On the shock-induced explosion resulting from an impact by a planar detonation

We analyse the processes which occur when a planar detonation propagating from the fixed end of a donor explosive charge impacts on an acceptor homogeneous explosive. We propose a model for estimating the minimal length of the donor charge for which an explosion can be generated in the acceptor. We show that the self-similarity of the donor flow imposes a minimal length on the donor charge so its piston effect be capable of keeping the volumetric-expansion rate of the shocked acceptor to small-enough values and, thereby, of triggering explosion in a finite time. The donor detonation is represented as a Chapman-Jouguet discontinuity; the chemical decomposition in the acceptor is described by the Arrhenius global rate law. The model reproduces the experimental trend according to which the smaller minimal lengths are obtained with donor explosives that have larger heats of reaction and initial pressures. The minimal lengths predicted by the model agree well with those obtained by means of one-dimensional numerical simulations. Additional simulations show that the minimal length for generating an explosion is smaller than, but perhaps of the same order as, the minimal length for generating a transition to detonation. Further work is necessary to (i) analyse the case of donor explosives with finite reaction rates, and to (ii) account for the detonation cellular structure in the simulations of shock-to-detonation transitions. Received 21 December 2001 / Accepted 15 July 2002 Published online 4 November 2002 Correspondence to: Pierre Vidal An abridged version of this paper was presented at the 18th Int. Colloquium on the Dynamics of Explosions and Reactive Systems at Seattle, USA, from July 29 to August 3, 2001     

The motion of explosion products behind the front of a detonation wave

The velocity of the explosion products behind the detonation wavefront in a 50/50 TNT-hexogen explosive was measured by an electromagnetic method.The experimental data on the mass velocity profile behind the wavefront in charges of different lengths, and the results of measurements of the motion of the backward rarefaction waves can be well described if in the mass velocity-time curves one isolates a stationary zone of 0.1 sec and regards the rest of the motion as self-similar.The experimentally observed sharp drop of mass velocity behind the wavefront indicates that the isentropic exponent of the explosion products increases upon expansion.The observed data on the distribution of mass velocities were used to calculate the isentrope of the explosion products in the pressure range 100–250 000 atm.     

Strong explosion in a combustible gas mixture

Assume that a planar, cylindrical, or spherical point explosion takes place in a combustible mixture of gases. As a result of the explosion a strong shock wave develops and triggers chemical reactions with the release of heat. The solution of the problem for the case in which the thickness of the heat release zone is neglected (the infinitely thin detonation wave model) was obtained in [1–3].It was emphasized in [4] that these solutions can be considered only as asymptotic solutions for time and distance scales which are large in comparison with the scales which are characteristic for the chemical reactions, and under the assumption that as the overdriven detonation wave which is formed in the explosion is weakened by the rarefaction waves it does not degenerate into an ordinary compression shock. Here the question remains open of the possibility of obtaining such asymptotic solutions with account for finite chemical-reaction rates.In conclusion the authors wish to thank E. Bishimov for carrying out most of the computations for this study.     

非理想爆轰产物流场的程序燃烧计算法

研究了用程序燃烧法计算非理想爆轰时引进不真实反应速率和人为粘性对化学反应区终点处参数的影响,证实不会引起流体力学波和程序燃烧波的分离。还给出了一般炸药状态方程情况的爆速曲率关系和对化学反应区终点参数计算误差的估计。     

Stabilization of detonation combustion in a high-velocity flow of a hydrogen-oxygen mixture

The flow of a hydrogen-oxygen mixture diluted with argon in a supersonic axisymmetric nozzle consisting of an inlet cylinder, a convergent region, a cylindrical throat, and a divergent region is considered. The supersonic flow enters the channel along the axis of symmetry. The flow structure is calculated with allowance for hydrogen ignition. A possibility of stabilizing the combustion zone is studied and the forces acting on the nozzle from the flow are determined. The problem is solved in the two-dimensional approximation with account for detailed combustion kinetics.     

Flame propagation in the turbulent flow of a burning mixture

The propagation of a flame in the turbulent flow of a burning mixture is analyzed theoretically. An equation is derived for the gas temperature and velocity probability distributions. The solutions of this equation are analyzed and the rate of flame propagation is determined.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 3–15, September–October, 1976.The author wishes to thank V. A. Sabel'nikova for critical comments.     

Direct initiation of detonation in a hydrogen-oxygen mixture diluted with nitrogen

The direct initiation of plane and cylindrical detonation waves in a hydrogen-oxygen mixture diluted with nitrogen using an exploding copper wire and a moving piston is investigated.Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No.6, pp. 151–156, November–December, 1992.The authors are grateful to G. D. Smekhov for calculating the Chapman-Jouguet detonation parameters and to V. V. Mitrofanov, who reviewed the article, for his useful comments.     

波纹结构迎爆面泡沫金属对甲烷-空气混合气体爆炸能量的吸收特性

为进一步探究气体爆炸荷载下异构迎爆面泡沫金属的吸能特性,在前期开展锯齿结构迎爆面材料吸能特性实验的基础上,以3种波纹结构迎爆面（凸面型、凹面型和凹凸连续型）泡沫金属材料为研究对象,利用自主搭建的气体爆炸管网实验平台,开展了该泡沫金属材料在甲烷-空气混合气体爆炸荷载下的吸能特性测定实验。采用不同波纹结构迎爆面阻隔爆材料,测定了管道内爆炸冲击波超压、火焰传播速度和火焰温度等随时间和空间的变化,分析了不同波纹结构迎爆面阻隔爆材料的吸能效果。结果表明：(1)迎爆面为波纹结构的泡沫金属材料对爆炸超压的衰减效果优于迎爆面为锯齿结构的泡沫金属材料和迎爆面为平面结构的泡沫金属材料,且迎爆面为凸面型波纹结构和凹凸连续型波纹结构的泡沫金属材料对超压衰减的速率高于迎爆面为锯齿结构和凹面型波纹结构的泡沫金属材料;迎爆面为锯齿结构的泡沫金属材料对火焰传播速度的衰减略强于迎爆面为波纹结构和平面结构的泡沫金属材料;迎爆面为波纹结构的泡沫金属材料对火焰温度的衰减效果优于迎爆面为锯齿结构及平面结构的泡沫金属材料。(2)在本文实验条件下,3种波纹结构（凸面型、凹面型和凹凸连续型）迎爆面泡沫金属材料的熄爆参数分别为5.338、4.340和6.090 MPa·℃,低于锯齿结构迎爆面材料的熄爆参数17.680 MPa·℃,且远低于熄爆参数安全值390 MPa·℃,波纹结构迎爆面材料具有良好的防护效果。(3)这3种迎爆面为波纹结构的泡沫金属材料均具有良好的吸能特性,均优于迎爆面为锯齿形结构的泡沫金属材料,且明显优于迎爆面为平面结构的泡沫金属材料。

     

液态燃料对连续旋转爆轰发动机爆轰特性的影响

为了研究液态燃料对连续旋转爆轰发动机爆轰特性的影响,采用CE/SE方法对以汽油/富氧空气为燃料的CRDE进行数值模拟,分析了不同液滴半径、当量比对爆轰性能参数的影响。计算结果表明:随着液滴半径增大,爆轰压力峰值、温度峰值以及爆轰波速度均降低,且压力峰值与温度峰值在爆轰波传播过程中出现不稳定现象;当增大到70 μm时,爆轰波将无法成功起爆。随着当量比的增大,CRDE爆轰波速度及平均推力增大,爆轰压力、温度以及气相周向速度的峰值均先增大后减小。在当量比1.1附近,爆轰压力与温度的峰值出现极大值;而气相周向速度峰值的极大值出现在当量比0.9附近。基于燃料的比冲随着当量比增大而减小。     

Parametric study of double cellular detonation structure

A parametric numerical study is performed of a detonation cellular structure in a model gaseous explosive mixture whose decomposition occurs in two successive exothermic reaction steps with markedly different characteristic times. Kinetic and energetic parameters of both reactions are varied in a wide range in the case of one-dimensional steady and two-dimensional (2D) quasi-steady self-supported detonations. The range of governing parameters of both exothermic steps is defined where a “marked” double cellular structure exists. It is shown that the two-level cellular structure is completely governed by the kinetic parameters and the local overdrive ratio of the detonation front propagating inside large cells. Furthermore, since it is quite cumbersome to use detailed chemical kinetics in unsteady 2D case, the proposed work should help to identify the mixtures and the domain of their equivalence ratio where double detonation structure could be observed.     

爆轰产物状态方程的水下爆炸反演理论研究

由于水下爆炸过程中爆轰产物的信息以水中压缩波形式向外传递,本文旨在探讨如何利用水下爆炸试验数据确定爆轰产物的状态方程。相较于常规圆筒试验,水下爆炸试验具有装置简单成本低、装药尺寸限制少、测定压力范围更广的特点,更适用于大药量或非理想炸药的现场测试。本文从水中冲击波轨迹和波后压力时程曲线出发,发展了由冲击波及其波后流场还原水气界面的逆特征线算法,以及根据水气界面确定爆轰产物状态方程的遗传算法。与水下爆炸正演结果对比,发现逆特征线法可以较准确地还原水气界面的位置和压力参数,有效压力下限可达2 MPa,远低于圆筒试验的测试下限0.1GPa。根据水气界面的反演结果,遗传算法也能稳定地优化JWL方程参数,8种常用炸药的等熵衰减压力误差在爆压至0.01 GPa的区间内都小于3%。结果表明,利用本文的逆特征线算法和遗传算法,理论上可以反演出压力范围较宽、准确性较高的爆轰产物状态方程。     

Regular reflection of a shock wave from a solid wall in a stream of fuel mixture

The two-dimensional stationary problem of regular reflection of a shock wave from a plane solid wall in a fuel gas mixture is examined in the case when the mixture is ignited at the intersection of the incident wave with the wall and a flame front is formed behind the reflected shock wave. The shock waves and the flame front are considered plane surfaces of discontinuity. The fuel mixture and the reaction products are considered perfect, inviscid, and non-heat-conducting gases.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 161–163, July–August, 1978.     

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.