Influence of shockwave profile on ejecta from shocked Pb surface:Atomistic calculations

We conduct molecular dynamics simulations of the ejection process from a grooved Pb surface subjected to supported and unsupported shock waves with various shock-breakout pressures(PSB) inducing a solid–liquid phase transition upon shock or release. It is found that the total ejecta mass changing with PSBunder a supported shock reveals a similar trend with that under an unsupported shock and the former is always less than the latter at the same PSB. The origin of such a discrepancy could be unraveled that for an unsupported shock, a larger velocity difference between the jet tip and its bottom at an early stage of jet formation results in more serious damage, and therefore a greater amount of ejected particles are produced. The cumulative areal density distributions also display the discrepancy. In addition, we discuss the difference of these simulated results compared to the experimental findings.     

Molecular dynamics simulations of jet breakup and ejecta production from a grooved Cu surface under shock loading

Large-scale non-equilibrium molecular dynamics simulations are performed to explore the jet breakup and ejecta production of single crystal Cu with a triangular grooved surface defect under shock loading. The morphology of the jet breakup and ejecta formation is obtained where the ejecta clusters remain spherical after a long simulation time. The effects of shock strength as well as groove size on the steady size distribution of ejecta clusters are investigated. It is shown that the size distribution of ejecta exhibits a scaling power law independent of the simulated shock strengths and groove sizes. This distribution, which has been observed in many fragmentation processes, can be well described by percolation theory.     

一种新的光子多普勒速度频谱分析方法

光子多普勒速度计可给出飞层表面某一速度带内颗粒群速度随时间演化的频谱数据, 在冲击动力学实验尤其是微喷射及其混合研究中得到广泛应用. 本文提出一种新的光子多普勒频谱数据分析方法, 可推断出混合区厚度变化和前端等效颗粒尺度. 利用该方法, 对一些典型状态下喷射混合速度频谱开展分析, 获得了不同冲击压力、气体条件下颗粒度数据, 证实了气体环境下喷射颗粒的气动破碎现象, 以及破碎后尺度与初始条件的依赖性, 为喷射混合物理规律研究提供了重要依据.     

Perturbation evolution at a metal-metal interface subjected to an oblique shock wave: Supersonic velocity of the point of contact

The perturbation evolution at the interface between identical metals (metal plates) that is exposed to high-speed oblique shock waves is observed experimentally for the first time (the waves are attached to the point of contact, so that a cumulative jet cannot form). The experiments are numerically simulated by the two-dimensional Lagrange method. An elastoplastic model where the dynamic yield strength is a function of material state parameters is employed. An analytical technique to treat instability development under given loading conditions is suggested. High strains produce a high-temperature zone near the interface (thermal softening zone). A short-lived shear flow with a high velocity gradient depending on the angle and velocity of plate collision is observed. In this zone, the shear modulus and the yield strength are appreciably lower than under normal conditions, which favors instability development.     

微喷射粒子团簇探测算法及其应用

在团簇多重标号技术基础上,提出了团簇探测的新算法,并以此作为大尺度二维和三维分子动力学模拟冲击加载金属材料微喷射粒子团簇分析的子程序.以二维为例描述了算法的逻辑结构,测试分析了算法的运行效率,并将其应用到二维分子动力学模拟冲击加载金属Cu和Al微喷射粒子的团簇统计分析中,对微喷射粒子团簇尺寸分布得到一些规律性认识.     

爆轰波对碰驱动平面锡飞层的动力学及动载行为特征研究

强冲击下的物质变形、破坏及诱发的轻重介质混合问题,是内爆压缩科学和工程应用领域的研究重点.本文针对爆轰波对碰条件下的复杂加载动力学过程及其动载破坏形态特征,开展数值模拟研究与极曲线理论分析.设计了爆轰波对碰驱动平面锡飞层的计算模型,获得了爆轰加载动力学过程及波系相互作用物理图像,分析了锡飞层对碰区自由表面速度历史的典型特征.给出了锡飞层中折射激波对碰发生马赫反射的临界条件,解读了三波结构的传播行为,阐明了对碰区内存在"一维正冲击"区域,一维区外存在单次斜冲击向两次斜冲击过渡的复杂加载动力学过程,提出了对碰区冲击动力学模型,揭示了影响对碰区动载行为特征的机理.数值模拟结果与极曲线理论分析结果相互印证,符合较好.本文的研究成果,将为深入理解和解读对碰区特殊的物质破坏及混合现象提供重要的理论支撑.     

激光加载下金属锡材料微喷颗粒与低密度泡沫混合实验研究

金属材料的微喷是冲击加载下金属表面发生的一种动态破碎现象,微喷研究在很多领域都具有重要意义,包括惯性约束聚变(ICF)和烟火制造等.由于激光实验特有的优势,近几年国内外开展了很多利用强激光驱动冲击加载研究材料微喷过程的实验.利用泡沫材料对微喷颗粒进行静态软回收虽然可以获得颗粒的形态分布、颗粒尺寸及颗粒质量等定量结果,但并不能反演微喷颗粒从进入泡沫到停滞过程中的动态混合过程.为此,在神光Ⅱ升级装置上利用皮秒脉冲激光照射金丝产生高能X射线,实现了对锡微喷颗粒与低密度泡沫混合过程的高时间分辨和高空间分辨背光照相.背光图像面密度结果证实微喷颗粒在泡沫中并没有发生二次破碎.静态回收结果表明,在锡材料与泡沫紧贴放置的情况下,微喷颗粒在泡沫中的穿透深度随着加载压强升高呈现先增大后减小的规律,与非紧贴放置的实验结果有明显的差别.     

动载荷下金属板表面的微物质喷射

 用石英晶体传感器技术，测量了冲击波作用下铝合金（Ly-12）和纯铅样品自由表面的微物质喷射量。在冲击压力为32 GPa时，测得光洁度为3.2、0.4、0.1 μm的铝合金的微物质喷射量分别为1.53～3.28 g/m²，0.2～0.3 g/m²和0.053～0.096 g/m²，对光洁度为3.2 μm的纯铅样品，在压力为13 GPa和47 GPa时，微物质喷射量分别微26.4～42.4 g/m²和183～328 g/m²。在最高冲击压力约为20 GPa时，做了多次冲击下的微物质喷射量测量，发现比单次冲击加载下的喷射量有很大的减少。结果表明，微物质喷射量与自由表面的加工条件、局部熔化和加载方式等因素有关。     

等离子体激励器的静特性与高速特性仿真研究

A parametric study of high-frequency plasma jet actuator was carried out, using the experiment- tally measured energy distribution law of arc discharge as an ideal heat source. The influence of the exit angle of the actuator on the flow field was explored. The jet flow field characteristics of the spark discharge actuator under supersonic flow (Ma0=2.0) were investigated. The results show that the energy density of heat flux increases and the jet front and forward shock wave moves faster with the decrease of discharge region, and the smaller the exit angle of the jet is, the stronger the momentum injection ability of the actuator along the flow direction is. The rule still applies under high-speed air flow conditions. Compared to the static condition, the momentum injection capability of the jet is stronger and the influence domain is larger under supersonic flow conditions.     

冲击射流激波振荡与抑制

欠膨胀冲击射流具有复杂的激波结构,并伴随产生高幅值的离散频率单音.通过高速摄像获取的纹影图像并结合噪声测量,对欠膨胀冲击射流激波振荡过程、剪切层不稳定波的模态和离散频率单音的产生进行了系列研究.给出了冲击距离为5倍喷嘴出口直径的复杂流动实验结果分析,射流剪切层不稳定波有对称和非对称两种模态,发现不同模态下的离散频率单音...     

Magnetohydrodynamic Shocks in the Interplanetary Space: a Theoretical Review

I discuss in this brief review some properties of magnetohydrodynamic (MHD) discontinuities in the interplanetary space. My emphasis is on a special case of MHD discontinuity, namely interplanetary (IP) shocks, and those that are found at 1 AU. I derive the Rankine-Hugoniot (RH) equations to evaluate plasma parameters in the downstream region (shocked plasma) in relation to the upstream region (unshocked plasma). These properties are used to classify IP shocks in terms of their geometry and their direction of propagation in relation to the Sun. The shock geometry is determined in terms of two angles: \(\theta _{B_{n}}\), the angle between the upstream magnetic field and the shock normal, and \(\theta _{x_{n}}\), the angle between the shock normal and the Sun-Earth line. Sources of IP shocks frequently found in the solar wind at Earth’s orbit are presented. Then the RH equations are solved for two categories of IP shocks in a special case: perpendicular shocks, when \(\theta _{B_{n}}\) is 90 ^°, and oblique shocks, when that angle is 45 ^°. Finally, I highlight the importance of knowing the shock geometry, mainly the impact angle \(\theta _{x_{n}}\), specially whether the shock is frontal or inclined, for space weather-related investigations. IP shocks are known to be more geoeffective if they strike the Earth’s magnetosphere frontally, or with impact angle nearly null. These results have been reported both by modeling and experimental studies in the literature.     

两电极等离子体合成射流激励器工作特性研究

采用放电测量和高速阴影技术对两电极等离子体合成射流激励器工作特性进行了系统实验研究.实验表明:激励器工作击穿电压和放电峰值电流随激励器所处环境压强的降低和放电频率的增大而减小,激励器腔体内的放电过程为火花电弧放电.典型的等离子体合成射流流场包含有一道前驱激波和一股呈蘑菇状的高速射流.在整个射流发展过程中,前驱激波以当地声速恒速传播,不随激励器条件的改变而变化,波的强度则随着激励器出口直径的减小、腔体体积的增大、环境压强的降低和放电频率的升高而减小.激励器腔体体积和放电频率的增加会降低腔内气体的加热效果,并减小射流速度.激励器出口直径和环境压强对射流速度的影响按规律变化且存在最佳值.本文实各验条件下激励器都产生了明显的前驱激波和高速射流,具有实现高速流场主动流动控制的应用潜能.     

超高速正撞击溅射物实验与仿真研究

 随着人类航天活动日益频繁,由微流星体和空间微小碎片超高速撞击航天器表面反溅生成的溅射物,对空间碎片环境的影响将越来越大。利用2017-T4铝合金球弹丸超高速正撞击5A06铝合金靶板进行了地面模拟实验与数值仿真计算,研究了反溅碎片特性参数,其中包括溅射物的平均速度、平均尺寸、平均溅射角,为空间碎片溅射物模型的建立奠定基础。采用多元回归方法,确定了溅射物平均速度与弹丸速度、弹丸尺寸之间的函数关系。研究表明,利用光滑粒子法（SPH）进行数值仿真计算,可以有效模拟溅射物平均尺寸、平均速度、平均溅射角;溅射物平均速度随弹丸速度、弹丸尺寸的增加而增加;溅射物基本呈圆锥形反溅,溅射物平均溅射角在41°左右,基本不受弹丸速度、弹丸尺寸的影响。     

Supersonic flow characteristics in laser grooving

The gas flow structure in laser grooving has been evaluated by numerical simulation and experiments in this study. A nozzle designed with a specific arrangement of compound jets for laser grooving has been tested. For this nozzle configuration the compressible flow structure of a shock wave induced by a supersonic side jet has been predicted in a numerical simulation using FLUENT, a computational fluid dynamics code and visualized in the experiment where the wall pressure on the grooving zone was evaluated and measured for jets impinging on the substrate at varying attacking angles of the side jet. The results obtained numerically and experimentally were comparable. In addition, the relationships between the material removal efficiency and the flow structure have also been established. It transpired that the attacking angle made a significant and dramatic improvement on the flow structure and grooving appearance and that a large wall pressure with a clear grooving profile can be obtained for attacking angles between 40° and 50° in the present test setup.     

Comparative visualized investigation of impact-driven high-speed liquid jets injected in submerged water and in ambient air

This paper is a comparative study on the characteristics of high-speed liquid jets injected in surrounding water and air using shadowgraph technique. One of the main objectives is to investigate the effects of liquid’s physical properties, used to generate the high-speed liquid jets, on jet generation’s characteristics. Moreover, comparative investigations on effects of those liquid jets after injected in water and air are reported. The high-speed liquid jets were generated by the impact of a projectile launched by a horizontal single-stage power gun. The impact-driven high-speed liquid jets were visualized by shadowgraph technique and images were recorded by a high-speed digital video camera. The process of impact-driven high-speed liquid jet injection in air and water, oblique shock waves, jet-induced shock waves, shock waves propagation, the bubble behavior, bubble collapse-induced rebound shock waves and bubble cloud regeneration were clearly observed. It was found that different properties of liquid (surface tension and kinematic viscosity) affect the jet maximum velocity and shape of the jet. Bubble behaviors were only found for the jet injected in water. From the shadowgraph images, it is found that the maximum average jet velocity, expansion and contraction velocities of bubble in axial direction increase when the value of the multiplied result of surface tension by kinematic viscosity increases. Therefore, surface tension and kinematic viscosity are the significant physical properties that affect characteristics of high-speed liquid jets.     

Influence of air pressure on the performance of plasma synthetic jet actuator

Plasma synthetic jet actuator(PSJA) has a wide application prospect in the high-speed flow control field for its high jet velocity.In this paper,the influence of the air pressure on the performance of a two-electrode PSJA is investigated by the schlieren method in a large range from 7 k Pa to 100 k Pa.The energy consumed by the PSJA is roughly the same for all the pressure levels.Traces of the precursor shock wave velocity and the jet front velocity vary a lot for different pressures.The precursor shock wave velocity first decreases gradually and then remains at 345 m/s as the air pressure increases.The peak jet front velocity always appears at the first appearance of a jet,and it decreases gradually with the increase of the air pressure.A maximum precursor shock wave velocity of 520 m/s and a maximum jet front velocity of 440 m/s are observed at the pressure of 7 k Pa.The averaged jet velocity in one period ranges from 44 m/s to 54 m/s for all air pressures,and it drops with the rising of the air pressure.High velocities of the precursor shock wave and the jet front indicate that this type of PSJA can still be used to influence the high-speed flow field at 7 k Pa.     

Jump relations for shocks in an anisotropic magnetized plasma

The jump relations for shocks moving into a collision-free anisotropic magnetized plasma are investigated under the assumption of isotropy of the plasma behind the shock front. The plasma ahead of the shock is assumed to be stable against the fire-hose instability and the mirror instability. In order to facilitate comparison with the work of Bazer and Ericson on isotropic shocks our nomenclature has been adapted to theirs. It turns out that as in the case of isotropic shocks the density ratio can be at most four corresponding to γ=5/3, that the change in magnetic field is bounded and that except for the case of Alfvén shocks the transverse parts of the magnetic field are collinear. It is further shown that the influence of the anisotropy is greatest for nearly equal thermal and magnetic energy densities. In the case of negative anisotropy no compressive shocks are possible with a major decrease in magnetic field if the thermal energy density much exceeds the magnetic energy density. A new kind of shock is shown to result from the analysis, the major effect of which is to destroy the anisotropy with only small changes in density, magnetic field and velocity vector. Its propagation speed is unbounded. Furthermore it has turned out that compressive, magnetic field increasing shocks have lower bounds in the density jump and magnetic field change for negative and positive anisotropy, respectively. In the collision-free case no unique entropy condition depending only on the total pressure components and densities can be given before the solution of the problem of shock structure. Therefore even expansive shocks may be admissible. The applicability of the isotropy assumption and ad-hoc-assumptions of other authors are briefly discussed.     

Generation of laser-driven flyer dominated by shock-induced shear bands: A molecular dynamics simulation study

High-power pulsed lasers provide an ingenious method for launching metal foils to generate high-speed flyers for high-pressure loading in material science or aerospace engineering.At high-temperature and high-pressure laser-induced conditions,the dynamic response of the metals and the mechanism of flyer formation remain unclear.In this study,the overall process of the laser-driven aluminum flyer,including laser ablation,rupture of metal foil,and the generation of the flyer was investigated by molecular dynamics combined with the two-temperature model.It was found that under high laser fluence(over 1.3 J/cm;with 200-fs laser pulse duration),the laser induced a shock wave with a peak pressure higher than25 GPa,which led to shear bands expanding from the edge of the laser ablation zone in the foil.Compared with the cases of low laser fluence less than 0.5 J/cm^-1,the shear band induced by high laser fluence promotes the rupture of the foil and results in a high-speed flyer(>1 km/s)with better flatness and integrity.In addition,the shock wavefront was found to be accompanied by aluminum crystal phase transformation from face-centered cubic(FCC)to body-centered cubic structure.The crystal structure reverts with the decrease of pressure,therefore the internal structure of the generated flyer is pure of FCC.The results of this study provide a better understanding of the laser-induced shock effect on the foil rupture and flyer quality and forward the development of the laser-driven flyer.     

Interaction of strong converging shock wave with SF<Subscript>6</Subscript> gas bubble

Interaction of a strong converging shock wave with an SF₆ gas bubble is studied, focusing on the effects of shock intensity and shock shape on interface evolution. Experimentally, the converging shock wave is generated by shock dynamics theory and the gas bubble is created by soap film technique. The post-shock flow field is captured by a schlieren photography combined with a high-speed video camera. Besides, a three-dimensional program is adopted to provide more details of flow field. After the strong converging shock wave impact, a wide and pronged outward jet, which differs from that in planar shock or weak converging shock condition, is derived from the downstream interface pole. This specific phenomenon is considered to be closely associated with shock intensity and shock curvature. Disturbed by the gas bubble, the converging shocks approaching the convergence center have polygonal shapes, and the relationship between shock intensity and shock radius verifies the applicability of polygonal converging shock theory. Subsequently, the motion of upstream point is discussed, and a modified nonlinear theory considering rarefaction wave and high amplitude effects is proposed. In addition, the effects of shock shape on interface morphology and interface scales are elucidated. These results indicate that the shape as well as shock strength plays an important role in interface evolution.     

Bow shocks formed by a high-speed laser-driven plasma cloud interacting with a cylinder obstacle

A bow shock is formed in the interaction of a high-speed laser-driven plasma cloud with a cylinder obstacle. Its temporal and spatial structures are observed by shadowgraphy and interferometry. The width of the shock transition region is ～ 50 μm, comparable to the ion–ion collision mean free path, which indicates that collision is dominated in the shock probably. The Mach-number of the ablating plasma cloud is ～ 15 at first, and decreases with time resulting in a changing shock structure. A two-dimension hydrodynamics code, USim, is used to simulate the interaction process. The simulated shocks can well reproduce the observed.