爆炸式电磁感应脉冲发生器

为了探索脉冲发生器新的技术方法，在传统脉冲发生器的基础上，提出了一种依靠爆炸驱动的电磁感应脉冲发生器。介绍了发生器的工作过程，对发生器中炸药的爆炸和冲击过程进行了计算和数值模拟，建立了带有初始电压和初始静磁场的发生器的工作电路模型，得出了感应电压的计算方法。设计了一种通过永磁体提供初始静磁场的脉冲发生器，并分别对装有两种不同炸药的发生器进行了实验。实验表明:爆速较高的炸药驱动发生器可产生峰值更高的电压脉冲。实验结果偏低于计算结果，原因是理论计算中简化了磁芯磁场和冲击波速度。     

多点导通爆炸逻辑网络闭合开关研制

应用爆炸逻辑网络知识,依据金属射流击穿绝缘薄膜导通放电原理,研制了一种多点导通爆炸逻辑网络闭合开关。在小型脉冲功率发生器上的短路实验及同步性测量结果表明,该开关电感小于5nH,能够承受80kV以上的高电压和兆安级以上的大电流,同步性为55ns,其形状为平板状,便于与平行板状传输线连接。并与单点导通的雷管爆炸闭合开关作了比较,结果表明,多点导通爆炸逻辑网络闭合开关的电感低于单点导通的雷管爆炸闭合开关。上述结果进一步说明,多点导通爆炸逻辑网络闭合开关具有低电感、耐高电压大电流以及便于与平行板传输线连接的特点,在要求回路电感非常小、使用单开关的脉冲功率发生器中具有非常好的应用前景。     

电爆炸丝断路开关性能实验研究

详细研究了初始能量、电爆炸丝截面积和丝长度等参数对含电爆炸丝断路开关的电感储能脉冲功率调节系统输出电流、电压的影响,并将实验结果与数值模拟结果进行了比较,给出了相关的结果。实验结果表明初始能量爆炸丝参数对丝电流、丝电压的影响有一定的规律。     

新型功率调节系统中的炸药驱动断路开关技术

介绍了两种炸药驱动断路开关的基本工作原理及主要性能。提出了在以爆炸磁压缩发生器为能源的脉冲功率调节系统中，采用两级爆炸断路开关。估算并比较了采用两级断路开关和只用一级爆炸丝断路开关时爆炸丝开关中的能量损耗。     

单金属丝电爆炸实验系统研究

概述了实验系统设计的原则，依此研制了小型脉冲功率系统，得到了金属丝电爆炸的实验结果。     

表面涂层对非晶薄带爆炸焊接温度影响探讨

针对在非晶薄带爆炸复合制备块体非晶复合材料过程中涂层对温度的影响，提出对非晶薄带实施涂层后再进行爆炸复合。利用放缩法将涂层后的薄带简化为均匀材料，并对30 m厚的Fe78B13Si9非晶涂层前、后爆炸焊接层内温度场进行系列分析计算，表明:(1) 高速撞击产生的热量主要集中在涂铜层上，涂层处理能够显著减小界面撞击引起的热影响区域；(2) 相对于非涂层的非晶爆炸复合，文中方案平均温升降低约280 K；(3) 铜涂层后，碰撞界面冷却速率高达107 K/s。研究表明，具有表面涂层的非晶薄带在爆炸复合制备层合块体非晶复合材料过程中，能够更好地保持非晶材料的非晶结构，并有效扩大爆炸焊接窗口。     

爆炸荷载下钢筋混凝土梁的变形和破坏

利用爆炸压力模拟器进行钢筋混凝土简支梁爆炸冲击实验，详细介绍了实验设计，通过实验系统分析了钢筋混凝土(RC)梁变形破坏特征以及钢筋作用机理和对变形破坏的影响，并建立了RC梁的分离式有限元模型，利用LS-DYNA分析了实验过程，对计算结果与实验结果进行了比较，分析了误差产生的原因，得到了爆炸冲击荷载作用下RC梁的损伤破坏特征和机理，可为毁伤评估和结构抗爆设计提供参考。     

水下爆炸中气泡射流壁压特性实验研究

水下爆炸气泡射流载荷是中近场水下爆炸壁压载荷的重要组成部分, 将水下爆炸气泡射流简化为一段高速水柱来研究水下爆炸气泡射流载荷特性是研究水下爆炸气泡射流载荷的主要手段。本文基于腔内爆炸提出了一种新的高速水射流实验方法，并给出了实验装置设计、实验方法以及实验系统。基于实验系统，开展了不同工况下高速水射流的实验研究，研究了腔口位置、腔深对水射流形态的影响，并对水射流的形态形成因素进行了分析。使用压电型壁压传感器测得了水射流冲击壁压，给出了水射流冲击壁压的特性及其特点。实验结果表明:腔口位置与腔深是影响水射流端面形态的重要因素；生成的高速水射流冲击壁压峰值满足水锤理论。基于腔内爆炸的高速水射流实验方法能够应用于包括水下爆炸气泡射流在内的高速水射流形态、壁压特性的研究。     

惰性气体N2/CO2抑制瓦斯爆炸实验研究

为探究惰性气体(N₂和CO₂)对瓦斯气体爆炸影响，采用中型尺寸瓦斯爆炸实验装置，在N₂及CO₂体积分数为0%、9%、14%工况下开展了瓦斯爆炸实验研究，获取了N₂和CO₂对矿井瓦斯抑爆特性的影响规律，并针对瓦斯爆炸过程中惰性气体N₂和CO₂对爆炸超压变化的影响及爆炸抑制效果进行了对比分析。结果表明:随着初始混合气体中惰性气体N₂或CO₂含量的升高，瓦斯爆炸超压均明显降低，CO₂的抑爆效果优于N₂；N₂和CO₂对较高浓度瓦斯气的抑爆效果更为显著。     

电感储能脉冲功率调节系统的研究

研制了一种小型的电感储能脉冲功率调节系统,它能把低阻抗的爆炸压缩装置的输出能量有效地转换成为适合于电子束和等离子体物理实验需要的高电压大功率脉冲。我们分析了以电爆炸丝断路开关为基础的电感储能功率调节系统,并给出了它的工作性能及实验结果。当储能电感的磁通量达到0.1Wb时,在40的负载电阻上可获得上升前沿为50ns、幅度大于600kV的脉冲电压。该系统结构紧凑,运行成本低,重复性好。已建立了该系统相应的理论模型和计算程序,数值模拟结果和实验结果一致。     

Mechanisms of detonation transmission in layered H2-O2 mixtures

When a plane detonation propagating through an explosive comes into contact with a bounding explosive, different types of diffraction patterns, which may result in the transmission of a detonation into the bounding mixture, are observed. The nature of these diffraction patterns and the mode of detonation transmission depend on the properties of the primary and bounding explosives. An experimental and analytical study of such diffractions, which are fundamental to many explosive applications, has been conducted in a two channel shock tube, using H₂-O₂ mixtures of different equivalence ratios as the primary and bounding or secondary explosive. The combination of mixtures was varied from rich primary / lean secondary to lean primary / rich secondary since the nature of the diffraction was found to depend on whether the Chapman-Jouguet velocity of the primary mixture,D _p, was greater than or less than that of the secondary mixture,D _s. Schlieren framing photographs of the different diffraction patterns were obtained and used to measure shock and oblique detonation wave angles and velocities for the different diffraction patterns, and these were compared with the results of a steady-state shock-polar solution of the diffraction problem. Two basic types of diffraction and modes of detonation reinitiation were observed. WhenD _p>D _s, an oblique shock connecting the primary detonation to an oblique detonation in the secondary mixture was observed. WithD _p<D _s, two modes of reinitiation were observed. In some cases, ignition occurs behind the Mach reflection of the shock wave, which is transmitted into the secondary mixture when the primary detonation first comes into contact with it, from the walls of the shock tube. In other cases, a detonation is initiated in the secondary mixture when the reflected shock crosses the contact surface behind the incident detonation. These observed modes of Mach stem and contact surface ignition have also been observed in numerical simulations of layered detonation interactions, as has the combined oblique-shock oblique-detonation configuration whenD _p>D _s. WhenD _p>D _s, the primary wave acts like a wedge moving into the secondary mixture with velocityD _p after steady state has been reached, a configuration which also arises in oblique-detonation ramjets and hypervelocity drivers.     

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0.1 GPa。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。     

铝粉含量和粒度对CL-20含铝炸药水中爆炸反应特性的影响

为了研究CL-20基含铝炸药的爆炸反应机理，利用水中爆炸实验，测量了不同铝粉含量和粒度的CL-20炸药水中爆炸的冲击波参数、二次压力波参数，计算了冲击波能和气泡能。结果表明，水中爆炸的冲击波能和气泡能表征了爆轰和二次反应两个阶段的炸药爆炸能量分配，CL-20炸药中的铝粉主要在二次反应阶段发生反应，只有少部分的铝粉参与了早期的爆轰反应。气泡脉动形成的二次压力波能描述铝粉含量和粒度对二次反应过程的影响，铝粉含量对炸药的二次反应有显著的影响；铝粉粒度对炸药的水下爆炸的初始冲击波参数、冲击波能和气泡能的影响很小，对铝粉与爆轰产物的二次反应速率影响较大。     

The criterion of the existence or inexistence of transverse shock wave at wedge supported oblique detonation wave

A simplified theoretic method and numerical simulations were carried out to investigate the characterization of propagation of transverse shock wave at wedge supported oblique detonation wave.After solution validation,a criterion which is associated with the ratio Φ (u 2 /u CJ) of existence or inexistence of the transverse shock wave at the region of the primary triple was deduced systematically by 38 cases.It is observed that for abrupt oblique shock wave (OSW)/oblique detonation wave (ODW) transition,a transverse shock wave is generated at the region of the primary triple when Φ < 1,however,such a transverse shock wave does not take place for the smooth OSW/ODW transition when Φ > 1.The parameter Φ can be expressed as the Mach number behind the ODW front for stable CJ detonation.When 0.9 < Φ < 1.0,the reflected shock wave can pass across the contact discontinuity and interact with transverse waves which are originating from the ODW front.When 0.8 < Φ < 0.9,the reflected shock wave can not pass across the contact discontinuity and only reflects at the contact discontinuity.The condition (0.8 < Φ < 0.9) agrees well with the ratio (D ave /D CJ) in the critical detonation.     

Supersonic flow of combustible gas mixture past sphere with account for ignition delay time

Assume an axisymmetric blunt body or a symmetric profile is located in a uniform supersonic combustible gas mixture stream with the parameters M₁, p₁, and T₁. A detached shock is formed ahead of the body and the mixture passing through the, shock is subjected to compression and heating. Various flow regimes behind the shock wave may be realized, depending on the freestream conditions. For low velocities, temperatures, or pressures in the free stream, the mixture heating may not be sufficient for its ignition, and the usual adiabatic flow about the body will take place. In the other limiting case the temperature behind the adiabatic shock and the degree of gas compression in the shock are so great that the mixture ignites instantaneously and burns directly behind the shock wave in an infinitesimally thin zone, i. e., a detonation wave is formed. The intermediate case corresponds to the regime in which the width of the reaction zone is comparable with the characteristic linear dimension of the problem, for example, the radius of curvature of the body at the stagnation point.The problem of supersonic flow of a combustible mixture past a body with the formation of a detonation front has been solved in [1, 2]. The initial mixture and the combustion products were considered perfect gases with various values of the adiabatic exponent .These studies investigated the effect of the magnitude of the reaction thermal effect and flow velocity on the flow pattern and the distribution of the gasdynamic functions behind the detonation wave.In particular, the calculations showed that the strong detonation wave which is formed ahead of the sphere gradually transforms into a Chapman-Jouguet wave at a finite distance from the axis of symmetry. For planar flow in the case of flow about a circular cylinder it is shown that the Chapman-Jouguet regime is established only asymptotically, i. e., at infinity.This result corresponds to the conclusions of [3, 4], in which a theoretical analysis is given of the asymptotic behavior of unsteady flows with planar, spherical, and cylindrical detonation waves.Available experimental data show that in many cases the detonation wave does not degenerate into a Chapman-Jouguet wave as it decays, bur rather at some distance from the body it splits into an adiabatic shock wave and a slow combustion front.The position of the bifurcation point cannot be determined within the framework of the zero thickness detonation front theory [1], and for the determination of the location of this point we must consider the structure of the combustion zone in the detonation wave. Such a study was made with very simple assumptions in [5].The present paper presents a numerical solution of the problem of combustible mixture flow about a sphere with a very simple model for the structure of the combustion zone, in which the entire flow behind the bow shock wave consists of two regions of adiabatic flow-an induction region and a region of equilibrium flow of products of combustion separated by the combustion front in which the mixture burns instantaneously. The solution is presented only for subsonic and transonic flow regions.     

Population inversion behind a detonation wave propagating in a variable-density medium

The creation of an active medium by means of detonation has been investigated on a number of occasions. It was suggested that one could use the expansion of the detonation products of an acetylene-air mixture in vacuum [1] or the cooling of the detonation products of a mixture of hydrocarbons and air through a nozzle [2, 3]. In [4], the detonation of a solid high explosive was used to produce population inversion in the gas mixture CO₂-N₂-He(H₂O). Stimulated emission from HF molecules was observed in [5] behind the front of an overdriven detonation wave propagating in an F₂-H₂-Ar mixture in a shock tube. Population inversion behind a detonation wave was studied in H₂-F₂-He mixtures in [6–8] and in H₂-Cl₂-He mixtures in [9] with energy release on a plane and on a straight line in a medium with constant density. Similar problems were solved for shock waves propagating in both a homogeneous gaseous medium [7, 10] and in the supersonic part of an expanding nozzle. In the present paper, we study theoretically population inversion behind an overdriven detonation wave propagating in a mixture (fine carbon particles + acetylene + air) which flows through a hypersonic nozzle. The propagation of detonation in media with variable density and initial velocity was considered, for example, in [11, 12]. Analysis of the gas parameters behind a detonation wave propagating in a medium with constant density (for a given fuel) showed that the temperature difference across the detonation front is insufficient to produce population inversion of the vibrational levels of the CO₂ molecule.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 65–71, January–February, 1980.I am grateful to V. P. Korobeinikov for a helpful discussion of the results.     

Initiation of gaseous detonation by a high speed body

The investigation of detonation initiated by the passage of a high speed body is presented. The following experiments are carried out for mixture of C₂H₂ + 2.5 O₂ passed by a hemispherical or blunt cylinder with velocity ranging from 800 to 1400 m/s. A new mechanism of the transformation of shock waves to detonation waves is observed at near-critical regimes. The analytical correlation between the aerodynamical characteristics of high speed body and the physico-chemical parameters of explosive mixture is proposed as the initiation criterion of gaseous detonation. Analytical and experimental data agree well with each other.This article was processed using Springer-Verlag T_EX Shock Waves macro package 1.0 and the AMS fonts, developed by the American Mathematical Society.     

压装TNT的SDDT特性研究

本文报告厂将水箱技术同改型隔板试验结合起来研究凝聚炸药由冲击波经爆燃向爆轰转变(SDDT)的方法。实测了压装TNT(装药密度1.615g/cm~3)的SDDT曲线,并确定了其燃烧阈值和爆轰阈值(分别为2.1GPa和2.5-3.0GPa)。按照流体动力学特征线法计算了不同强度起爆冲击波作用下在炸药中形成的一系列冲击波、爆燃波和爆轰波的剖面,这些剖面反映了炸药SDDT的基本特征。所取得的信息对于炸药的实际应用和对冲击波起爆的深入研究均有价值。     

Detonation wave initiated by explosive condensation of supersaturated carbon vapor

An experimental study of the influence of condensation of supersaturated carbon vapor formed behind reflected shock waves on the process of propagation of a shock wave and formation of a detonation wave of condensation is carried out. Highly supersaturated carbon vapor was formed from thermal decay of unstable carbon suboxide C₃O₂ → C + 2CO behind a shock wave in mixtures containing 10–30% C₃O₂ in Ar. This reaction was followed by fast growth of condensed carbon particles, accompanied by heat release. Experiments have shown a considerable temperature and pressure increase in the narrow zone behind the wave front, resulting in shock wave amplification and transition to a detonation-like regime. An analysis of the kinetics and heat release in the given conditions and calculations based upon one-dimensional detonation theory have shown that in a mixture of 10% C₃O₂ + Ar, insufficient heat release resulted in a regime of “overdriven detonation”. In a mixture of 20% C₃O₂ + Ar a very good coincidence of measured values of pressure and wave velocity with calculated Chapman–Jouguet parameters is observed. In a 30% C₃O₂ + Ar mixture, an excess heat release caused a slow down of the effective condensation rate and a regime of “underdriven detonation” is observed.