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Wake characterization: Full flow simulation of space structures in low earth orbit.

机译：尾迹表征：低地球轨道空间结构的全流模拟。

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The problem of wake effects, particularly the near wake, from spacecraft in Low Earth Orbit is of increasing interest. The flow simulation reported herein combines the fully coupled effects of neutral particle flow, plasma flow, electromagnetic field effects and spacecraft charging. The simulation necessarily allows for chemically reacting flows (associative ionization, dissociation, and chain exchange). The simulation also allows for thermal accommodation at a spacecraft surface.; Due to the highly coupled nature of the flow physics, a full solution simultaneous approach is used. This is required due to the need for extremely high resolution data of the near wake region. In this approach, the neutral flow is modeled using a Direct Simulation Monte Carlo technique. The charged particles are modeled using a particle approach to solve the Poisson equation. A technique of having a separate neutral particle grid and charged particle grid is used. Neutral and charged particles are allowed collisional interaction. During one time step, the neutral-particle-move process is done separately from the charged-particle-move process which is accomplished in the presence of the electromagnetic field. A major advantage of the technique is that results may be obtained with the dominant effects of orbital flows simultaneously modeled. A major disadvantage is that the technique is computationally expensive.; Flow calculations for the neutral and charged particle cases are compared to independent computational simulations to confirm the accuracy. The solution procedure and technique are presented for several types of flows with orbital altitudes ranging from 250 km to 500 km. Excellent agreement with previously verified computational algorithms has been obtained for the case of neutral particle flow and charged particle flow. Results for the full flow simulation are presented for 250 km and 500 km.
机译：低地球轨道上的航天器引起的尾流效应问题，特别是近尾声问题日益引起人们的关注。本文报道的流动模拟结合了中性粒子流动，等离子体流动，电磁场效应和航天器充电的完全耦合效应。该模拟必须允许化学反应流（缔合电离，离解和链交换）。模拟还允许在航天器表面进行热调节。由于流动物理学具有高度耦合的性质，因此使用完整解决方案同时进行的方法。由于需要近尾流区域的超高分辨率数据，因此需要这样做。在这种方法中，使用直接模拟蒙特卡洛技术对中性流建模。使用粒子方法对带电粒子进行建模以求解泊松方程。使用具有分开的中性粒子网格和带电粒子网格的技术。中性粒子和带电粒子允许碰撞相互作用。在一个时间步骤中，中性粒子移动过程与带电粒子移动过程是分开进行的，而带电粒子移动过程是在存在电磁场的情况下完成的。该技术的主要优点是，可以在同时模拟轨道流的主导效应的情况下获得结果。一个主要的缺点是该技术在计算上是昂贵的。将中性和带电粒子情况下的流量计算与独立的计算模拟进行比较，以确认准确性。针对轨道高度为250 km至500 km的几种类型的流，提出了求解过程和技术。对于中性粒子流和带电粒子流，已经与先前验证的计算算法达成了极好的协议。给出了250 km和500 km的全流量模拟结果。

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