A finite element method for poro mechanical modelling of geotechnical problems using local second gradient models

In this paper, a new finite element method is described and applied. It is based on a theory developed to model poromechanical problems where the mechanical part is obeying a second gradient theory. The aim of such a work is to properly model the post localized behaviour of soils and rocks saturated with a pore fluid. Beside the development of this new coupled theory, a corresponding finite element method has been developed. The elements used are based on a weak form of the relation between the deformation gradient and the second gradient, using a field of Lagrange multipliers. The global problem is solved by a system of equations where the kinematic variables are fully coupled with the pore pressure. Some numerical experiments showing the effectiveness of the method ends the paper. Copyright © 2005 John Wiley & Sons, Ltd.     

侧喷孔分布对多股燃气射流在充液室中扩展特性的影响

该文对火药燃烧形成的多股高压燃气射流从模拟弹头头部喷入柱形充液室的过程进行了数值研究。采用雷诺平均N-S方程结合可实现k-ε湍流模型来描述单个中心泰勒空腔和多个侧面泰勒空腔在受限液体环境中的扩展过程,同时分析了侧面喷孔个数对燃气扩展的影响。数值结果表明,减少侧面喷孔的个数,泰勒空腔的剖面形状并未发生明显变化,相邻侧面泰勒空腔的汇聚过程变慢,泰勒空腔充满充液室的时间增加。侧面喷孔的个数减少,泰勒空腔内部的静压趋于稳定,流场内径向截面的平均总压降低。     

潜射导弹空化特性水洞模型试验研究

潜射导弹水下弹道品质决定了发射过程的成败。发射速度提高形成的导弹附体空泡造成了流体动力的不确定性,增加了水下弹道设计的难度。针对潜射导弹水下航行的特点,采用通气空泡技术来模拟不同空化状态下航行的导弹,给出了空泡形态及其流体动力特性,分析了锥头锥角对空泡形态和流体动力特性的影响,得出了回射流效应及弹体自由攻角随锥角增大而增大的结论。借鉴超空泡武器外形理论,设计了增强弹道稳定性的截头锥头型,并通过试验验证了该头型弹体稳定性好的特点。试验结果可供潜射导弹水弹道设计人员参考。     

变燃速发射药芯料体积流率波动值的数值模拟

利用POLYFLOW软件,对不同操作条件下变燃速发射药芯料在机筒内的流动情况进行三维数值模拟,对其体积流率波动因素进行研究。结果表明,芯料的体积流率与螺杆转速成正比,不同转速下芯料体积流率高频波动值在0.02%~0.03%之间,芯料的体积流率波动值与螺杆转速波动值成正比关系;芯料的体积流率与入口压力成正比,不同入口压力下体积流率高频波动值为0.024%~0.026%;入口压力波动较大时,芯料的体积流率波动随着入口压力的增大而较快增加。     

Numerical Simulation for Ventilated Supercavitation High Speed Underwater Vehicle

Supercavitation is a revolutionary technique to achieve high drag reduction for underwater vehicle. It can help us to break through the conventional speed barrier. This article presents a numerical algorithm for ventilated supercavitation flow field based on mixture multiphase flow model, briefs the calculation results and compares them with that tested in high-speed water tunnel and towing tank. The mathematical model, its numerical calculation method, computational region and boundary conditions are discussed in detail. Some pertinent nondimensional parameters about the ventilated supercavitation, such as geometrical configuration of supercavity, drag coefficient and ventilation rate are investigated. Reynolds number is selected to predict gas ventilation rate instead of Froude number. Finally, based on the test and simulation results, a semi-empirical formula of the ventilation rate estimation suitable for different conical angle caritators is proposed.     

气室冲量模拟器建模与仿真研究

气室冲量模拟器是导气式自动机模拟试验系统的核心部件,其动力学特性决定了该系统是否可以模拟武器实弹射击时的气室火药燃气压力冲量。以某14．5mm高射机枪为例,对气室冲量模拟器进行了气体动力学仿真。介绍了气室冲量模拟器的工作原理,根据气体动力学和热力学理论,利用经典龙格一库塔法建立了气室冲量模拟器活塞运动的数学模型,并应用MATLAB编程求出了数值解,将仿真结果与实测结果进行对比,得出该气室冲量模拟器可以被用来模拟气室冲量,完成模拟射击试验。     

惯性炮尾式膨胀波火炮膨胀波速度和行程计算仿真

膨胀波火炮利用弹丸在膛内运行到一定位置时提前开闩的方法,实现了在不降低弹丸初速的前提下大幅度减小火炮后坐力的目的。基于膨胀波火炮后喷装置的工作特性,对两种不同打开方式进行了讨论,着重对惯性炮尾式膨胀波火炮进行了物理模型和经典内弹道模型建立,并进行数值仿真。最后根据经验公式估算的惯性炮尾开闩行程,利用反推法计算了惯性炮尾式膨胀波火炮膨胀波在身管内的传播速度和行程,进而获得了惯性炮尾最佳打开时机和开闩行程。     

非结构化网格下二维钝头体绕流DSMC数值模拟

本文采用非结构化三角网格为基本网格单元,应用DSMC(直接模拟蒙特卡罗法)方法对超声速稀薄气体钝头体绕流问题进行数值模拟。对不同Knudsen数和不同Mach数下的绕流问题进行数值模拟,得到在高空稀薄气体区域飞行器外部流场变化的一些基本规律。结果表明:随着Knudsen数的增加,激波减弱,激波层厚度增大,激波位置远离钝体表面,壁面热流密度减小;在相同的Knudsen数下,随来流的速度增加,壁面热流密度增大。这些模拟结果对有效的完成飞行器热防护具有十分重要的意义。     

Computational and Experimental Investigation on Aerodynamic Characteristics of Terminally Sensitive Projectile with S-C Shaped Fins

The design of terminally sensitive projectile scanning platform requires a better understanding of its aerodynamic characteristics.The terminally sensitive projectile with S-C fins has a complex aerodynamic shape,which is constructed with small length to diameter ratio cylindrical body on which two low aspect ratio fins are installed.The study focuses on the effect of fin aspect ratio on the aerodynamic characteristics.Simulation was carried on based on computational fluid dynamics(CFD) method,and the pressure distribution characteristic,drag coefficient,lift coefficient and rolling moment coefficient varying with attack angle were obtained.A free flying experimental investigation focused on the kinetic aerodynamics was made.The results show that the fins provide sufficient drag to balance the terminally sensitive projectile weight to keep it flying at low and stable speed.The lift coefficient has a negative linear varying with attack angle.The rolling moment decrease with the increase in attack angle and the decrease in wing span area.     

浙江省水利河口研究院科学技术发展50年

经过几代人的不懈探索和努力奋斗，迎来了浙江省水利河口研究院50华诞。50a来，该院各专业从无到有、从小到大，研究领域不断拓展、研究手段不断丰富、研究水平不断提升，科研队伍不断壮大，综合科研技术实力获得了飞速发展。对该院的历史沿革和基本情况作了介绍，并对该院成立50a来的水利河口科技进展，主要包括钱塘江河口治理开发研究、其它河口海岸开发研究、水资源水环境研究、防灾减灾研究、岩土力学及工程勘探、水工水力学试验研究、水工材料研究与应用、工程设计、工程质量检测及评价、水土保持研究与应用、水利信息自动化的开发与研制等作了重点介绍。