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于哲峰 , 陈旭明 , 杨鹰 , 等 . 高超声速飞行器尾迹转捩及其对雷达散射截面的影响 [J ] . 兵工学报 , 2019 , 40 ( 12 ): 2467 - 2472 . DOI: 10.3969/j.issn.1000-1093.2019.12.010 http://doi.org/10.3969/j.issn.1000-1093.2019.12.010 当飞行器在大气层中以高超声速飞行时，在下游形成的等离子体尾迹有可能引起雷达散射截面（RCS）突增现象，影响飞行器的探测、跟踪和识别。在自由飞弹道靶上开展高超声速模型流场特性试验研究，测量不同马赫数和靶室压力下模型尾迹的流场结构和转捩位置，利用转捩准则对试验结果进行分析，讨论了转捩位置变化对高超声速飞行器RCS特性产生的影响。结果表明：模型特征尺寸、飞行马赫数和压力等是影响转捩位置的主要参数；尾迹对高超声速飞行器RCS的影响非常复杂，将改变RCS大小，使雷达成像变模糊甚至产生假目标。

YU Z F , CHEN X M , YANG Y , et al . Wake transition of the hypersonic vehicle and its influence on RCS [J ] . Acta Armamentarii , 2019 , 40 ( 12 ): 2467 - 2472 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2019.12.010 http://doi.org/10.3969/j.issn.1000-1093.2019.12.010 A long plasma wake is formed downstream when a hypersonic vehicle is flying in the atmosphere. It may cause a sudden increase in radar cross section (RCS), which affects the detection, tracking and identification of hypersonic vehicle. The flow field characteristics of hypersonic model in the free flight ballistic range is experimentally studied. The flow field structure and transition position of wake at different Mach numbers and chamber pressures were measured. The possible influence of transition position on the RCS characteristics of hypersonic vehicle is discussed. The results show that the model feature size, flight Mach number and chamber pressure are the main parameters affecting the transition position. The influence of the plasma wake on the hypersonic vehicle RCS is very complicated, which changes RCS and makes the radar imaging blurry, and even produce the fake targets. Key

袁野 , 王丽燕 , 曹占伟 , 等 . 碳纤维增强类复合材料烧蚀产物对等离子体流场特性影响的实验研究 [J ] . 兵工学报 , 2020 , 41 ( 2 ): 298 - 304 . DOI: 10.3969/j.issn.1000-1093.2020.02.011 http://doi.org/10.3969/j.issn.1000-1093.2020.02.011 高速飞行器表面的防热材料在气动加热产生的高温下会分解烧蚀并产生等离子体。为分析不同烧蚀条件下碳纤维增强类复合防热材料的烧蚀产物对下游流场特性的影响，利用高频等离子体风洞，采用高频感应加热方式对碳/碳和碳/碳化锆两种复合防热材料进行烧蚀并产生高速等离子体射流，在下游通过朗缪尔探针和平头柱塞量热计获得不同烧蚀状态下的流场电子数密度和驻点热流。研究结果表明：随着两种材料烧蚀率的增加，下游流场中的电子数密度和驻点热流逐渐降低，表明“黑障”风险和气动加热现象得到缓解；碳/碳化锆材料在降低下游流场的电离度和焓值方面优于碳/碳材料；随着材料前方来流焓值的增大，两种材料烧蚀造成的下游流场电离度和焓值的差异会在一定程度上缩小。

YUAN Y , WANG L Y , CAO Z W , et al . Experimental research on the influence of ablation product of carbon fiber reinforced composite material on the plasma flow field characteristics [J ] . Acta Armamentarii , 2020 , 41 ( 2 ): 298 - 304 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2020.02.011 http://doi.org/10.3969/j.issn.1000-1093.2020.02.011 The thermal protection material of high speed flight vehicle would be ablated and release the plasma under the high temperature induced by aerodynamic heating. In order to study the influence of ablation products of carbon fiber reinforced composite material on the flow field characteristics in different conditions of ablation, the high speed plasma jets were established through the ablation of two kinds of carbon fiber reinforced composite thermal protection materials (C/C and C/ZrC) in high frequency plasma wind tunnel. The number density of electrons and the stagnation point heat flux downstream were acquired using Langmuir probe and calorimeter in different conditions of ablation. The results show that the number density of electrons and the stagnation point heat flux in the flow field decrease with the increase in the ablation rate, relieving the “black-out” and aerothermal heating. C/ZrC is superior to C/C in weakening the ionization and the enthalpy of the flow field. With the increase in the enthalpy of the incoming flow, the differences in the ionization and enthalpies of the flow fields induced by the ablation of C/C and C/ZrC decrease to some extent.Key

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