Modeling of the whole process of shock wave overpressure of freefield air explosion

The waveform of the explosion shock wave under free-field air explosion is an extremely complex problem.It is generally considered that the waveform consists of overpressure peak,positive pressure zone and negative pressure zone.Most of current practice usually considers only the positive pressure.Many empirical relations are available to predict overpressure peak,the positive pressure action time and pressure decay law.However,there are few models that can predict the whole waveform.The whole process of explosion shock wave overpressure,which was expressed as the product of the three factor functions of peak,attenuation and oscillation,was proposed in the present work.According to the principle of explosion similarity,the scaled parameters were introduced and the empirical formula was absorbed to form a mathematical model of shock wave overpressure.Parametric numerical simulations of free-field air explosions were conducted.By experimental verification of the AUTODYN numerical method and comparing the analytical and simulated curves,the model is proved to be accurate to calculate the shock wave overpressure under free-field air explosion.In addition,through the model the shock wave overpressure at different time and distance can be displayed in three dimensions.The model makes the time needed for theoretical calculation much less than that for numerical simulation.

Experimental Investigation on Shock Wave Characteristics of Aluminized Explosives in Air Blast

To investigate the shock wave characteristics of RDX-based aluminized explosives,air blast tests were conducted for measuring the parameters of 10 kg aluminized explosives which contained 0-40% aluminum.The results showed that with the increasing of aluminum content,the overpressures and impulses increase at first and then decrease within 7 m or 5 m,which reached the maximum when aluminum content was 20% or 30%.Power exponential formulas are used to fit the shock wave parameters vs scaled distance,where an equal weight of TNT is used to calculate the scaled distance.The overpressures of HL0 and TNT in tested locations not only conform to the similar law,but also conform to the same attenuation law after gaining the scaled distances of equal TNT mass.The pre-exponential factors of overpressure and impulse,kp and kI,decrease along with the increasing of Al content and keep the same pace as the calculated PCJ）.The attenuation coefficients a_P and aIincrease at first and decrease later with the increasing of aluminum content,and they reached the maximal values with30% Al containing,which keeps the same pace as the calculated QV.

Influence of air pressure on mechanical effect of laser plasma shock wave

The influence of air pressure on mechanical effect of laser plasma shock wave in a vacuum chamber produced by a Nd：YAG laser has been studied. The laser pulses with pulse width of 10ns and pulse energy of about 320mJ at 1.06μm wavelength is focused on the aluminium target mounted on a ballistic pendulum, and the air pressure in the chamber changes from 2.8 × 10^ 3 to 1.01 × 10^5pa. The experimental results show that the impulse coupling coefficient changes as the air pressure and the distance of the target from focus change. The mechanical effects of the plasma shock wave on the target are analysed at different distances from focus and the air pressure.

Air Plasma Mitigation of Shock Wave

Shock wave is a detriment in the development of supersonic aircrafts;it increases flow drag as well as surface heating from additional friction;it also initiates sonic boom on the ground which precludes supersonic jetliner to fly overland. A shock wave mitigation technique is demonstrated by experiments conducted in a Mach 2.5 wind tunnel. Non-thermal air plasma generated symmetrically in front of a wind tunnel model and upstream of the shock, by on-board 60 Hz periodic electric arc discharge, works as a plasma deflector, it deflects incoming flow to transform the shock from a well-defined attached shock into a highly curved shock structure. In a sequence with increasing discharge intensity, the transformed curve shock increases shock angle and moves upstream to become detached with increasing standoff distance from the model. It becomes diffusive and disappears near the peak of the discharge. The flow deflection increases the equivalent cone angle of the model, which in essence, reduces the equivalent Mach number of the incoming flow, manifesting the reduction of the shock wave drag on the cone. When this equivalent cone angle exceeds a critical angle, the shock becomes detached and fades away. This shock wave mitigation technique helps drag reduction as well as eliminates sonic boom.

Shock Wave Mitigation by Air Plasma Deflector

When the spacecraft flies much faster than the sound speed (~1200 km/h), the airflow disturbances deflected forward from the spacecraft cannot get away from the spacecraft and form a shock wave in front of it. Shock waves have been a detriment for the development of supersonic aircrafts, which have to overcome high wave drag and surface heating from additional friction. Shock wave also produces sonic booms. The noise issue raises environmental concerns, which have precluded routine supersonic flight over land. Therefore, mitigation of shock wave is essential to advance the development of supersonic aircrafts. A plasma mitigation technique is studied. A theory is presented to show that shock wave structure can be modified via flow deflection. Symmetrical deflection evades the need of exchanging the transverse momentum between the flow and the deflector. The analysis shows that the plasma generated in front of the model can effectively deflect the incoming flow. A non-thermal air plasma, generated by on-board 60 Hz periodic electric arc discharge in front of a wind tunnel model, was applied as a plasma deflector for shock wave mitigation technique. The experiment was conducted in a Mach 2.5 wind tunnel. The results show that the air plasma was generated symmetrically in front of the wind tunnel model. With increasing discharge intensity, the plasma deflector transforms the shock from a welldefined attached shock into a highly curved shock structure with increasing standoff distance from the model;this curved shock has increased shock angle and also appears in increasingly diffused form. In the decay of the discharge intensity, the shock front is first transformed back to a well-defined curve shock, which moves downstream to become a perturbed oblique shock;the baseline shock front then reappears as the discharge is reduced to low level again. The experimental observations confirm the theory. The steady of the incoming flow during the discharge cycle is manifested by the repeat of the baseline shock front.

Shadowgraph investigation of plasma shock wave evolution from Al target under 355-nm laser ablation

The propagation of a plasma shock wave generated from an Al target surface ablated by a nanosecond Nd：YAG laser operating at 355 nm in air is investigated at the different focusing positions of the laser beam by using a time-resolved shadowgraph imaging technique. The results show that in the case of a target surface set at the off-focus position, the condition of the focal point behind or in front of the target surface greatly influences the evolution of an Al plasma shock wave, and an ionization channel forms in the case of the focal point set in front of the target surface. Moreover, it is found that the shadowgraph with the evolution time around 100 ns shows that a protrusion appears at the front tip of the shock wave if the focal point is at the target surface. In addition, the calculated results of the expanding velocity of the shock wave front, the mass density, and pressure just behind the shock wave front are presented based on the shadowgraphs.

TNT和温压炸药浅埋爆炸效应差异性研究

为研究TNT和温压炸药浅埋爆炸效应的差异性,文章开展了浅埋爆炸试验,系统分析了TNT和温压炸药在爆坑形貌和地表空气冲击波波形等方面的差异。结果表明:相同工况的浅埋爆炸,温压炸药产生的爆坑直径、深度以及体积都大于TNT,装药埋深为0.1 m和0.3 m时,温压炸药产生的爆坑体积分别是TNT的1.2倍和2.3倍。通过对测得的冲击波参数进行比较,分析得出:当埋深为0.1 m和0.3 m时,比例距离为1的测点处温压炸药产生的冲击波峰值压力分别是TNT的2.16倍和1.41倍;在研究范围内,比例距离和埋深变化对不同类型装药的冲击波冲量衰减量影响很小,但对衰减率有较大影响,当埋深从0.1 m增加为0.3 m时,2种类型装药的冲量衰减率都增加了近1倍。

激波冲击下air/SF_6界面的Richtmyer-Meshkov不稳定性

实验研究了低马赫数(1.27)激波作用air/SF6界面的RM不稳定性问题。air/SF6初始正弦界面由厚度为1～2!m的薄膜相隔得到,用阴影法测试界面演化过程。实验结果表明:由于不稳定性重流体(SF6)向轻流体(air)演化成"尖钉"结构,而轻流体演化为"气泡"结构;由于界面切向速度差的Kelvin-Helm-holtz不稳定性,"尖钉"头部翻转成蘑菇头形状;之后,蘑菇杆破碎。扰动振幅发展的实验结果与Zhang-Sohn模型和PPM数值计算的结果较吻合。

多层气泡膜隔层结构对水下冲击波衰减效果分析

为分析多层气泡膜隔层结构对水下爆炸冲击波衰减效果,使用不同规格气泡膜并设计不同层数的空气隔层结构,以8号工业电雷管作为爆源,进行水下爆炸试验,获得水下冲击波参数,通过冲击波超压峰值与比冲击波能对比分析气泡膜对水下冲击波的衰减效果。结果表明:随着气泡膜层数的增加,冲击波超压峰值衰减率随之增加,1#气泡膜衰减率由48.32%上升至89.10%,2#气泡膜衰减率由86.08%上升至91.33%,3#气泡膜衰减率由87.87%上升至91.45%,4#气泡膜衰减率由90.34%上升至92.37%;薄膜隔层对比气泡膜空气隔层,其对水下冲击波的衰减影响比重较小,在层数相同的条件下,气泡膜气泡直径越大对水下冲击波的衰减效果越好,说明隔层结构中气泡对冲击波的衰减有着重要的作用;通过比冲击波能分析,气泡膜空气隔层比冲击波能消耗均超过98.50%以上,能量消耗显著。在实际应用中,可以使用气泡膜作为防护材料,能够有效地降低冲击波对被保护对象带来的危害。

供风量与气泡帷幕层数协同下水中爆炸冲击波的削波效果

气泡帷幕能有效地削弱水中冲击波对周围环境的影响。为了研究气泡帷幕供风量和层数对水中冲击波的协同作用,在供风量为30、60、90 L/min的条件下分别设计了含1、2、3层气泡帷幕的水下爆炸试验。结果表明,气泡帷幕的衰减率随供风量和层数增加而增大。当供风量较小(如30、60 L/min)时,随着气泡帷幕层数的增加,相邻层数之间峰值压力的衰减效率越来越低;当供风量较大(如90 L/min)时,随着气泡帷幕层数的增加,相邻层数之间峰值压力的衰减效率越来越高。结合实际工程的经济效益和水下复杂环境问题对削波效果进行分析,确定在供风量为30 L/min时开启2层气泡帷幕是最优的削波方案,为相关的实际工程问题提供参考和新思路。

Simulation of Airblast Load and Its Effect on RC Structures

In the analysis of a structure subjected to an explosion event, the determination of the blast load constitutes a crucial step. The effect of the blast load on the structure depends not only on the peak shock overpressure, but also the impulse (hence the duration). For structures with a regular geometry, the blast load may be fairly well estimated using appropriate empirical formulae; however, for more complex situations, a direct simulation using appropriate computational techniques is necessary. This paper presents a numerical simulation study on the prediction of the blast load in free air using a hydrocode, with focus on the sensitivity of the simulated blast load to the mesh grid size. The simulation results are compared with empirical predictions. It is found that the simulated blast load is sensitive to the mesh size, especially in the close-in range, and with a practically affordable mesh grid density, the blast load tends to be systematically underestimated. The study is extended to internal blast cases. An example concrete slab under internal explosion is analyzed using a coupled analysis scheme. The internal blast load from the simulation is examined and the response of the RC slab is commented.

Characteristics of supersonic flow in new type externally pressurized spherical air bearings

In order to predict accurately the characteristics of supersonic flow in new type externally pressurized spherical air bearings under large bearing clearance and high air supply pressure,which could decrease their load carrying capacity and stability,a CFD-based analysis was introduced to solve the three-dimensional turbulent complete compressible air flow governing equations.The realizable κ-ε model was used as a turbulent closure.The supersonic flow field near air inlets was analyzed.The flow structures illustrate that the interaction exists between shock waves and boundary layer,and the flow separation is formed at the lower corner and the lower wall around the point of a maximum velocity.The numerical results show that the conversion from supersonic flow to subsonic flow in spherical air bearing occurs through a shock region(pseudo-shock),and the viscous boundary layer results in the flow separation and reverse flow near the shock.The calculation results basically agree with the corresponding experimental data.

装药埋深对地表空气冲击波影响的试验研究

为研究土壤中装药埋深对地表空气冲击波传播规律的影响,开展了5kg TNT的触地爆炸试验以及埋深分别为0.108、0.228、0.85m的爆炸试验,获得了多个比例距离处的冲击波峰值压力、冲量以及正压作用时间数据,分析了埋深对冲击波传播特性的影响。结果表明,冲击波峰值压力和冲量随着埋深的增加而减小,随着爆距的增大而减小;触地爆炸比例距离为4的测点处其峰值压力是比例距离为1处的3.24%,埋深为0.108m的爆炸试验比例距离为4处的测点其峰值压力是比例距离为1处的25.02%;埋深为0.108m时,比例距离为1处的峰值压力和冲量分别是触地爆炸对应值的8.7%和20.4%;并对两种工况的正压作用时间进行了分析,触地爆炸的正压作用时间随爆心距增加呈指数增加,埋深为0.85m的爆炸试验其正压作用时间呈对数增加。通过对试验数据的进一步分析,建立了冲击波峰值压力、冲量与埋深、比例距离的工程计算模型,可用于浅埋爆炸时弹药威力评价与毁伤效能预估。

浅埋爆炸空气冲击波峰值压力计算方法研究

为研究装药比例埋深和比例距离对浅埋爆炸空气冲击波峰值压力的影响,测试了3种比例埋深工况下,7种比例距离处浅埋爆炸空气冲击波的峰值压力,结合量纲分析对试验数据进行拟合,得到了浅埋爆炸空气冲击波峰值压力的经验公式。结果表明:空气冲击波峰值压力随着比例埋深和比例距离的增加而减小;随着比例距离增加,比例埋深对空气冲击波峰值压力的影响减弱;空气冲击波峰值压力ΔPD与装药量Q、爆心距R和埋深L有关,其经验公式为:■。

动爆冲击波场空间位置分布规律研究

为研究装药速度对爆炸冲击波场空间位置分布规律的影响,对不同速度装药的空中爆炸冲击波场进行了数值模拟,获取了动爆冲击波场演化历程图像。仿真结果表明:装药速度影响下爆炸冲击波波阵面的形状不再为球形,并且冲击波作用场呈现沿装药速度方向移动的现象,其移动量可以由波阵面所围区域几何中心的移动来表征,移动停止时几何中心的移动距离与装药速度大小近似成正比。对几何中心的移动距离开展了量纲分析,并在仿真数据的基础上建立了装药速度影响下几何中心移动距离的工程计算模型,校验结果表明,计算模型的精度较好,具有一定普适性。

基于LS-PrePost的不同形状装药爆炸仿真研究

LS-PrePost是一款功能强大、操作便捷的爆炸仿真软件。*INITIAL_VOLUME_FRACTION_GEOMETRY和*LOAD_BLAST是LS-PrePost中的关键字卡片,而SPH是一种光滑粒子流体动力学方法,都可以用来施加爆炸载荷。为研究球形装药爆炸仿真建模方法,使用以上方法进行建模,分析不同建模方法的优缺点及适用场景。选择最优建模方法研究1 kg TNT炸药不同形状装药爆炸产生空气冲击波的不同。本文在研究爆炸仿真建模现状的基础上,查阅文献资料,选择最优建模方法。在经过验证的有限元模型上进行爆炸仿真,模拟实验仅改变装药形状参数,对球形、柱形、方形装药的有限元爆炸模型进行求解,得到不同比例距离下的超压峰值,制作图表比较各组超压峰值数据的差异。结果表明,在比例距离小于等于1.0 m·kg^(-1/3)时,柱形装药的超压峰值与球形装药更接近,而方形装药超压峰值与球形装药差异更大;随着比例距离的增加,柱形装药的峰值超压与球形装药的比值变化不大,而方形装药的峰值超压与球形装药的比值逐渐增加,变化较大。不同装药形状对于爆炸产生的冲击波超压的影响是不容忽视的,在研究实际爆炸案件的装药及其爆炸破坏作用时,应尽可能采用最接近实际情况的装药形状。在通过爆炸仿真方法研究问题时,也要选择合适的建模方法和装药条件,才能保证分析结果的准确可靠。

吸气式飞行器连续变马赫数风洞试验技术

为研究吸气式飞行器加/减速引起的进气道起动/再起动现象,以及该过程导致的飞行器整体气动性能突变问题,基于二维楔面激波机理,在1.2 m量级风洞中开展了超声速连续变马赫数试验技术研究,通过研制激波发生与控制系统,实现了一次风洞试验过程中马赫数连续可调。该技术方案具有马赫数调节简单、响应快,马赫数控制可靠、精度高等特点。流场校测表明,瞬时变马赫数区域流场品质满足国军标要求,可开展基于马赫数连续变化的测力测压等风洞试验。在进气道动态特性验证试验中,成功捕获了连续减速状态下进气道由起动到不起动的动态过程,临界状态特性与仿真结果一致性较高。

空中爆炸冲击波下结构动响应及其抗冲击波设计研究进展

随着军事需求的不断增加,多种武器设备都会面临爆炸冲击波环境生存问题,例如,水下爆炸冲击波对船舶的作用、空中爆炸冲击波对飞机、导弹等结构的影响等,因此爆炸冲击波载荷作用下结构的动态响应及防护研究是一个急需关注的热点与难点问题。本研究主要对空中爆炸冲击波方向的研究进行了详细的梳理及综述。首先对空中爆炸冲击波载荷的参数经验公式计算、数值模拟及载荷试验验证研究进展进行了综述;进一步详细介绍了冲击波作用下平板结构、加筋结构及其他典型结构的动响应研究及抗冲击波结构设计进展,研究成果内容涉及爆炸冲击波作用下结构的理论与数值模拟方法研究、结构损伤及破坏效应研究、结构抗冲击波及防护设计研究、结构抗爆吸能特性研究、空中爆炸冲击波试验方法及验证研究等;最后基于目前已有的研究成果,从技术成熟的角度对此领域进行了总结与展望,并提出了几方面急需研究解决的关键技术问题,为后续的工程类结构抗冲击波设计研究提供参考。

飞秒激光诱导的空气等离子体冲击波探究

一定强度的飞秒激光聚焦于空气能生成空气等离子体并诱导生成冲击波。为了观察该冲击波传播特性,引入了超快时间分辨涡旋滤波成像技术,并对观测到的冲击波动力学过程进行了分析。实验探测到泵浦能量为1.5 mJ的飞秒激光经过透镜聚焦到空气中产生等离子体空气冲击波,分析了在3~15μs时间段冲击波的动态演化过程。结果表明,飞秒激光等离子体空气冲击波在传输时以不对称的球形形状向外扩散,且沿着激光传播方向的传播速度与背着激光传播方向的传播速度不同,分别为372 m/s和341 m/s。这一观察结果与传统的点爆炸模型的对称情形不同,尝试对该不对称动力学过程进行了合理解释。

战斗部壳体厚度对爆炸空气冲击波的影响

采用LS-DYNA进行数值模拟,研究了战斗部壳体壁厚及壁厚半径比的改变对爆炸空气冲击波传播特性的影响和对壳体飞散规律的影响.对数值模拟结果的数据进行拟合,并进行量纲分析.结果表明,爆炸空气冲击波峰值随距离的衰减指数与壳体厚度近似成线性关系,壳体越厚,衰减指数越大,空气冲击波峰值随距离衰减越快.分界面(壳体和空气)处的冲击波峰值压力与壳体壁厚成反比,壳体越厚,分界面处的压力越低.战斗部外壳速度、加速时间、加速度与壳体厚度相关,壳体越厚,壳体飞散速度的最大值越小,加速时间越长,加速度越小.