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1.
动能杆定向抛撒规律的数值模拟   总被引:2,自引:0,他引:2  
针对反导动能杆的定向抛撒 ,应用数值模拟软件AUTODYN 2D对动能杆的定向爆炸驱动和相互作用过程进行了数值仿真 ,获得了杆条抛撒速度和飞散角等变化规律。即在杆条排布结构不变的情况下 ,随装药弧度的减小 ,杆条的飞散角增大 ,而杆条飞散的平均速度则随装药弧度的减小而减小。与所进行的动能杆定向抛撒装置试验对比 ,试验结果与数值模拟结果基本一致。  相似文献   

2.
根据弹丸在舱内运动及出舱后弹丸与炮弹之间的运动特点,建立了完整的子母弹抛撒飞行力学模型.该模型的建立,便于研究活塞式动态抛撒的子母弹的运动特征,以及子弹在舱内和舱外的运动规律.另外,根据所建立的模型和作战性能指标,可以估算燃烧舱内所需要的火药量和舱内受到的压力,从而选取所需的火药量.  相似文献   

3.
燃料爆炸抛撒成雾的实验与数值研究   总被引:16,自引:2,他引:14  
为了合理设计云雾爆轰装置 ,对液体燃料爆炸抛撒规律作了实验与数值模拟研究。获得 6~ 2 5 0kgFAE装置云雾形成的若干重要实验数据。通过实验数据分析给出了云雾膨胀的相似律 ,并研究了爆炸抛撒过程中近场与远场阶段特性 :用一个简化的解析模型描述了液体燃料的近场膨胀 ,给出了液体燃料在加速阶段的极限速度 ;用数值方法研究了远场云雾的物理特性 ,给出了云雾速度场及云雾内部燃料浓度与燃料蒸汽浓度的分布。  相似文献   

4.
根据弹丸在舱内运动及出舱后弹丸与炮弹之间的运动特点,建立了完整的子 母弹抛撒飞行力学模型. 该模型的建立,便于研究活塞式动态抛撒的子母弹的运动特征,以 及子弹在舱内和舱外的运动规律. 另外,根据所建立的模型和作战性能指标,可以估算燃烧 舱内所需要的火药量和舱内受到的压力,从而选取所需的火药量.  相似文献   

5.
摘要:采用LS-DYNA非线性动力学有限元程序,对某抛撒机构中的能量转换核心装置—波纹管在均布内压作用下的动态膨胀过程进行了数值分析,获得了波纹管动态响应规律;系统的考察了各种因素对波纹管的变形模式及其应力应变变化规律的影响;模拟了波纹管在内部压力和外围子弹群等共同作用下的耦合变形运动过程,对内弹道抛撒全过程进行了模拟,获得了波纹管耦合变形规律和子弹抛撒特性。模拟计算结果与试验现象基本一致。  相似文献   

6.
对具有轴向初始速度即竖直下抛液体燃料的爆炸抛撒云雾形成过程进行了数值研究。近场的数据来自丁珏等的工作,以此数据作为远场初始参数。远场是燃料液滴与空气、燃料蒸汽、不同尺寸的液滴颗粒组成的多相体系之间的相互作用的过程。液滴的直径比较小,把液滴看成连续介质,且相互作用只考虑液滴的蒸发、破碎、碰撞聚合。轴向初速为0(静爆)时计算结果与实验结果相吻合。这说明本模型可以模拟爆炸抛撒云雾的形成过程,进而可以预估高速运动下云雾的形成过程。用以上模型计算了竖直下抛初速为100m/s、装填5kgPO的FAE装置的爆炸抛撒过程。所得的结果表明,100m/s的初速将影响云雾的最终形状及云雾内部的浓度分布。  相似文献   

7.
利用LS-DYNA三维动力有限元程序对三点起爆的翻转型EFP形成过程及三个尾翼进行了数值模拟,结果表明:数值计算结果和实验结果吻合得较好,可为弹丸设计的改进和优化提供重要的参考依据。分别选择Johnson-Cook和Steinberg两种本构模型对药型罩材料进行了数值模拟对比,结果表明:药型罩材料的本构模型选取对形成的尾翼效果有一定的影响,Steinberg本构模型与试验结果符合得更好。  相似文献   

8.
对穿甲弹准定常侵彻半无限厚靶 板的问题,提出了一个考虑应变率效应的包括带有蘑菇头的未碎弹体、弹的破碎及扩孔区、 靶的破坏和扩孔区的简化侵彻模型. 通过侵彻过程中简化模型各部分的力学守恒定律,得到 了侵彻问题的简化常微分方程组,并以分析和数值计算相结合的方法分析了弹、靶强度的应 变率效应及弹破碎应变的应变率效应对侵彻效果的影响. 数值计算结果跟实验结果对比基本 一致.  相似文献   

9.
PBX-9404的化学反应速率方程及起爆特性   总被引:1,自引:0,他引:1  
通过对炸药化学反应速率方程的分析,建立了基于Kim弹粘塑性球壳塌缩热点模型原理的三项式化学反应速率方程模型。运用遗传算法确定了反应速率方程相关参数,通过与Forest-Fire反应速率模型数值模拟结果的对比对所建模型的合理性进行了验证。将所建反应速率方程模型嵌入有限元程序对PBX-9404炸药起爆过程进行数值模拟,根据模拟结果分析了炸药遭受冲击加载后炸药孔隙率、颗粒尺寸等变化对炸药冲击起爆过程的影响。  相似文献   

10.
为研究内弹道初始阶段中心点火管燃气在膛内药床中的流动特性和传播规律,设计了可视化点传火实验平台,并进行了膛内假药床的点传火实验。基于加权本质无震荡(weighted essentially non-oscillatory, WENO)格式,构造了膛内轴对称二维内弹道两相流模型,对膛内燃气在假药床中的流动过程进行数值模拟。计算结果与可视化实验结果符合较好,全局压力平均误差为5.35%。表明数值计算准确地描述了燃气流动特性,完整地呈现了点火管燃气在假药床中的发展过程。在点火初始阶段,膛内压力径向效应明显,气相沿径向传播较快,药床药粒基本不会发生运动;随着燃气逐渐在膛内传播,膛内压力呈现径向一致、轴向梯度分布的特征,在压力梯度作用下,气相轴向速度开始占据主导,径向速度在膛底和中部区域减小为零,而固相速度随气相速度变化而变化;气相在到达弹底前,由于固相颗粒的壅塞,会提前出现速度反向波动现象。  相似文献   

11.
The two-phase flow process in an ejector was numerically and experimentally studied using R141b as a working fluid. A modified one-dimensional gas–liquid ejector model was proposed to remedy the defect in the traditional one. Gas–liquid boundary layer regions were discussed and used to close the model. Mac Cormack method is used to discrete controlling equations of gas–liquid two-phase flow in the ejector. The radial distribution of velocity and temperature, the variation of void fraction, the axial velocity variation and the influence of primary steam pressure on the mixing process were predicted with the numerical model. An experimental rig was set up to validate the model by comparing the experimental pressure distribution in the ejector with the calculating one.  相似文献   

12.
本文对动失速型非定常分离涡结构的控制方法,在低速风洞中应用相平均测压技术进行了实验研究。在二元平板模型中部安装一作俯仰振荡的扰流板产生动失速型分离涡,在其上游安装另一用作控制的小扰流板。实验结果表明,应用前置的振荡小扰流板可影响并改变动失速分离涡的强度和对流特性。在最有利的控制相位下,涡吸力峰可降低48%,涡对流时间可以推迟0.19周期。对于间歇式振荡扰流板,采用相位提前控制方式比相位滞后控制方式更有效。  相似文献   

13.
The purpose of a supersonic ejector consists in the mixing of two fluids with different stagnation pressures in order to obtain a fluid at an intermediate stagnation pressure at the discharge. Depending on the geometry of the ejector and on the operating conditions, the entrained secondary stream may reach sonic/supersonic velocities within the ejector, leading to the capping of the entrained mass flow rate for fixed reservoir conditions. Although the associated limitation of the entrainment ratio (due to choking) is a well known phenomenon, there is still a lack of understanding of the complex flow phenomena at play within supersonic ejectors, and further detailed knowledge and modeling of the choking process is necessary. This paper presents a detailed analysis of the choking phenomenon through advanced post-processing of CFD calculations which are validated with experimental results both at the global and the local scales. This in-depth investigation of the choking phenomenon within the ejector is proposed both qualitatively and quantitatively for given reservoir conditions. The complex flow signature highlighted by means of the numerical results is then investigated and corroborated through experimental shadowgraphy. Studies combining experimental results (including visualizations) with numerical simulations are rather scarce in the open literature and to the knowledge of the authors, this study is the first one that proposes such a detailed analysis. For the present ejector geometry and operating conditions, the choking phenomenology of the secondary stream is found to closely correspond to the model of the Fabri-choking early postulated in Fabri and Siestrunck (1958).  相似文献   

14.
The use of a non-steady ejector based on wave rotor technology is modeled for pulse detonation engine performance improvement and for compatibility with turbomachinery components in hybrid propulsion systems. The rotary wave ejector device integrates a pulse detonation process with an efficient momentum transfer process in specially shaped channels of a single wave-rotor component. In this paper, a quasi-one-dimensional numerical model is developed to help design the basic geometry and operating parameters of the device. The unsteady combustion and flow processes are simulated and compared with a baseline PDE without ejector enhancement. A preliminary performance assessment is presented for the wave ejector configuration, considering the effect of key geometric parameters, which are selected for high specific impulse. It is shown that the rotary wave ejector concept has significant potential for thrust augmentation relative to a basic pulse detonation engine.  相似文献   

15.
以氢气和氧气混合物为例,通过对加装收敛扩张型引射器,采用数值计算方法对脉冲爆震发动机性能进行模拟,获得了爆震管出口相对引射器喉部处于上游、中间和下游三种引射器位置对脉冲爆震发动机性能的影响规律.计算结果表明,爆震管出口相对引射器喉部处于下游时的增推效果最好,处于中间时次之,上游时效果最差.将二次流率与增推比进行比较,发现引射器的冲量增推比随引射的二次流率增加而增大.  相似文献   

16.
The impact of 12 spoiler–tab configurations, of different heights and widths, on the tip vortex generated by an oscillating NACA 0015 wing was investigated experimentally. For an oscillating wing equipped with a spoiler, the peak tangential velocity and core and total circulation were greatly reduced compared to a tab, regardless of its width, while the core radius remained largely unaffected with its center displaced vertically above the baseline wing. The most noticeable impact of a spoiler with a reduced height was its potential in alleviating the blade–vortex interaction (BVI) strength. Meanwhile, the largest favorable impact on the critical vortex flow parameters was achieved via a 25%-span spoiler–tab combination with a height of 5 and 2.5% chord, respectively. A contrary effect on the BVI suppression, especially during pitch-up, was, however, observed. The impact on the BVI can be improved by reducing the height of the spoiler at the expense of unfavorable change in the vortex strength and displacement.  相似文献   

17.
Experimental studies were performed in order to improve the understanding of the performance of ejector driven by an air-breathing pulse detonation engine (PDE) with a convergent nozzle. This research utilized a gasoline-air PDE at four different operating frequencies of 8 Hz, 10 Hz, 12 Hz and 15 Hz. The performance of PDE-ejector was quantified by thrust measurements. The effects of single ejector length and axial location on thrust augmentation were investigated. It was found that the single ejector with L/D of 2 showed the best performance and the maximum thrust augmentation occurred at a downstream placement of +1 tube diameter. The performances of two-stage and three-stage ejectors were also investigated. The results indicated that both the overlap ratio and the flow area between two stages should not be too large. The performance of the two-stage ejector was not as sensitive as single-stage ejector to axial position in current conditions. The three-stage ejector behaved better than the two-stage ejector but worse than the single-stage ejector in this work. A maximum thrust augmentation of 1.8 was obtained with an L/D of 2 at a downstream placement of +1 position and 15 Hz operating frequency.  相似文献   

18.
Conventional compression-refrigeration systems not only consume a large amount of electric power, but also cause serious environmental pollution. Among the various possible approaches in overcoming these two problems, a steam-ejector refrigeration system is believed to be most effective. This paper experimentally investigates the controlling parameters of a steam ejector, including operating conditions and the exit Mach number of the primary nozzle. Operation maps useful to the practical design are constructed from experimental results, and the empirical equations are correspondingly derived. Excessively increasing the exit Mach number of primary nozzle is unnecessary, and 4.35 should be a moderate value. With regard to the performance characteristics of the ejector itself, a steam ejector is better than an R114 ejector and is comparable to an R113 ejector. Moreover, with the use of a two-stage ejector, the required pressure to drive a steam ejector is reduced, and the low-grade heat source can be efficiently used. The results of primitive observation of the flow field are also discussed in this work.  相似文献   

19.
We present quantitative analysis of image sequences of multi-stream injection nozzle flows with several different injection geometries in an experiment simulating mixing in a chemical oxygen-iodine laser. To visualize mixing, image sequences were acquired with planar laser-induced fluorescence (PLIF) in iodine that was injected into the main flow. The injection nozzle consisted of a slot, ejector, and injector block, with rows of ejector and injector holes along the slot length. The ejector flow exits in an underexpanded state so that upon expanding it forces the slot and injector flows together to enhance mixing. For this study, the diameter and geometry of ejector holes were varied to assess their effect on mixing. Two configurations of ejector holes were used, each with two different diameters for a total of four cases with data collected at downstream stations. We carry out a quantitative mixing analysis for these configurations, using two methods to quantify the mixing. The first method considers the statistics of the PLIF image intensity histograms, which are bimodal for poorly-mixed flows and have a single peak in well-mixed flows. The second method quantifies the properties of the mixing interface. Our analysis shows that two injection schemes significantly enhance mixing by stretching the mixing interface.  相似文献   

20.
Notched spoilers have been observed to be more effective than uniform spoilers to suppress the flow-induced cavity resonance of vehicles with open sunroofs. In this study, a few mechanisms possibly involved in buffeting suppression from notched spoilers were investigated experimentally and numerically. One objective was to investigate the spatial coherence and phase of the wall pressure fluctuations downstream of notched spoilers in comparison with the same quantities for uniform spoilers. Another objective was to gather detailed measured data to allow the verification of computer simulations of the flow over the notched spoiler. Experiments were performed to measure the velocity and wall pressure fields downstream of spoilers mounted on the rigid floor of a closed test section wind tunnel. Efforts were made to reproduce the spoiler and wind tunnel geometry and boundary conditions of the experimental setup in the numerical simulations. The numerical investigation used the Lattice Boltzmann Method (LBM), with the so-called Very Large Eddy Simulation (VLES) viscosity turbulence model. The results of the numerical investigation were in satisfactory agreement with measured data at low frequencies, where buffeting is expected to occur. The results suggested that the notches break down the homogeneity of the leading edge cross-stream vortices predominantly responsible for the cavity excitation. This decreased the cross-stream coherence of the surface pressure field, thereby reducing the magnitude of the net equivalent excitation force acting over the surface downstream.  相似文献   

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