起爆方式对子母式战斗部破片速度影响的数值分析

为研究起爆方式对子母式战斗部破片速度分布及增益的影响,利用LS-DYNA软件对子母式战斗部的爆炸进行了数值模拟,并就不同起爆方式对破片速度分布及增益的变化进行了对比分析与研究.结果表明,两端同时偏心起爆的方式为最优起爆方式,破片速度增益最大;其次是偏心线起爆;最后是一端偏心起爆,可为战斗部设计提供参考.     

装药结构对破片初速影响特性

为了满足低附带战斗部的毁伤效果,将炸药与破片混合形成新型混合装药模式。在混合装药模式中,为了研究不同装药结构对破片初速的影响特性,设计了3种不同装药结构并进行数值模拟和试验;对比发现,数值模拟与试验结果规律吻合,破片的初速与装药结构有一定的关系。根据试验数据拟合了3种不同装药结构中破片最大速度曲线对比图,通过分析得出:不同装药结构中,炸药与破片分层越多,爆轰瞬间,相邻炸药所产生爆轰效果会发生叠加,爆轰波对破片的驱动效果会增强,则破片的初速也就越大。     

爆轰波斜冲击作用下破片飞散特性研究

为研究非对称结构战斗部的破片飞散特性,利用斜激波理论对爆轰波作用于壳体表面的过程进行研究,并利用自由面速度倍增定律对波在自由面反射后质点速度的计算进行简化,得到了破片飞散角的计算模型。利用D型战斗部试验数据对计算模型进行验证,结果表明,斜激波理论计算得到的破片飞散与试验结果吻合很好;当入射角较小时,壳体飞散角与入射角成线性关系。     

活性破片飞散特性及毁伤效应研究

为了掌握活性破片的空间飞散特性及毁伤效能,采用数值仿真与试验相结合的方法研究了某预制活性破片战斗部在爆炸作用下的飞散特性,得到了活性破片的空间分布和初始速度分布参数的有关数据,分析了活性破片对靶板的毁伤规律.结果表明:活性破片战斗部在起爆300 μs后,70％的活性破片速度分布在1 500～2 000 m/s;50％的...     

杀伤战斗部破片定向飞散特性研究

研究了钢预制破片壳体在四种装药爆轰驱动下的飞散特性。求得了使破片飞行路径呈平行型的预制破片壳体的临界半径及相应的破片初始速度。     

二维波束控制引信与定向战斗部配合

将相控阵天线引入引信中,实现了引信天线波束的二维控制。研究了相控阵天线的基本原理,给出了波长、扫描范围和阵元数等参数的值。研究了目标脱靶方位识别原理,分析了定向战斗部破片动态杀伤区的散布特性。把定向战斗部中心破片飞向角与引信波束指向角之差作为起爆控制量,提出了一种相控阵引信与定向战斗部配合的方法。仿真结果表明,这种方法能精确控制战斗部起爆时机,提高引战配合效率。     

可变形定向破片战斗部模型试验和数值模拟研究

基于可变形定向破片战斗部的作用原理,设计了试验结构模型,并对其进行了静爆试验研究。根据试验结果,建立了有限元分析模型,利用LS-DYNA程序对可变形定向战斗部变形过程以及破片的飞散过程进行了数值模拟。结果表明,在目标方向破片密度和速度都有较大幅度增益,数值模拟与试验结果比较吻合。     

高速破片撞击充液容器形成液压水锤的试验研究

为研究高速破片撞击充液容器形成的液压水锤效应，设计一套试验装置和测试方法，试验破片撞击充液容器产生空腔的变化过程、液体中不同位置处的压力变化以及前后面板的变形情况。试验发现：破片撞击容器后面板时会出现一圈空化气泡，气泡在后面板内表面从撞击点位置迅速沿径向扩展；液压水锤初始冲击阶段，距离撞击点较近区域在初始冲击波压力脉冲过后会出现一个较大负压，而距离撞击点较远区域不受负压影响；破片撞击速度对容器前面板最大变形影响较小，变形范围随着撞击速度的增大沿撞击点向四周扩展。后面板的最大变形及变形范围都随着破片撞击速度的增大而变大。     

金属圆管内爆轰波对碰部位速度的影响因素

利用LS-DYNA动力有限元程序对张世文等人做的金属圆管内爆轰波相互作用效应实验进行数值模拟,其模拟结果与实验结果具有较好的一致性。在此基础上着重分析了装药和金属圆管壁厚对金属圆管内爆轰波对碰部位速度的影响规律,为弹丸的设计提供了参考。     

定向杀伤弹药

定向杀伤弹药是通过预制杀伤体产生的杀伤场来毁伤目标的弹药。它已成为杀伤弹药的主要发展方向之一。预制杀伤体在毁伤目标过程中产生不同形状的破片场。定向杀伤弹药可以根据破片场的形状,大致分为3类:环形场定向杀伤弹药、轴线场定向杀伤弹药和辐射场定向杀伤弹药(图1)。     

Effects of total pressures and equivalence ratios on kerosene/air rotating detonation engines using a paralleling CE/SE method

In this paper, the kerosene/air rotating detonation engines(RDE) are numerically investigated, and the emphasis is laid on the effects of total pressures and equivalence ratios on the operation characteristics of RDE including the initiation, instabilities, and propulsive performance. A hybrid MPI + OpenMP parallel computing model is applied and it is proved to be able to obtain a more effective parallel performance on high performance computing(HPC) systems. A series of cases with the total pressure of 1 MPa, 1.5 MPa, 2 MPa, and the equivalence ratio of 0.9, 1, 1.4 are simulated. On one hand, the total pressure shows a significant impact on the instabilities of rotating detonation waves. The instability phenomenon is observed in cases with low total pressure (1 MPa) and weakened with the increase of the total pressure. The total pressure has a small impact on the detonation wave velocity and the specific impulse. On the other hand, the equivalence ratio shows a negligible influence on the instabilities, while it affects the ignition process and accounts for the detonation velocity deficit. It is more difficult to initiate rotating detonation waves directly in the lean fuel operation condition. Little difference was observed in the thrust with different equivalence ratios of 0.9, 1, and 1.4. The highest specific impulse was obtained in the lean fuel cases, which is around 2700 s. The findings could provide insights into the understanding of the operation characteristics of kerosene/air RDE.     

Application of Two-dimensional Viscous CE/SE Method in Calculation of Two-phase Detonation

The method of two-dimensional viscous space-time conservation element and solution element (CE/SE) can be used to calculate the gas-liquid two-phase interior flow field in pulse detonation engine (PDE). In this paper, the evolution of the detonation wave and the distribution of its physical parameters were analyzed. The numerical results show that the change of axial velocity of gas is the same as that of detonation pressure. The larger the liquid droplet radius is, the longer the time to get stable detonation wave is. The calculated results coincide with the experimented results better.     

Experimental study on the detonation process of a pulse detonation engine with ionized seeds

An experimental platform of a pulse detonation engine (PDE) was established to study the effect of different K₂CO₃ ionized seed mass contents on the detonation process. The pressure and ion concentration were detected in the detonation process of the PDE with different contents of ionized seeds. The initiation process of the PDE at different ignition frequencies was studied. The results show that the gas conductivity in the detonation process increased by adding ionized seeds to the PDE tube, and the conductivity increased with the increase in ionized seed mass content. With the increase in ionized seed mass content, the range of the conductivity decreased. The PDE was successfully ignited and formed a stable detonation wave at ignition frequencies of 5 Hz and 10 Hz, and the peak pressure of the stable detonation with the ignition frequency of 5 Hz was 17% higher than that with an ignition frequency of 10 Hz. The detonation wave intensity was weakened and degenerated to a shock wave that propagated in the tube without the fuel filled at the ignition frequency of 20 Hz.     

Experimental research on the instability propagation characteristics of liquid kerosene rotating detonation wave

In order to study the instability propagation characteristics of the liquid kerosene rotating detonation wave (RDW), a series of experimental tests were carried out on the rotating detonation combustor (RDC) with air-heater. The fuel and oxidizer are room-temperature liquid kerosene and preheated oxygen-enriched air, respectively. The experimental tests keep the equivalence ratio of 0.81 and the oxygen mass fraction of 35% unchanged, and the total mass flow rate is maintained at about 1000 g/s, changing the total temperature of the oxygen-enriched air from 620 K to 860 K. Three different types of instability were observed in the experiments: temporal and spatial instability, mode transition and re-initiation. The interaction between RDW and supply plenum may be the main reason for the fluctuations of detonation wave velocity and pressure peaks with time. Moreover, the inconsistent mixing of fuel and oxidizer at different circumferential positions is related to RDW oscillate spatially. The phenomenon of single-double-single wave transition is analyzed. During the transition, the initial RDW weakens until disappears, and the compression wave strengthens until it becomes a new RDW and propagates steadily. The increased deflagration between the detonation products and the fresh gas layer caused by excessively high temperature is one of the reasons for the RDC quenching and re-initiation.     

Influence of propagation direction on operation performance of rotating detonation combustor with turbine guide vane

Due to the pressure gain combustion characteristics, the rotating detonation combustor (RDC) can enhance thermodynamic cycle efficiency. Therefore, the performance of gas-turbine engine can be further improved with this combustion technology. In the present study, the RDC operation performance with a turbine guide vane (TGV) is experimentally investigated. Hydrogen and air are used as propellants while hydrogen and air mass flow rate are about 16.1 g/s and 500 g/s and the equivalence ratio is about 1.0. A pre-detonator is used to ignite the mixture. High-frequency dynamic pressure transducers and silicon pressure sensors are employed to measure pressure oscillations and static pressure in the combustion chamber. The experimental results show that the steady propagation of rotating detonation wave (RDW) is observed in the combustion chamber and the mean propagation velocity is above 1650 m/s, reaching over 84% of theoretical Chapman-Jouguet detonation velocity. Clockwise and counterclockwise propagation directions of RDW are obtained. For clockwise propagation direction, the static pressure is about 15% higher in the combustor compared with counterclockwise propagation direction, but the RDW dominant frequency is lower. When the oblique shock wave propagates across the TGV, the pressure oscillations reduces significantly. In addition, as the detonation products flow through the TGV, the static pressure drops up to 32% and 43% for clockwise and counterclockwise propagation process respectively.     

Effect of wave shaper on reactive materials jet formation and its penetration performance

Wave shaper effect on formation behavior and penetration performance of reactive liner shaped charge (RLSC) are investigated by experiments and simulations. The reactive materials liner with a density of 2.3 g/cm³ is fabricated by cold pressing at a pressure of 300 MPa and sintering at a temperature of 380 °C. Experiments of the RLSC with and without wave shaper against steel plates are carried out at standoffs of 0.5, 1.0, and 1.5 CD (charge diameter), respectively. The experimental results show that the penetration depths and structural damage effects of steel plates decrease with increasing the standoff, while the penetration depths and the damage effects of RLSC without wave shaper are much greater than that with wave shaper at the same standoff. To understand the unusual experimental results, numerical simulations based on AUTODYN-2D code are conducted to discuss the wave shaper effect, including the propagation behavior of detonation wave, the velocity and temperature distribution of reactive jet, and penetration depth of reactive jet. The simulations indicate that, compared with RLSC without wave shaper, there is a higher temperature produced inside reactive jet with wave shaper. This unusual temperature rise effects are likely to be an important mechanism to cause the initiation delay time of reactive jet to decline, which results in significantly decreasing its penetration performance.     

Shock initiation performance of NTO-based polymer bonded explosive

3-nitro-1,2,4-tri-azol-5-one (NTO) is a high energy insensitive explosive. To study the shock initiation process of NTO-based polymer bonded explosive JEOL-1 (32%octahydro-1,3,5,7-tetranitro-1,3,5,7-tetrazocine (HMX), 32% NTO, 28% Al and 8% binder system), the cylinder test, the gap experiments and numerical simulation were carried out. Firstly, we got the detonation velocity (7746 m/s) and the parameters of Jones-Wilkins-Lee (JWL) equation of state (EOS) for detonation product by cylinder test and numerical simulation. Secondly, the Hugoniot curve of unreacted explosive for JEOL-1 was obtained calculating the data of pressure and time at different Lagrangian positions. Then the JWL EOS of unreacted explosive was obtained by utilizing the Hugoniot curve as the reference curve. Finally, we got the pressure growth history of JEOL-1 under shock wave stimulation and the parameters of the ignition and growth reaction rate equation were obtained by the pressure-time curves measured by the shock-initiation gap experiment and numerical simulation. The determined trinomial ignition and growth model (IG model) parameters can be applied to subsequently simulation analysis and design of insensitive ammunition with NTO-based polymer bonded explosive.     

A quasi-isentropic model of a cylinder driven by aluminized explosives based on characteristic line analysis

A quasi-isentropic study on the process of driving a cylinder with aluminized explosives was carried out to examine the influence of the aluminum (Al) reaction rate on cylinder expansion and the physical parameters of the detonation products. Based on the proposed quasi-isentropic hypothesis and relevant isentropic theories, the characteristic lines of aluminized explosives driving a cylinder were analyzed, and a quasi-isentropic model was established. This model includes the variation of the cylinder wall velocity and the physical parameters of the detonation products with the Al reaction degree. Using previously reported experimental results, the quasi-isentropic model was verified to be applicative and accurate. This model was used to calculate the physical parameters for cylinder experiments with aluminized cyclotrimethylenetrinitramine explosives with 15.0 % and 30.0 % Al content. The results show that this quasi-isentropic model can be used not only to calculate the cylinder expansion rule or Al reaction degree, but also to calculate the physical parameters of the detonation products in the process of cylinder expansion. For explosives with 15.0 % and 30.0 % Al, 24.3 % and 18.5 % of the Al was found to have reacted at 33.9 μs and 34.0 μs, respectively. The difference in Al content results in different reaction intensity, occurrence time, and duration of two forms of reaction (diffusion and kinetic) between the Al powder and the detonation products; the post-detonation burning reaction between the Al powder and the detonation products prolongs the positive pressure action time, resulting in a continuous rise in temperature after detonation.     

1D study of the detonation phenomenon and its influence on the interior ballistics of the combustion light gas gun

One-dimensional simulations with a detailed hydrogen-oxygen reaction mechanism have been performed to investigate detonation phenomenon in a combustion light gas gun (CLGG). Convection fluxes of the Navier-Stokes equations are solved using the WAF (weighted average flux) scheme HLLC Riemann solver. A high resolution fifth-order WENO scheme for the variable extrapolation at the volume interface and a fourth-order Runge-Kutta scheme for the time advancement are used. Validation tests of the stoichiometric hydrogen-oxygen deflagration to detonation transition process shows good agreement between the computed results and the analytical and documented solutions, demonstrating the reliability on the detonation simulation of the current scheme. Simulation results of the interior ballistic process of the CLGG show that the flame propagation experiences three distinct stages. The blast detonation wave causes a high-pressure shock and hazardous oscillations in the chamber and makes the projectile accelerate with fluctuations, but has only a small improvement to the muzzle velocity.