利用激光超声技术测量介观尺度材料的声速

设计并建立了一种可用于测量介观尺度(几十微米至几毫米)材料声速的激光超声系统.该系统采用脉宽为6.3 ns的调Q激光器作为超声波激发光源,使用光纤位移干涉仪进行超声位移探测.利用新建立的激光超声系统,测量了不同厚度铜箔的纵波声速.结果表明,激光超声系统得到的声速具有较高精度,可以将其应用于介观尺度材料声速测量.     

用超声干涉仪测不同温度下液体内的声速

测定流体中的声速是超声最重要的应用之一,本文提供一种用超声干涉仪测量液体中声速的装置。由于海水中的声速具有很大的实际意义,故我们在实验中采用30‰的盐水为样品,而且测量了不同温度下盐水中的声速。因为这实际上是不同深度下海水中声速测量的模拟。     

一套高温高压原位拉曼散射、布里渊散射测量系统

本文描述了一套利用激光加热技术、金刚石对顶砧高压技术,集成共聚焦拉曼光谱测量、六通道布里渊散射光谱测量、以及黑体辐射光谱测温,成功搭建起来的高温高压原位拉曼散射、布里渊散射的光学测量系统。利用该系统,并结合薄膜沉积金属、光刻技术改进了金刚石对顶砧中样品的装填方法,解决了样品透明不易加热的问题。已利用该系统得到液态氩在0.85 GPa常温状态下和14.58 GPa熔融状态下的体声速分别为1.85 Km/s和5.19 Km/s。     

简易超声干涉仪的安装

媒质中声速的测量具有重要的实际和理论意义。在测量液体声速的近代方法中,超声干涉仪比较简单,精度高并应用广。 干涉仪测声速的基本原理是:在被测液体中,当超声辐射板与反射板之间的距离发生相对变化时,超声辐射板的阻抗将随之周期改变,从而可以直接确定声波波长λ,然后再乘以已知的超声频率υ,即可求得声速v=λυ。     

静水压加载单晶MgO的超声测量与压力标定

通过对单晶MgO的高压声速测量,结合高压Brillouin散射数据,对静水压加载条件下六面顶压机高压腔中的压力进行了多点系统标定(系统油压从15 MPa到51 MPa,间隔2 MPa),建立了新的大腔体压机超声测量和压力标定技术。相比传统的仅采用2~3个标定压力点的方法,该技术在统计上更加可靠。结合LY12铝的高压声速测量,进一步验证了该压力标定方法的合理性。与固体传压组装相比,固液混合传压组装在相同油压下的压力值系统偏低,分析认为这主要是由于固体传压介质中的剪切效应导致标定压力值系统偏高造成的。     

用于微位移测量的笔束激光干涉仪

介绍了一种基于空间干涉原理的亚微米零差干涉位移测量方法。该方法是对笔束激光干涉仪在微位移测量领域的应用 ,干涉仪的测量精度不受光束波前畸变等光源噪声的影响。给出了干涉仪主要结构参数的选取原则 ;构建了用于微位移测量的笔束激光干涉仪实验系统。实验结果表明 ,该系统具有纳米测量分辨率。     

非对称冲击-卸载实验中纵波声速的特征线分析方法

材料高压声速是获取材料在冲击下的剪切模量、强度和相变信息的重要物理量, 对于研究材料在高速冲击下的行为非常重要. 由于飞片、样品和窗口材料阻抗失配等因素, 传统的声速分析方法无法对非对称冲击-卸载实验中单样品的窗口界面速度进行准确的分析. 本文在反向特征线方法的基础上, 考虑了飞片与样品、样品和窗口界面的相互作用, 建立了适合于仅含单一厚度样品的非对称冲击-卸载实验的特征线声速分析方法, 通过对数值实验给出的速度剖面的分析表明, 该方法能够较为准确地获得待测材料高压下的声速及卸载路径.     

高超声速模型尾迹电子密度二维分布反演方法

弹道靶利用二级轻气炮将模型加速到高超声速状态,模型在靶室内超高速飞行时形成等离子体尾迹.为实现高超声速模型尾迹电子密度径向二维分布诊断,利用七通道微波干涉仪测量系统获得了高超声速模型尾迹截面不同位置处平均电子密度.该系统采用一发七收的方式,实现平面波照射等离子体及平面波接收,天线波束可完全覆盖尾迹径向范围.多通道微波干涉仪数据处理过程常将等离子体视为分层介质,考虑到分层界面上折射效应的影响,本研究利用射线追踪方式建立电磁传播模型,结合测量数据建立目标函数,通过遗传算法优化来反演高超声速模型尾迹电子密度径向二维分布.该数据处理方法的电子密度反演结果与相同来流条件下的数值模拟结果对比吻合较好,初步验证了该方法的有效性.分析了分层模型对电子密度分布特性的影响,结果表明利用七层模型对尾迹建模效果最佳,且适用于不同厚度尾迹,最大化利用接收通道数,确保了计算精度.利用该方法实现弹道靶高超声速球模型尾迹电子密度二维分布诊断,并给出了给定实验状态下模型尾迹电子密度二维分布的一些规律.     

反向碰撞法测量Sn的高压卸载声速

采用任意反射面速度干涉系统,通过对窗口碰撞面做特殊防护处理,发展了反向加载测量高压卸载声速的实验技术,解决了以往因使用缓冲层而不能得到样品材料体积声速的局限.利用该方法测量了Sn样品在37—80 GPa压力范围内的高压卸载声速,得到了较高精度的声速测量结果(纵波声速测量误差约为2%,体积声速误差约为5%),且与热力学理论计算结果一致. 关键词： 卸载声速 反向碰撞法 任意反射面速度干涉系统 Sn     

高温声速测量的激光遥测系统

不少年来人们一直在致力于探索高温下固体中超声声速的测量方法。其主要困难是测量所用的压电换能器能承受的温度有限制。为此而采取的措施有:加进足够长的耦合棒;选用能隔热的耦合剂;采用短时接触的传声方法;以及采用非接触方式的电磁声换能方法等。但所有这些仍未能使问题得到满意的解决。为此本文提出了一种全面激光遥测的方法,即用一套激光系统来激发超声脉冲,同时又用另一套激光系统来测量该声脉冲在样品中的传播时间,从而得出被测样品的超声声速。被测样品被密封在高温真空炉中,激光束则通过炉壁上的透光窗孔射入和射出。使测量装置与被测样品完全分离开,成为一套不受工作温度限制的遥测系统。     

An efficient method for the incompressible Navier–Stokes equations on irregular domains with no-slip boundary conditions,high order up to the boundary

Common efficient schemes for the incompressible Navier–Stokes equations, such as projection or fractional step methods, have limited temporal accuracy as a result of matrix splitting errors, or introduce errors near the domain boundaries (which destroy uniform convergence to the solution). In this paper we recast the incompressible (constant density) Navier–Stokes equations (with the velocity prescribed at the boundary) as an equivalent system, for the primary variables velocity and pressure. equation for the pressure. The key difference from the usual approaches occurs at the boundaries, where we use boundary conditions that unequivocally allow the pressure to be recovered from knowledge of the velocity at any fixed time. This avoids the common difficulty of an, apparently, over-determined Poisson problem. Since in this alternative formulation the pressure can be accurately and efficiently recovered from the velocity, the recast equations are ideal for numerical marching methods. The new system can be discretized using a variety of methods, including semi-implicit treatments of viscosity, and in principle to any desired order of accuracy. In this work we illustrate the approach with a 2-D second order finite difference scheme on a Cartesian grid, and devise an algorithm to solve the equations on domains with curved (non-conforming) boundaries, including a case with a non-trivial topology (a circular obstruction inside the domain). This algorithm achieves second order accuracy in the L^∞ norm, for both the velocity and the pressure. The scheme has a natural extension to 3-D.     

无钴合金钢的冲击响应实验研究

 利用一级轻气炮作为加载手段,研究了无钴合金钢在3~20 GPa压力区间的冲击响应特性。用激光干涉测速——VISAR记录了双波结构的自由面速度剖面,并利用常压下的弹性纵波速度近似替代低压冲击下的弹性先驱波速度,确定了无钴合金钢的Hugoniot关系。根据自由面速度反映的层裂信息,给出了无钴合金钢的Hugoniot弹性极限、层裂强度以及层裂片厚度等动态力学参数。     

Momentengleichungen für Plasmen mit anisotropem Neutralgasdruck und anisotropem Ionendruck

Strongly non-Maxwellian and non-isotropic velocity distributions of the neutral atoms and of the ions occur in collisionless plasmas at high degrees of ionization, especially in gas discharges at low pressures and high current densities and in high temperature plasmas. The velocity distributions and the related velocity moments for the neutral gas and the ion gas are calculated. The influence of the magnetic fields on the ions is neglected. Especially, the pressure tensors and the heat flow tensors are investigated. The differential equations are given for the velocity moments of the velocity distribution. Additional terms occur in the equation of motion, if the pressure is non-isotropic and non-Cartesian coordinates are used. A heat flow tensor is evaluated that closes the system of differential equations for the neutral gas consistently and allows to rederive typical formulas of the molecular neutral gas flow. The heat flow tensor essentially determines the type of the differential equation system for the velocity moments. It is shown, that the neutral gas temperature is not constant across the plasma. Different statements deal with the heat flow tensor in the ion gas. In particular, non-vanishing ion temperature on the axis and a system of differential equations for the positive column under free-fall conditions are investigated. The inertia terms for the ion gas and the neutral gas must be taken into account in the pressure balance of the plasma.     

Influence of ambient pressure on the performance of an arc discharge plasma actuator

The arc discharge plasma actuator (ADPA) has wide application prospects in high‐speed flow control because of its local heating effect and strong disturbance. In this paper, the influence of ambient pressure, which ranges from 3 to 20 kPa, on the performance of a two‐electrode ADPA is investigated by a schlieren system. The duration of the arc heated region, as well as its area, is extracted by image processing. As the ambient pressure increases, different flow field evolutions occur. The duration of the ADPA heated region increases with the ambient pressure. The maximum duration reaches 1185.3 µs at 20 kPa. The velocity of the discharge‐induced blast shock wave first decreases gradually and then remains at 345 m/s for all air pressures. The blast shock wave has a higher velocity at lower pressures when it is freshly produced. A maximum blast shock wave velocity of 582 m/s is observed at the pressure of 7 kPa. The arc heated region is not sensitive to ambient pressure, but the deposited energy from the arc increases when the pressure increases.     

用作VISAR窗口的LiF晶体折射率变化修正因子

 利用加窗VISAR测速方程和平面碰撞实验产生已知样品-窗口界面粒子速度的方法，对LiF晶体用作VISAR（激光波长532 nm）测速窗口时的折射率变化修正因子进行了测定。给出了LiF晶体窗口在冲击压力2.7~66 GPa范围内，折射率变化修正因子测量结果及界面粒子速度修正方法。     

三级炮加载技术在超高压状态方程研究中的应用

根据阻抗梯度飞片设计原则和超高速数值模拟技术设计出一种新的叠层波阻抗梯度飞片,并利用三级炮加载技术将Ta飞片加速至9 km/s以上,测量了Ta在超高压下的状态方程。三级炮实验实现了冲击波速度与粒子速度的同时测量,Ta的Hugoniot数据与文献中发表的数据具有很好的线性关系,说明三级炮加载技术适合于材料超高压状态方程研究。     

Influence of air pressure on the performance of plasma synthetic jet actuator

Plasma synthetic jet actuator(PSJA) has a wide application prospect in the high-speed flow control field for its high jet velocity.In this paper,the influence of the air pressure on the performance of a two-electrode PSJA is investigated by the schlieren method in a large range from 7 k Pa to 100 k Pa.The energy consumed by the PSJA is roughly the same for all the pressure levels.Traces of the precursor shock wave velocity and the jet front velocity vary a lot for different pressures.The precursor shock wave velocity first decreases gradually and then remains at 345 m/s as the air pressure increases.The peak jet front velocity always appears at the first appearance of a jet,and it decreases gradually with the increase of the air pressure.A maximum precursor shock wave velocity of 520 m/s and a maximum jet front velocity of 440 m/s are observed at the pressure of 7 k Pa.The averaged jet velocity in one period ranges from 44 m/s to 54 m/s for all air pressures,and it drops with the rising of the air pressure.High velocities of the precursor shock wave and the jet front indicate that this type of PSJA can still be used to influence the high-speed flow field at 7 k Pa.     

Pressure and velocity profiles in a static mechanical hemilarynx model

This study examined pressure and velocity profiles in a hemilarynx mechanical model of phonation. The glottal section had parallel walls and was fabricated from hard plastic. Twelve pressure taps were created in the vocal fold surface and connected to a differential pressure transducer through a pressure switch. The glottal gap was measured with feeler gauges and the uniform glottal duct was verified by use of a laser system. Eight pressure transducers were placed in the flat wall opposite the vocal fold. Hot-wire anemometry was used to obtain velocity profiles upstream and downstream of the glottis. The results indicate that the pressure distribution on the vocal fold surface was consistent with pressure change along a parallel duct, whereas the pressures on the opposite flat wall typically were lower (by 8%-40% of the transglottal pressure just past mid-glottis). The upstream velocity profiles were symmetric regardless of the constriction shape and size. The jet flow downstream of the glottis was turbulent even for laminar upstream conditions. The front of the jet was consistently approximately 1.5 mm from the flat wall for glottal gaps of 0.4, 0.8 and 1.2 mm. The turbulence intensity also remained approximately at the same location of about 4 mm from the flat wall for the two larger gaps.     

A novel pressure–velocity formulation and solution method for fluid–structure interaction problems

In the standard approach for simulating fluid–structure interaction problems the solution of the set of equations for solids provides the three displacement components while the solution of equations for fluids provides the three velocity components and pressure. In the present paper a novel reformulation of the elastodynamic equations for Hookean solids is proposed so that they contain the same unknowns as the Navier–Stokes equations, namely velocities and pressure. A separate equation for pressure correction is derived from the constitutive equation of the solid material. The system of equations for both media is discretised using the same method (finite volume on collocated grids) and the same iterative technique (SIMPLE algorithm) is employed for the pressure–velocity coupling. With this approach, the continuity of the velocity field at the interface is automatically satisfied. A special pressure correction procedure that enforces the compatibility of stresses at the interface is also developed. The new method is employed for the prediction of pressure wave propagation in an elastic tube. Computations were carried out with different meshes and time steps and compared with available analytic solutions as well as with numerical results obtained using the Flügge equations that describe the deformation of thin shells. For all cases examined the method showed very good performance.     

基于三频点声速测量的气体压强合成算法

利用声速测量精度高, 测量方法简单的特点, 提出一种基于三个频率点测量声速合成气体压强的算法。首先在三个频率点测量声速, 然后计算得到声速频散谱拐点的弛豫频率, 最后根据弛豫频率与压强成线性正比的关系得到气体压强, 仿真结果验证了该算法的可行性。为在线实时检测气体腔体压强提供了一种技术简单、精度高的超声方法。