双层楔形爆炸反应装甲飞板的运动规律

根据单层爆炸反应装甲(explosive reactive armor, ERA)飞板运动规律,建立了双层楔形ERA飞板的运动模型。利用该模型对双层楔形ERA各飞板的运动规律进行分析,由此计算出飞板之间相互作用的时间。采用X光脉冲闪光测试系统对相应的实验进行记录,结果表明:根据理论模型计算结的相互作用时间与实验测得数据吻合较好,且双层平行ERA较单层ERA的飞板相互作用时间提高了5倍,双层楔形ERA的飞板相互作用时间又较双层平行ERA的提升38%。     

基于复合面/背板的平板装药防护性能

采用实验和数值模拟方法研究了橡胶复合板作为爆炸反应装甲面、背板时的防护性能,分析了两种反应装甲结构的防护机理,并与面密度相同的钢反应装甲进行了对比。实验结果表明:爆炸反应装甲面板或背板为橡胶复合板时的防护性能优于钢反应装甲,其中橡胶复合板作为背板时效果最优。数值模拟结果表明:橡胶复合板在爆炸驱动下外层钢板速度相比于钢反应装甲飞板提高16%,橡胶复合板的界面效应及其飞板间隙可以有效减小逃逸射流的长度。     

????????????????????????о?

利用X光照片对射流垂直侵彻反应装甲这一物理过程进行研究，认为爆 轰场加快了射流失稳断裂过程. 并基于射流在空气中运动断裂模型的基础上，运用弹塑性相 关理论，建立了在爆炸场中射流断裂时间模型，利用该模型得到了干扰后射的侵彻模型.     

运动板干扰长杆体分析模型

通过对长杆体与运动板相互作用物理过程分析,在长杆体与半无限靶板高速碰撞的理论模型基础上,建立了长杆与运动板作用直径损失模型,并应用杆体直径损失量来定量地描述运动薄板干扰过程,初步得到了实验和数值模拟结果验证,为研究长杆弹与运动靶板相互作用提供理论基础.     

大气/钢靶板交界处对平行入射聚能射流干扰的数值模拟

利用非线性动力学软件LS-DYNA,对聚能射流平行入射大气/钢靶板交界处的侵彻过程进行了数值模拟.通过分析数值模拟过程和结果,讨论了聚能射流头部速度和碰撞出口处横向速度的变化规律.结果表明:大气/钢靶板交界处不仅降低了聚能射流头部的轴向速度,而且使射流头部产生横向偏移,最大速度达到约1.8 km/s;后续射流横向偏移速...     

爆炸复合中起爆区不定常段的确定

对2岩石炸药的定常爆轰形成过程进行了实验研究;对起爆端稀疏波效应进行了计算。实验结果表明,距起爆端约10倍装药厚度以内为不定常爆轰区。距离起爆端小于5倍装药厚度时,飞板速度及碰撞角增幅较大,5～10倍装药厚度,两者增幅趋缓,10倍装药厚度以后,爆速、飞板速度及碰撞角逐步进入定常状态。飞板碰撞角的工程计算与实验结果的一致性较好。     

滑移爆轰问题无网格MPM法数值模拟

利用MPM(material point method)计算方法,以爆炸焊接作为实例,对炸药滑移爆轰过程和金属飞板与基板之间的碰撞变形进行了数值模拟.并将无网格MPM法的数值计算结果与近似解析公式的计算结果进行了比较,二者基本吻合,有力地证明了无网格MPM法在求解爆炸冲击问题中的有效性和健壮性.     

数值模拟油井射孔器作用过程方法研究及应用

提高射孔器性能是射孔弹厂家面临的和油田用户关心的主要问题。油井聚能射孔器的作用过程涉及爆轰波的形成、传播、爆轰波与其他介质的相互作用等爆轰问题,射流的形成、延展等界面碰撞问题,射流对靶的侵彻、靶的成坑和动态响应等侵彻问题,作用过程复杂。为了研究油井聚能射孔器的作用过程和机理,降低设计成本,缩短研制周期,本文介绍了模拟石油射孔器从炸药起爆,射流形成,射流侵彻钢靶、井液、混凝土靶的整个作用过程的欧拉数值方法,包括数学模型、离散方法、相应的本构模型,以及为节省计算机时采用的计算和理论分析耦合的模拟方法,并将数值模拟结果与实验进行了比较。研究结果表明,数值模拟结果与实验结果符合的较好,说明方法是有效的和可行的。     

空气炮碰撞实验台发射过程的数值模拟

利用计算流体动力学方法对单级空气炮碰撞实验台的发射过程进行了数值仿真,所得碰撞车发射速度与实验结果吻合。在此基础上,对碰撞车发射过程的流场变化、车体前后压力以及储气罐压力变化进行分析。结果表明,泄漏气体先于碰撞车充满整个发射空间,形成初始流场,使得车前压力出现正负交替现象,但其数值较小,对车体加速过程的影响可以忽略。当碰撞车进入泄压段后,受冲击射流作用,碰撞车仍处于加速状态,且速度增量约为2 m/s。     

合金工具钢的水下爆炸焊接

针对水下爆炸焊接法对超薄、高硬度脆性材料的独特应用特点,开展合金工具钢与铜箔的焊接复合实验。采用高爆速炸药倾斜装药方式,开展实验研究。利用有限元软件ANASYS/LS-DYNA对水下爆炸冲击波驱动飞板的飞行过程进行数值模拟,验证焊接参数合理性。模拟结果显示,飞板与基本碰撞速度沿焊接方向逐渐减小。微观组织观察显示,界面整体表现为爆炸焊接波状形态,呈沿焊接方向逐渐减弱的趋势,与模拟预计结果一致。对焊接实验样品界面处进行显微硬度测试,显示近界面处硬度稍有增加。     

The Effect of Splitting Timing on Mixing in a Jet with Double Injections

We present large-eddy simulation (LES) of a high-pressure gas jet that is injecting into a quiescent inert environment. The injection is through a nozzle with a diameter of 1.35 mm. Four injection strategies are considered in which the results of a single continuous injection case are compared with those of double injection cases with different injection splitting timing. In all double injection cases, the injection pulsing interval is kept the same, and the total injected mass is equal to that of the single injection case. On the other hand, the splitting timing is varied to investigate the effects of various injection splitting strategies on the mixture formation and the penetration length of the jet. Results show that the jet penetration length is not so sensitive to the splitting timing whereas the mixing quality can significantly change as a result of shifting the onset of injection splitting toward the end of injection. Especially, it is found that by adopting a post-injection strategy where a single injection splits into the main injection and late small injection near the end of injection period the mixing between the injected gas and ambient air is significantly improved. This trend is not as obvious when the injection splitting timing shifts toward the beginning or even in the middle of injection period. The increase of entrainment in the tail of each injection is one of the underlying physics in the mixing improvement in double injection cases. In addition to that, splitting a single injection into two smaller injections increases the surrounding area of the jet and also stretches it along the axial direction. It can potentially increase the mixing of injected gas with the ambient air.     

A gas jet superposition model for CFD modeling of group-hole nozzle sprays

In the present study, a jet superposition modeling approach is explored to model group-hole nozzle sprays, in which multiple spray jets interact with each other. An equation to estimate the merged jet velocity from each of the individual jets was derived based on momentum conservation for equivalent gas jets. Diverging and converging group-hole nozzles were also considered. The model was implemented as a sub-grid-scale submodel in a Lagrangian Drop–Eulerian Gas CFD model for spray predictions. Spray tip penetration predicted using the present superposition model was validated against experimental results for parallel, diverging and converging group-hole nozzles as a function of the angle between the two holes at various injection and ambient pressures. The results show that spray tip penetration decreases as the group hole diverging or converging angle increases. However, the spray penetration of the converging group-hole nozzle arrangement is more sensitive to the angle between the two holes compared to diverging nozzle because the radial momentum component is converted to axial momentum during the jet–jet impingement process in the converging group-hole nozzle case. The modeling results also indicate that for converging group-hole nozzles the merged sprays become ellipsoidal in cross-section far downstream of the nozzle exit with larger converging angles, indicating increased air entrainment.     

非对称射流形成的几何理论(二)

将平板非对称正碰撞形成射流满足的定常方程组封闭条件推广到非正碰情况，提出了平面二维条件下非对称射流形成的一般理论，给出了射流形成的临界条件和出流射流的理论公式。对斜碰撞情形下非对称射流的出流方向、厚度随碰撞角和来流初始位形的变化规律进行了理论预测和数值模拟，理论解与二维欧拉程序的仿真结果符合较好。     

爆轰波波形与药型罩结构匹配对杆式射流成形的影响

为提高杆式射流对钢靶的侵彻能力,设计了一种偏心亚半球药型罩,通过爆轰波碰撞理论推导出药型罩压垮速度,并结合改进的PER理论建立了杆式射流成形的模型。分析了药型罩结构参数对爆轰波碰撞压力的影响规律,获得了等质量变壁厚药型罩射流质量及速度分布的变化规律。结果表明:马赫反射压力随偏心距的增大而增大,随外壁曲率半径的增大而减小,而正规斜反射压力与马赫反射压力变化规律相反,且马赫反射压力受药型罩结构影响较大;通过对比不同方案,罩顶与罩口部厚、中间薄形状药型罩形成的射流质量提高了29.5%,头部速度提高了21.3%,且速度梯度最大,相同炸高条件下侵彻深度提高了约2倍装药直径。针对优化结构进行了数值模拟和实验验证,通过对爆轰波波形与药型罩结构合理的匹配设计,使形成的杆式射流成形及侵彻性能得到显著提升。     

熔喷双槽形喷嘴气体射流流场初探

在熔喷非织造布加工中,气体射流作为工作介质使聚合物熔体实现拉伸,气体射流流场的研究对熔喷气流拉抻数学模型研究非常重要。熔喷双槽形喷嘴形成的流场可以看作两股平面射流的合成。从单个点涡的性质出发,研究了涡偶的性质和涡偶代替射流的可行性。研究表明,在喷丝孔轴线附近,涡偶和射流的速度分布趋势相同,且有比较相近的速度分布,从而说明以涡偶代替射流是可行的。在此基础上,用两个涡偶分别代替两股射流,然后进行合成,推导出两股射流合成后速度分布的理论公式,该公式的计算结果与实验结果吻合较好。将该公式引入熔喷气流拉伸数学模型,预测出的纤维直径与采用经验公式时的预测结果几乎完全相同。结果表明,应用涡偶代替射流推导出的气流速度分布公式能够较好地描述熔喷双槽形喷嘴气体射流流场,可以用于完善熔喷气流拉伸数学模型。     

Solitary wave interaction

The interaction between solitary wave solutions to a double sine-Gordon equation is examined numerically. Depending on the velocity, formation of breather-like modes or quasi solitonic behaviour are observed when a 2δ-kink interact with a 2π-antikink. As a result of collision between a (2π-2δ)-kink and a (2π-2δ)-antikink two 2δ-kink-antikink pairs always appear.     

Rarefied gas shear flow between two movable segments of parallel plates

A study is made of the two-dimensional steady-state rarefied gas flow observed between two parallel plane surfaces of finite and different length when one of the surfaces is fixed and the other moves parallel to itself at a constant velocity, while remaining within the bounds of a given segment with fixed ends (the motion is similar to that of a conveyer belt). This flow can be regarded as a twodimensional counterpart of the classical one-dimensional Couette flow. The corresponding problem is formulated in a rectangular domain for the nonlinear kinetic equation with a model collision operator and is solved by a finite-difference method for various boundary conditions. For simplicity's sake, the flow was studied under conditions such that it can be considered near-isothermal. The gas pressures on each side of the gap formed by the plates may be the same or different. If the pressures on both sides of the gap are equal, then a near-zero-gradient flow develops between the plates. In this case, the greater the plate length, the nearer the flow in the middle of the gap to one-dimensional Couette flow. The end effects are examined, together with the conditions in which the flow in the middle of the domain can be assumed to be practically one-dimensional. In the zero-gradient regime, the system operates, in general, as a pump transferring gas from one side of the gap the other. The ability to pump gas also remains if a small counterpressure exists.Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 3, pp. 150–155, May–June, 1995.The work was financially supported by the Russian Foundation for Fundamental Research (project No. 93-013-17928).     

包覆板材料为陶瓷时平板装药的防护性能

运用口径36mm的精密成型装药实验,研究了等效厚度相同的碳化硅和氧化铝陶瓷平板装药的防护性能,并与包覆材料为钢的平板装药进行了对比。运用LS-DYNA3D软件,对平板装药与聚能装药的作用过程进行了三维数值模拟。实验结果显示,对于此结构的平板装药,碳化硅和氧化铝陶瓷平板装药使聚能装药侵彻能力分别下降了88%和82%,优于钢板的防护性能。数值模拟结果显示,陶瓷包覆板从边缘至中心依次出现断裂和粉碎现象,钢板与射流后部作用为断续干扰,而陶瓷板为连续干扰。     

PIV MEASUREMENT OF CLOSE IMPINGING JET ON FLAT PLATE 1)

运用时间分辨粒子成像测速系统(time-resolved particle image velocimetry, TR-PIV)对近距离下射流冲击平板时的流场进行了直接测量, 通过对两个正交的平面流场开展测量, 揭示了冲击距离和雷诺数对射流间隙内三维流动特征及涡系结构演化规律的影响. 结果表明: 射流间隙存在三种典型的涡系结构, 分别为双涡环模式、单涡环模式和卷吸模式, 但在大流量湍流状态下, 射流可能会冲破涡环, 形成随机的高速出流, 各流动模式的出现主要与射流流态及壁面约束作用有关. 运用涡量分析对三种典型涡系结构的能量传递和损失特性进行了比较. 结果表明: 近距离冲击时, 射流的能量通过涡环模式向外传递. 在双涡环模式下, 两个涡环的旋向相反, 端面的约束作用使得两个涡环都被严格约束在射流棒端面之内, 且一次涡环强度显著大于二次涡环强度. 最后, 运用本征正交分解方法对射流间隙内的流动模态及其能量分布进行了分析. 单涡和双涡模式前十阶模态分析结果表明: 能量脉动在较低阶时即以配对的模式出现, 这表明一次涡环与二次涡环均具有良好的对称性, 同时在双涡模式中, 一次涡环是占主导作用的大尺度流动结构. 卷吸模式的前三阶模态分析表明: 射流的能量集中在射流上游, 能量随紊动扩散急剧衰减.     

近距离下射流冲击平板PIV实验研究

运用时间分辨粒子成像测速系统(time-resolved particle image velocimetry, TR-PIV)对近距离下射流冲击平板时的流场进行了直接测量, 通过对两个正交的平面流场开展测量, 揭示了冲击距离和雷诺数对射流间隙内三维流动特征及涡系结构演化规律的影响. 结果表明: 射流间隙存在三种典型的涡系结构, 分别为双涡环模式、单涡环模式和卷吸模式, 但在大流量湍流状态下, 射流可能会冲破涡环, 形成随机的高速出流, 各流动模式的出现主要与射流流态及壁面约束作用有关. 运用涡量分析对三种典型涡系结构的能量传递和损失特性进行了比较. 结果表明: 近距离冲击时, 射流的能量通过涡环模式向外传递. 在双涡环模式下, 两个涡环的旋向相反, 端面的约束作用使得两个涡环都被严格约束在射流棒端面之内, 且一次涡环强度显著大于二次涡环强度. 最后, 运用本征正交分解方法对射流间隙内的流动模态及其能量分布进行了分析. 单涡和双涡模式前十阶模态分析结果表明: 能量脉动在较低阶时即以配对的模式出现, 这表明一次涡环与二次涡环均具有良好的对称性, 同时在双涡模式中, 一次涡环是占主导作用的大尺度流动结构. 卷吸模式的前三阶模态分析表明: 射流的能量集中在射流上游, 能量随紊动扩散急剧衰减.