聚能射流对固体火箭发动机的冲击起爆

为研究聚能金属射流对固体火箭发动机的冲击响应，开展了聚能装药空射实验及某尺寸发动机在无防护情况下的射流冲击实验，使用高速摄影仪记录了爆炸响应过程，并测量了不同距离及方向的空气超压和破片速度。利用AUTODYN有限元计算软件对实验过程进行了数值模拟，通过调整流固耦合的网格大小，避免了耦合泄漏。实验结果表明，火箭发动机受到射流冲击后，会发生剧烈爆炸，推进剂完全反应，破片速度达4 700 m/s以上，距离发动机爆炸中心1 m处的空气超压达到19.78 MPa，爆炸中心温度达到3 000 ℃以上，该推进剂爆炸能量略高于常规炸药。模拟结果显示，射流以头部速度7 000 m/s的速度冲击发动机壳体后，射流头部的尖端被严重烧蚀，且速度降至约5 600 m/s；推进剂在受到射流侵彻1～2 mm后，发生剧烈反应；爆炸冲击波以球形沿圆柱孔装药传播，并通过圆柱形中心孔冲击另一侧推进剂，发生装药的二次冲击起爆，同时伴有回爆现象，在推进剂中心的高斯点出现了3次超压波峰；距离发动机中心1 m处3个高斯点的平均空气压力峰值为18.75 MPa，与实验结果吻合较好。     

Propagation characteristics of shock waves driven by gaseous detonation waves

We experimentally investigated propagation characteristics of the shock wave driven by a gaseous detonation wave emerging from the open end of a cylindrical detonation tube. In the present study, we visualized the shock wave and exhaust flowfields using a shadowgraph optical system and we obtained peak overpressure in the tube axial direction and the continuous shape transformation of shock waves around the tube open end. We also obtained overpressure histories of the shock wave using piezo-pressure transducers within 201 m from the open end of the tube. We normalized and classified these results by four regions using non-dimensional pressure and distance which are independent of variety of mixture and tube diameter. In the vicinity of the open end of the tube, the shock wave is nearly planar and does not significantly attenuate, and the peak overpressure maintains approximately C–J pressure. Subsequently, the shock wave attenuates rapidly, transforming from quasi-spherical to spherical. Farther from the tube open end, the shock wave propagates with approximately sound characteristic so that the peak overpressure decreases proportional to 1/r. Eventually, the shock wave begins to attenuate more rapidly than ideal sound attenuation, which may be due to the viscous effect.     

装药动爆冲击波特性研究

导弹、炮弹等战斗部爆炸时具有一定的速度，较大的运动速度会使爆炸冲击波场分布发生变化，进而对弹药的毁伤威力产生影响。本文中采用AUTODYN软件对速度分别为0、272、340、680、1 020和1 700 m/s的TNT球形裸装药在空气中爆炸的冲击波场进行了仿真计算，定量研究装药在动爆条件下的峰值超压、比冲量和正压作用时间等威力参数特性。结果表明，方位角小于90°时装药速度与冲击波超压、比冲量成正相关，与正压作用时间成负相关；方位角大于90°时装药速度与冲击波超压、比冲量成负相关，与正压作用时间成正相关。超压峰值大小沿方位角成正弦变化。最后，分析了冲击波峰值超压数据，建立了动爆冲击波超压的计算模型，该模型计算结果与仿真和实验结果吻合较好。     

基于地震波触发的战斗部动爆冲击波试验研究

提出了一种基于地震波触发的战斗部爆炸冲击波超压测试方法,该测试方法能可靠获取战斗部动爆冲击波超压峰值。采用提出的测试方法对着靶速度为0、535和980 m/s的战斗部空中爆炸冲击波分别进行了测试,并对战斗部动爆冲击波超压峰值测试结果和经验公式计算值进行了对比,定量分析了战斗部速度对冲击波压力场分布的影响。最后,在实测数据的基础上采用薄板样条插值方法重建了战斗部动爆冲击波超压三维可视化模型,为实战复杂环境下基于实测数据研究动爆冲击波特性提供了依据。     

大断面隧道钻爆冲击波的衰减规律

隧道开挖爆破产生的空气冲击波的破坏效应，将会对人员、机具设备与周围环境造成危害。隧道钻孔爆破冲击波的影响因素比裸露药包爆炸更多、更复杂，研究其衰减规律对采取合适的防护措施意义重大。本文中开展了时速350 km双线铁路大断面隧道钻孔爆破空气冲击波的现场测试，分析了不同工况下冲击波传播规律及影响因素。结果表明:钻爆冲击波超压时程曲线存在多个不同幅值的超压波峰，波峰之间具有明显微差延时的短间隔性，传播至远场未形成稳定的单一平面波，与单一药包爆炸冲击波的传播规律存在差异；钻爆冲击波超压信号由多段与微差延时相对应的子信号叠加而成，子信号数量与毫秒延期雷管段数相同，呈现出典型的时域特征；相同爆破条件下，大断面隧道钻爆时的乳化炸药冲击波转化因数小于小断面巷道工况下的；相较于总药量及最大段药量，按掏槽药量计算的超压峰值与实测超压峰值之间的相关性最强，钻爆冲击波最大超压峰值宜按掏槽段炸药TNT当量确定；隧道内大型机械设备等障碍物改变了钻爆冲击波流场的传播规律，呈现较明显的叠加放大效应。     

在开阔空间中水对爆炸冲击波的削波作用

用数值方法计算了开阔空间中布置在炸药周围的水对爆炸冲击波的削波作用。计算结果与实验测量数据进行了比较。计算表明 ,在炸药周围布置 1～ 5倍于炸药质量的水可以把爆炸冲击波峰值压力减小17%～ 46 %。     

Reinitiation process of detonation wave behind a slit-plate

The propagation phenomenon of a detonation wave is particularly interesting, because the detonation wave is composed of a 3D shock wave system accompanied by a reaction front. Thus, the passage of a detonation wave draws cellular patterns on a soot-covered plate. The pressure and temperature behind the detonation wave are extremely high and may cause serious damages around the wave. Therefore, it is of great significance from a safety-engineering point of view to decay the detonation wave with a short distance from the origin. In the present study, experiments using high-speed schlieren photography are conducted in order to investigate the behaviors of the detonation wave diffracting from two slits. The detonation wave produced in a stoichiometric mixture of hydrogen and oxygen is propagated through the slits, and the behaviors behind the slit-plate are investigated experimentally. When a detonation wave diffracts from the slits, a shock wave is decoupled with a reaction front. Since the two shock waves propagate from the slits interact with each other at the center behind the plate, the detonation wave is reinitiated by generating a hot-spot sufficient to cause local explosions. Furthermore, it is clarified that the shock wave reflected from a tube-wall is also capable of reinitiating the detonation wave. The reinitiation distance of the detonation wave from the slit-plate is correlated using a number of cells emerged from each slit.      

Investigation of the properties of a shock wave arising in a supersonic flow of plasma,passing through a transverse magnetic field

In a flow of plasma, set up by an ionizing shock wave and moving through a transverse magnetic field, under definite conditions there arises a gasdynamic shock wave. The appearance of such shock waves has been observed in experimental [1–4] and theoretical [5–7] work, where an investigation was made of the interaction between a plasma and electrical and magnetic fields. The aim of the present work was a determination of the effect of the intensity of the interaction between the plasma and the magnetic field on the velocity of the motion of this shock wave. The investigation was carried out in a magnetohydrogasdynamic unit, described in [8]. The process was recorded by the Töpler method (IAB-451 instrument) through a slit along the axis of the channel, on a film moving in a direction perpendicular to the slit. The calculation of the flow is based on the one-dimensional unsteady-state equations of magnetic gasdynamics. Using a model of the process described in [9], calculations were made for conditions close to those realized experimentally. In addition, a simplified calculation is made of the velocity of the motion of the above shock wave, under the assumption that its front moves at a constant velocity ahead of the region of interaction, while in the region of interaction itself the flow is steady-state.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 86–91, January–February, 1975.     

舱内爆炸角隅汇聚反射冲击波超压特性研究

为研究密闭舱室内爆角隅汇聚反射冲击波超压特性,利用缩比模型进行了某典型舱室内爆试验,得到远离角隅、两面角隅和三面角隅处的冲击波载荷,结合数值模拟研究了3种特征位置处冲击波传播规律及载荷特征。研究结果表明:远离角隅处壁面反射冲击波超压曲线呈现单峰结构,反射冲击波以球面波传播;距两面角隅一定范围内冲击波超压曲线呈现双峰结构,两面角隅冲击波超压曲线呈现单峰结构,角隅汇聚反射冲击波以椭球状传播;距三面角隅一定范围内冲击波超压曲线呈现多峰结构,三面角隅冲击波超压曲线呈现单峰结构,角隅汇聚反射冲击波以球面波传播;在合理假设条件下,根据量纲分析及数值模拟结果,得到首次冲击时角隅汇聚反射冲击波载荷经验计算公式。     

基于激波管评价的单兵头面部装备冲击波防护性能研究

为了优化单兵头面部防护装备结构,提升防护性能,首先开展了基于实爆场和激波管环境的裸头模抗爆炸冲击波对比测试。在此基础上,利用激波管对佩戴不同结构、不同防护等级的头盔-头模系统分别进行了正向及侧向爆炸冲击波防护性能测试,并对头盔-头模系统前部、前额部、顶部、后部、耳部以及眼部等重点区域的冲击波超压峰值和持续作用时间进行对比分析。实验结果表明,基于激波管的抗爆炸冲击波测试方法可替代外场实爆进行考核。受到冲击波正向作用时:两半盔头模顶部测点所测冲击波超压峰值约为喷管出口的 1/6,是裸头模和一体盔头模的 1/3;冲击波在两半盔顶部分体结构处分流卸压并形成叠加反射,导致作用时间延长（从 5.5～8.5 ms）,但超压峰值降低明显;对后部测点而言,冲击波的绕行和叠加使一体盔头模所测冲击波超压峰值（365 kPa）略高于两半盔头模（303 kPa）,约为裸头模（148 kPa）的 2.5 倍。通过提高单兵头面部防护装备结构密闭性（如佩戴眼镜、耳罩或者防护面罩）,可有效阻止冲击波进入头盔-头模系统内部,减弱叠加汇聚效应,提高单兵头面部装备防护性能。     

Structure of the detonation wave front in a mixture of nitromethane with acetone

It is shown that the leading front of an inhomogeneous detonation wave is a shock wave in which wave structures of the type of triple shock configurations are moving. It was experimentally found that the reaction in these inhomogeneities occurs in oblique shock waves. The reaction sites at the wave front are ring-shaped. In a 75: 25 mixture of nitromethane with acetone, up to 70% of the front surface is occupied by the reaction at the sites in the wave front. Measurements of the mass velocity profile indicate that afterburning takes place in the unloading area behind the Jouguet plane. Calculations of the heat release in the reaction mixture with a decrease in the mass velocity indicate that the material that have not reacted in the inhomogeneities can be ignited in the induction zone. It is suggested that the adiabatic flashes are a mechanism that generates inhomogeneities in the detonation wave front.     

Experimental investigation of door dynamic opening caused by impinging shock wave

To prevent damage caused by accidental overpressure inside a closed duct (e.g. jet engine) safety valves are introduced. The present study experimentally investigates the dynamic opening of such valves by employing a door at the end of a shock tube driven section. The door is hung on an axis and is free to rotate, thereby opening the tube. The evolved flow and wave pattern due to a collision of an incident shock wave with the door, causing the door opening, is studied by employing a high speed schlieren system and recording pressures at different places inside the tube as well as on the rotating door. Analyzing this data sheds light on the air flow evolution and the behavior of the opening door. In the present work, emphasis is given to understanding the complex, unsteady flow developed behind the transmitted shock wave as it diffracts over the opening door. It is shown that both the door inertia and the shock wave strength influence the opening dynamic evolution, but not in the proportions that might be expected.     

Interaction of a supersonic pulse jet with an obstacle

The nonstationary interaction between a supersonic pulse jet and a flat plate perpendicular to the jet axis is studied experimentally and numerically. The time dependences of the pressure and heat flux at various points on the obstacle and the spatial distribution of the density are obtained experimentally. The nonstationary flow is calculated numerically by the Godunov method. The experiments and calculations reveal the effect of the reflected starting shock wave and the front part of the swirled gas outflow on the distribution of the dynamic and thermal loads acting on the plate, in both time and space. Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 2, pp. 45–51, March–April, 1998. This research was carried out with partial financial support from the Russian Foundation for Fundamental Research (project No. 96-02-16170).     

钢化玻璃冲击波毁伤效应测试结果分析

为研究爆炸冲击波对钢化玻璃的毁伤阈值,开展了钢化玻璃冲击波毁伤效应实验。对每一发实验进行了爆炸参数测试,获得了冲击波超压随时间变化历程的实验数据。通过对实验数据的处理与分析,得到了爆炸冲击波基本参数,包括正反射超压、冲击波到时、正压作用时间、正反射冲量、负反射超压、负压作用时间和负反射冲量等。将实验结果与CONWEP计算结果进行了比较,比较结果表明二者误差很小,证明冲击波测试结果准确可靠。对冲击波正负反射参数进行了比较,结果表明冲击波正反射参数明显高于冲击波负反射参数。     

基于广义逆算法的冲击波超压场重建方法

针对局部布点测试不能全面了解冲击波传播过程的不足,以及冲击波超压经验公式的局限性,采用网络化测试技术获取冲击波信号,以计算机层析成像技术为基础,利用加权广义逆反演算法对爆炸冲击波速度场进行反演,根据峰值超压与速度的关系得到峰值超压场分布。经一定测试范围内实验验证,峰值超压重建结果优于经验公式计算结果。     

FAE爆炸场超压与威力的实验研究

利用现场测试系统动态灵敏度标定技术,分别等精度测试了FAE和TNT爆炸场峰值超压。在此基础上获得了各自的爆炸波峰值超压随传播距离的拟合曲线和TNT当量比。结果表明:FAE爆炸场超压分布规律与TNT有显著区别,前者属于大体积云雾爆炸,爆炸场可划分为云雾爆轰区、云雾边缘区和冲击波作用区;在云雾爆轰区,超压平均值在2.6MPa左右,在小于2/3云雾半径的范围内比同质量的TNT低,在大于2/3的云雾半径范围则显著大于TNT;在冲击波作用区,环氧丙烷燃料的FAE爆炸超压约是TNT爆炸效果的5倍,超压均呈衰减趋势,但FAE衰减比TNT缓慢许多。     

Background-oriented schlieren diagnostics for large-scale explosive testing

Experimental measurements of shock wave propagation from explosions of C4 are presented. Each test is recorded with a high-speed digital video camera and the shock wave is visualized using background-oriented schlieren (BOS). Two different processing techniques for BOS analysis are presented: image subtraction and image correlation. The image subtraction technique is found to provide higher resolution for identifying the location of a shock wave propagating into still air. The image correlation technique is more appropriate for identifying shock reflections and multiple shock impacts in a region with complex flow patterns. The optical shock propagation measurements are used to predict the peak overpressure and overpressure duration at different locations and are compared to experimental pressure gage measurements. The overpressure predictions agree well with the pressure gage measurements and the overpressure duration prediction is within an order of magnitude of the experimental measurements. The BOS technique is shown to be an important tool for explosive research which can be simply incorporated into typical large-scale outdoor tests.     

冲击波测试系统低频特性与补偿方法研究

为提高冲击波超压峰值的测量精度，多数学者把重点集中在系统高频特性研究上，以拓宽带宽的方式提高峰值测试的准确性。冲击波另外两个主要参数正压作用时间、比冲量却和测试系统的低频特性息息相关。针对实爆中出现的不同传感器正压作用时间差异较大的问题，对冲击波信号进行了边际谱分析，获得了信号的低频特性。建立了一阶参数模型来表征低频特性，通过激波管试验数据获取了7种系统的低频模型参数。采用零极点配置法设计了低频补偿模型。结果表明:冲击波测试系统低频特性严重影响冲击波信号正压作用时间测试准确性，基于低频特性补偿的数据处理方法可以有效的提高冲击波信号正压作用时间、比冲量地测试精度。     

爆炸驱动典型活性材料能量释放特性研究

为了研究活性材料爆炸驱动反应特性，基于粉末压制成型工艺，制备了Al/PTFE、Al/Ni两种典型的活性材料及Al₂O₃/PTFE、Al₂O₃/PTFE/W惰性材料。通过爆炸驱动试验，并结合高速摄影、远红外热像仪以及峰值超压测试技术，分析了不同活性材料壳体装药爆炸火球、温度场分布及空气冲击波峰值超压等特性。同时，在炸药爆炸空气冲击波峰值超压经验计算模型中考虑了活性材料释放的化学能，分析了反应释放能量对空气冲击波的影响规律。结果表明:活性材料在爆炸驱动过程中经历了强加载条件下反应、产生碎片并向四周飞散、撞击钢板及后续反应等阶段。活性材料对炸药爆炸产生的空气冲击波具有强化作用，爆炸加载瞬间材料仅发生了部分化学反应。     

Radiative cooling of plasma behind a reflected shock front

Calculation of gas flow in a shock tube on the basis of ideal theory [1] leads to results that differ from the real picture. In particular, the calculated velocity of the reflected shock wave exceeds the experimentally measured velocity [2] by about 20%. The calculated parameters of shock-heated gas agree well with the experimental results only directly behind the shock front [3]. The present paper reports a theoretical and experimental investigation of the variation of the plasma parameters behind the front of a reflected shock wave in argon. A picture of the gas-dynamic processes taking place after reflection of the incident shock wave by the end of the shock tube is determined. A method is developed for approximate analytic calculation, this making it possible to determine not only the parameters of the gas directly behind the front of the reflected shock wave for different positions of the wave relative to the end of the shock tube but also the variation of these parameters in other regions behind the reflected shock wave. The calculation takes into account the influence of the boundary layer and radiative cooling in the approximation of a low degree of ionization of the plasma and persistence of equilibrium conditions in the entire region behind the reflected shock wave. The experimental and theoretical profiles of the radiation behind the reflected shock wave are compared.