Satellite Collision Modeling with Physics-Based Hydrocodes: Debris Generation Predictions of the Iridium-Cosmos Collision Event and Other Impact Events
Satellite Collision Modeling with Physics-Based Hydrocodes: Debris Generation Predictions of the Iridium-Cosmos Collision Event and Other Impact Events
复制标题
使用基于物理的水电编码进行卫星碰撞建模：铱-宇宙碰撞事件和其他撞击事件的碎片生成预测
DOI：
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发表时间：
2010
期刊：
影响因子：
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通讯作者：
S. Olivier
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作者：
H. Springer;W. O. Miller;J. Levatin;A. Pertica;S. Olivier
卫星碰撞碎片对现有的空间资产和未来的空间任务构成风险。这些超高速碰撞产生的碎片的预测模型对于开发准确的空间态势感知工具和有效的缓减战略至关重要。超高速碰撞涉及跨越若干时间和长度尺度的复杂现象。我们已经开发了一个卫星碰撞碎片建模方法，包括拉格朗日流体代码丰富的光滑粒子流体动力学（SPH），先进的材料失效模型，详细的卫星网格模型，和大规模并行计算机。这些计算研究使我们能够调查卫星质心重叠和方向、相对速度和物质组成对碰撞碎片的大小、速度和物质类型分布的影响。我们已将碎片建模能力应用于最近的铱33-宇宙2251碰撞事件。虽然在这一事件中的相对速度是很好的理解，卫星CM重叠的程度和方向是不明确的。在我们的模拟中，我们改变了碰撞CM重叠和卫星的方向，从接近最大重叠到卫星最外面的部分重叠（即太阳能电池板和重力繁荣）。正如预期的那样，我们发现，随着卫星重叠的增加，碎片云的总质量和动量（转移）增加，碎片的平均大小减少，碎片的速度增加。预测的最大碎片还可使人们了解哪些卫星部件被进一步从撞击地点移走。很大一部分动量转移给了最小的碎片（< 1- 5毫米，取决于网格分辨率），特别是在大CM重叠模拟中。虽然将最小的碎片包括在内对于在水文代码模拟中加强质量和动量守恒至关重要，但对它们的处置似乎兴趣不大。根据我们的结果与观测结果的比较，铱33-宇宙2251碰撞事件不太可能是大质量重叠碰撞。我们还进行了单独的模拟，研究5和10厘米球形射弹以5、10和15公里/秒的接近速度撞击铱33号卫星所产生的碎片。鉴于卫星在轨道上的普遍性，必须了解卫星在小碎片威胁面前的脆弱性。这些研究还可以与概率关联分析合并，以更好地了解空间资产的风险。在这些计算研究中，我们发现由于耗散机制（例如，断裂）、碎片数和碎片速度对于固定的射弹尺寸随着速度的增加而增加。对于一个固定的速度，我们发现，较小的弹丸尺寸更有效地将动量转移到卫星。后一点具有重要的意义：8个（间隔）5厘米的碎片物体可以给卫星带来比一个10厘米的碎片物体在相同速度下更大的动量，并可能造成更大的损害。需要开展进一步的研究，以评估在这一速度范围内1-5厘米大小的碎片物体以及多个碎片物体对卫星造成的损害。«少
Satellite collision debris poses risks to existing space assets and future space missions. Predictive models of debris generated from these hypervelocity collisions are critical for developing accurate space situational awareness tools and effective mitigation strategies. Hypervelocity collisions involve complex phenomenon that spans several time- and length-scales. We have developed a satellite collision debris modeling approach consisting of a Lagrangian hydrocode enriched with smooth particle hydrodynamics (SPH), advanced material failure models, detailed satellite mesh models, and massively parallel computers. These computational studies enable us to investigate the influence of satellite center-of-mass (CM) overlap and orientation, relative velocity, and material composition on the size, velocity, and material type distributions of collision debris. We have applied our debris modeling capability to the recent Iridium 33-Cosmos 2251 collision event. While the relative velocity was well understood in this event, the degree of satellite CM overlap and orientation was ill-defined. In our simulations, we varied the collision CM overlap and orientation of the satellites from nearly maximum overlap to partial overlap on the outermost extents of the satellites (i.e, solar panels and gravity boom). As expected, we found that with increased satellite overlap, the overall debris cloud mass and momentum (transfer) increases, the average debris more » size decreases, and the debris velocity increases. The largest predicted debris can also provide insight into which satellite components were further removed from the impact location. A significant fraction of the momentum transfer is imparted to the smallest debris (< 1-5mm, dependent on mesh resolution), especially in large CM overlap simulations. While the inclusion of the smallest debris is critical to enforcing mass and momentum conservation in hydrocode simulations, there seems to be relatively little interest in their disposition. Based on comparing our results to observations, it is unlikely that the Iridium 33-Cosmos 2251 collision event was a large mass-overlap collision. We also performed separate simulations studying the debris generated by the collision of 5 and 10 cm spherical projectiles on the Iridium 33 satellite at closing velocities of 5, 10, and 15 km/s. It is important to understand the vulnerability of satellites to small debris threats, given their pervasiveness in orbit. These studies can also be merged with probabilistic conjunction analysis to better understand the risk to space assets. In these computational studies, we found that momentum transfer, kinetic energy losses due to dissipative mechanisms (e.g., fracture), fragment number, and fragment velocity increases with increasing velocity for a fixed projectile size. For a fixed velocity, we found that the smaller projectile size more efficiently transfers momentum to the satellite. This latter point has an important implication: Eight (spaced) 5 cm debris objects can impart more momentum to the satellite, and likely cause more damage, than a single 10 cm debris object at the same velocity. Further studies are required to assess the satellite damage induced by 1-5 cm sized debris objects, as well as multiple debris objects, in this velocity range. « less