascending debris is less; the total number of space debris generated by the collision of LEO satellites and space objects is closely related to the relative velocity of collisions, the larger the relative collision velocity is, the more the fragments are; as the collision relative velocity The number of ascending debris, descending debris and hyperbolic debris gradually increased. The impact of changing the velocity of space objects on the distribution of space debris was not obvious without changing the order of magnitude of the collision total momentum.