表面修饰硼酸盐润滑油添加剂的摩擦学性能

制备了表面修饰的硼酸盐润滑油添加剂（球形颗粒，粒径大都小于０．５μｍ），且用四球试验机研究了其摩擦学性能．结果表明：这种添加剂具有良好的极压抗磨减摩性能，当润滑油中元素Ｂ的质量分数为０．０５％时，四球磨斑直径最小，最大无卡咬负荷（ｐＢ值）最高；基础油的粘度和含水量对添加剂的极压抗磨性能有较大的影响，粘度为６５．３０ｍｍ２／ｓ时的极压抗磨性最好，水的质量分数为１％时的ｐＢ值最高，低于１％时的ｐＢ值比不含水时的高，水的质量分数高于１％时的ｐＢ值随水含量的增加而降低．Ｘ射线光电子能谱分析发现，表面修饰的硼酸盐润滑油添加剂在摩擦表面形成了一层混合的摩擦化学反应膜，其中元素Ｂ主要以ＢＮ的形式存在．     

不同围压实验变形物质中的微观滑移方式标志研究

通过不同围压条件下岩石破裂粘滑或稳滑实验样品的微观对比观测研究，分析了压力对滑移方式标志的可能影响，提出在不同围压条件下，变形物质中赋存的微观粘滑或稳滑的识别标志，为类似围压条件下形成的天然样品微观滑移方式标志的识别提供了实验判据。     

轴压作用下充液圆柱壳屈曲的实验研究

本文从实验及理论两个方面对充满液体的圆柱壳在轴向压力作用下液体内压的变化进行了实际测试及理论定性分析．采用薄壳理论分析了屈曲前液体内压随轴向压力的变化规律，讨论了壳材料、几何参数及边界约束对内压的影响．通过实验实际测定了内压随轴向压力的变化规律．通过实验手段测定了充满液体的圆柱壳临界载荷、屈曲模态，讨论了充满液体的圆柱壳的承载能力等问题．     

Investigations involving shock waves generation and shock pressure measurement in direct ablation regime and confined ablation regime

Recent investigations involving shock waves generation and shock pressure measurement in direct ablation regime and confined ablation regime for aluminium, copper, titanium and steel (40C130) materials are reported. Experimental measurements demonstrated that in direct ablation regime the peak pressures typically are less than 10 Pa when the incident laser intensity is about 10 W/cm and the time duration of the applied pressure is roughly equal to the laser pulse duration. It is shown that confinement of the surface with a transparent overlayer provided an effective method of enhancing laser-induced shock waves pressure in the target material with an order of magnitude for same laser intensity. Also, in this second regime, the pressure is applied over a period much longer than the laser-pulse duration. As an application measurements of the hardness of target surface before and after laser irradiation in direct ablation regime and confined ablation regime are given, and it is shown that the maximum value of surface hardness is obtained in confined ablation regime. Received 10 March 2001 / Accepted 13 April 2001     

液电冲击波的实验研究

本文用水下电火花微爆炸产生重复性极佳的球形冲击波,用双曝光全息干涉法测量了液电冲击波的传播,并观察到冲击波与水下电极之间的相互作用.实验结果表明此法适用于液电冲击波的测量,特别适用于由冲击波波前位移来确定其峰值压力分布.     

40Cr材料动态起裂韧性KId（）的实验测试

描述了利用Ｈｏｐｋｉｎｓｏｎ压杆技术加载三点弯曲试样测试４０Ｃｒ，材料动态起裂韧性ＫＩｄ（）的试验方法。试样上的动态载荷历程由Ｈｏｐｋｉｎｓｏｎ杆直接测得，并分别代入动态有限元程序及近似公式求得动态应力强度因子历史；由贴在试样裂尖附近的应变片确定起裂时间，最终确定起裂时的动态应力强度因子值，即动态起裂韧性ＫＩｄ（）。试验结果表明:利用Ｈｏｐｋｉｎｓｏｎ压杆技术加载三点弯曲试样测试材料动态起裂韧性的方法是可行的，起裂时，动态有限元的位移法、应力法及近似公式法求得的动态应力强度因子值比较吻合；在本文的载荷速率下，４０Ｃｒ材料动态起裂韧性ＫＩｄ（）与准静态裂韧性ＫＩｄ（）相比，降低了约２８％。     

Dynamical analysis of cavitation for a transversely isotropic incompressible hyper-elastic medium: Periodic motion of a pre-existing micro-void

In this paper, the dynamical cavitation behavior is analyzed for a sphere composed of a class of transversely isotropic incompressible hyper-elastic materials, where there is a pre-existing micro-void in the interior of the sphere. A second-order non-linear ordinary differential equation that governs the motion of the initial micro-void is obtained by using the boundary conditions. On analyzing the qualitative properties of the solutions of the differential equation, some interesting conclusions are proposed. It is proved that the number of equilibrium points of the differential equation depends on the values of the material parameters, and that the phase diagrams of the equation are closed, smooth and convex trajectories. For any prescribed surface tensile dead-loads, the motion of the initial micro-void undergoes a non-linear periodic oscillation. The dependence of the periodic motion of the initial micro-void on material parameters and the radius of the initial micro-void is examined, and numerical results are also provided. It is worth pointing out that the conclusions in this paper can be used to describe approximately the physical implications of the dynamical formation of a cavity in the sphere.     

Modeling the Formation of Fluid Banks During Counter-Current Flow in Porous Media

Fluid banks sometimes form during gravity-driven counter-current flow in certain natural reservoir processes. Prediction of flow performance in such systems depends on our understanding of the bank-formation process. Traditional modeling methods using a single capillary pressure curve based on a final saturation distribution have successfully simulated counter-current flow without fluid banks. However, it has been difficult to simulate counter-current flow with fluid banks. In this paper, we describe the successful saturation-history-dependent modeling of counter-current flow experiments that result in fluid banks. The method used to simulate the experiments takes into account hysteresis in capillary pressure and relative permeabilities. Each spatial element in the model follows a distinct trajectory on the capillary pressure versus saturation map, which consists of the capillary hysteresis loop and the associated capillary pressure scanning curves. The new modeling method successfully captured the formation of the fluid banks observed in the experiments, including their development with time. Results show that bank formation is favored where the p_c-versus-saturation slope is low. Experiments documented in the literature that exhibited formation of fluid banks were also successfully simulated.     

Drag Reduction of a Circular Cylinder Using an Upstream Rod

Experimental studies on the drag reduction of the circular cylinder were conducted by pressure measurement at a Reynolds number of 82 000 (based on the cylinder diameter). A rod was placed upstream of and parallel to the cylinder to control the flow around the cylinder. The upstream rod can reduce the resultant force of the cylinder at various spacing between the rod and the cylinder for α < 5^∘(α defined as the staggered angle of the rod and the cylinder). For α > 10^∘, the resultant force coefficient has a large value, so the upstream rod cannot reduce the force on the cylinder any more. For α = 0^∘ and d/D = 0.5 (where d and D are the diameter of the rod and the cylinder, respectively), the maximum drag of the cylinder reduces to 2.34% that of the single cylinder. The mechanism of the drag reduction of the cylinder with an upstream rod in tandem was presented by estimating the local contributions to the drag reduction of the pressure variation. In the staggered arrangement, the flow structures have five flow patterns (they are the cavity mode, the wake splitting mode, the wake merge mode, the weak boundary layer interaction mode and the negligible interaction mode) according to the pressure distribution and the hydrogen bubble flow visualization. The half plane upwind of the cylinder can be divided to four regions, from which one can easily estimates the force acting on the circular cylinder with an upstream rod in staggered arrangement.     

Experimental investigations on the dynamic behavior of a 2-DOF airfoil in the transitional Re number regime based on digital-image correlation measurements

The present paper investigates the fluid–structure interaction (FSI) of a wing with two degrees of freedom (DOF), i.e., pitch and heave, in the transitional Reynolds number regime. This 2-DOF setup marks a classic configuration in aeroelasticity to demonstrate flutter stability of wings. In the past, mainly analytic approaches have been developed to investigate this challenging problem under simplifying assumptions such as potential flow. Although the classical theory offers satisfying results for certain cases, modern numerical simulations based on fully coupled approaches, which are more generally applicable and powerful, are still rarely found. Thus, the aim of this paper is to provide appropriate experimental reference data for well-defined configurations under clear operating conditions. In a follow-up contribution these will be used to demonstrate the capability of modern simulation techniques to capture instantaneous physical phenomena such as flutter. The measurements in a wind tunnel are carried out based on digital-image correlation (DIC). The investigated setup consists of a straight wing using a symmetric NACA 0012 airfoil. For the experiments the model is mounted into a frame by means of bending and torsional springs imitating the elastic behavior of the wing. Three different configurations of the wing possessing a fixed elastic axis are considered. For this purpose, the center of gravity is shifted along the chord line of the airfoil influencing the flutter stability of the setup. Still air free-oscillation tests are used to determine characteristic properties of the unloaded system (e.g. mass moment of inertia and damping ratios) for one (pitch or heave) and two degrees (pitch and heave) of freedom. The investigations on the coupled 2-DOF system in the wind tunnel are performed in an overall chord Reynolds number range of $9.66\times 10^3\le \text{Re}\le 8.77\times 10^4$. The effect of the fluid-load induced damping is studied for the three configurations. Furthermore, the cases of limit-cycle oscillation (LCO) as well as diverging flutter motion of the wing are characterized in detail. In addition to the DIC measurements, hot-film measurements of the wake flow for the rigid and the oscillating airfoil are presented in order to distinguish effects originating from the flow and the structure.