Dynamic Stability of Electrostatic Torsional Actuators with van Der Waals Effect

electrostatic torsional nano-electro-mechanical systems (NEMS) actuators is analyzed in the paper. The dependence of the critical tilting angle and voltage is investigated on the sizes of structure with the consideration of vdW effects. The pull-in phenomenon without the electrostatic torque is studied, and a critical pull-in gap is derived. A dimensionless equation of motion is presented, and the qualitative analysis of it shows that the equilibrium points of the corresponding autonomous system include center points, stable focus points, and unstable saddle points. The Hopf bifurcation points and fork bifurcation points also exist in the system. The phase portraits connecting these equilibrium points exhibit periodic orbits, heteroclinic orbits, as well as homoclinic orbits.

微米尺度结构最大抗扭强度的在线测试和研究

提出了一种新型的测试结构，对面积为微米量级下键合的最大抗扭强度进行了测试) 实验设计一系列的单晶硅悬臂梁结构测试键合面积在微米量级时的最大剪切力，键合面为常用的矩形其边长从*!+ 到!#$!+，并根据实际移动距离计算得出的最大剪切力) 并实验实际得出最大剪切扭矩和相应的键合面积的曲线，以及最大扭转剪切破坏应力与悬臂梁加载距离的关系，并针对*$!+, *$!+ 的矩形键合结构进行了加载和位移的重复性实验测量，两次测量结果符合较好) 微电子机械系统（+-./0121.3/0+1.456-.52 78731+，9:9;）器件的设计人员可以根据结论曲线，针对所需的抗扭强度设计相应的键合面积，为9:9; 器件工艺的在线定量测试与设计提供参考)

The Interaction Between Shock Waves and Solid Spheres Arrays in a Shock Tube

When a shock wave interacts with a group of solid spheres, non-linear aerodynamic behaviors come into effect. The complicated wave reflections such as the Mach reflection occur in. the wave propagation process. The wave interactions with vortices behind each sphere's wake cause fluctuation in the pressure profiles of shock waves. This paper reports an experimental study for the aerodynamic processes involved in the interaction between shock waves and solid spheres. A schlieren photography was applied to visualize the various shock waves passing through solid spheres. Pressure measurements were performed along different downstream positions. The experiments were conducted in both rectangular and circular shock tubes. The data with respect to the effect of the sphere array, size, interval distance, incident Mach number, etc., on the shock wave attenuation were obtained.

Nanopillar junctions.

The fabrication of nanopillar devices has been essential to the understanding and development of metallic spin electronics. This paper discusses the processes that can be used for the fabrication of such structures and the challenges in which they present, with particular emphasis on extreme sub-micrometre pillar structures suitable for the study of spin-transfer torque effects.

Analysis of asymmetrical cold rolling with varying coefficients of friction

In this research, asymmetrical cold rolling was produced by the difference in the coefficient of friction between rolls and sheets rather than the difference of roll radius or rotation speeds. The influence of friction coefficient ratio on the cross shear deformation, rolling pressure and torque was investigated using slab analysis. The results showed that the shear deformation zone length increased with the increase of the friction coefficient ratio. The rolling force decreased only under the condition that the friction coefficient ratio increased while the sum of the friction coefficients was held constant. As the reduction per pass was increased, the shear deformation zone length increased and the rolling force also increased. An increase of the front tension resulted in a decrease of the shear deformation zone length. An increase of back tension, however, led to an increase of the shear deformation zone length. The reduction of rolling torque for the work roll with higher surface roughness was greater than that for the work roll with lower surface roughness. (C) 2002 Elsevier Science B.V. All rights reserved.

Waverider configurations derived from general conical flowfields

A method based on the computational fluid dynamics (CFD) is presented for a flexible waverider's design. The generating bodies of this method could be any cones. In addition, either the leading edge or the profile of the scramjet's inlet is used as the waverider's definition curve, parameterized by the quadric function, the sigmoid function or the B-spline function. Furthermore, several numerical examples are carried out to validate the method and the relevant codes. The CFD results of the configurations show that all the designs are successful. Moreover, primary suggestions are proposed for practical design by comparing the geometrical and aerodynamic performances of the cone-derived waveriders at Mach 6.

高焓膨胀波管的气动实验

该研究简报介绍了用膨胀波管产生高超声速气流的实验结果。用压力传感器测量了激波管内的激波速度，用激光全息摄影拍摄了飞船返回舱模型吹风时的激波形状，证实了在膨胀波管中建立了可用的流动条件。

滚转运动对乘波飞行器气动特性的影响

乘波飞行器运动过程中的非定常气动特性是高超声速飞行中的重要物理问题之一。采用数值模拟方法模拟了乘波飞行器在固定迎角下绕其对称轴强迫滚转运动这一过程。比较了在不同频率和滚转角下乘波飞行器的气动特性。计算格式采用AUSM类格式中最新的AUSM~+-up格式。计算结果表明:AUSM~+-up能很好地模拟飞行器滚转运动这一非定常过程;滚转运动时,所设计的乘波飞行器能使高压气体很好地附着在乘波飞行器下表面从而使其具有较好的气动特性;当频率较大时,乘波飞行器由于角速度的诱导作用会导致升力出现迟滞现象;做滚转运动时,滚转力矩小于零,产生正阻尼,乘波飞行器不会产生"摇滚"运动.

三角翼受迫俯仰滚转耦合运动的气动特性研究

基于刚性动网格的技术,选用B-L湍流模型,利用有限控制体积法对N-S方程进行数值离散,对76°大后掠三角翼的受迫俯仰滚转耦合运动进行了数值模拟,在此基础上,对俯仰滚转耦合运动的气动力特性和流场结构进行了分析.计算结果表明:俯仰滚转耦合运动时,三角翼上表面的涡分布的非对称性将产生横侧方向的偏航力矩和滚转力矩,滚转力矩和偏航力矩随着滚转振幅角和滚转缩减频率的增大而增大,但对法向力影响不大.

超声速液体射流的气动特性

介绍了有关脉冲超声速水射流以及柴油射流气动特性的研究结果。水射流实验是在一台垂直设置的内径为8mm的火药枪设备上进行的。用出口直径为5mm的喷嘴,产生了速度为600m/s的水射流。用纹影仪观察了射流及激波形状,从而测量了激波与前体驻点之间的离开距离。柴油射流实验是在一台水平设置的高压氦气气枪设备上进行的。

高超声速乘波飞行器气动实验研究

以绕楔高超声速流场为基础，用流线追踪法生成了一种高超声速飞行器气动概念构形、初步探索了高超声速飞行器机身/推进系统一体化气动构形设计方法，开展了高超声速测压实验，结果表明：该类构形飞行器在高超声速飞行时，可以产生较高的升阻比，前体的预压缩效果明显，是以吸气式冲压发动机动力的有效途的飞行器构形。

Numerical Analyses of Transonic Fluid/Structure interaction in Aircraft Engineering

Through the coupling between aerodynamic and structural governing equations, a fully implicit multiblock aeroelastic solver was developed for transonic fluid/stricture interaction. The Navier-Stokes fluid equations are solved based on LU-SGS (lower-upper symmetric Gauss-Seidel) Time-marching subiteration scheme and HLLEW (Harten-Lax-van Leer-Einfeldt-Wada) spacing discretization scheme and the same subiteration formulation is applied directly to the structural equations of motion in generalized coordinates. Transfinite interpolation (TFI) is used for the grid deformation of blocks neighboring the flexible surfaces. The infinite plate spline (IPS) and the principal of virtual work are utilized for the data transformation between fluid and structure. The developed code was fort validated through the comparison of experimental and computational results for the AGARD 445.6 standard aeroelastic wing. In the subsonic and transonic range, the calculated flutter speeds and frequencies agree well with experimental data, however, in the supersonic range, the present calculation overpredicts the experimental flutter points similar to other computations. Then the flutter character of a complete aircraft configuration is analyzed through the calculation of the change of structural stiffness. Finally, the phenomenon of aileron buzz is simulated for the weakened model of a supersonic transport wing/body model at Mach numbers of 0.98 and l.05. The calculated unsteady flow shows, on the upper surface, the shock wave becomes stronger as the aileron deflects downward, and the flow behaves just contrary on the lower surface of the wing. Corresponding to general theoretical analysis, the flow instability referred to as aileron buzz is induced by a stronger shock alternately moving on the upper and lower surfaces of wing. For the rigid structural model, the flow is stable at all calculated Mach numbers as observed in experiment

Numerical Research on Liquid Spray in Supersonic Cross Flow

Numerical simulation was conducted to characterize the kerosene spray injecting into supersonic cross flow, especially focusing on the aerodynamic secondary breakup effect of the supersonic cross flow on the initial droplets. It was revealed that the initial parent drops were broken up into small drops whose diameter is about O(10) micrometers soon after they entered into the supersonic cross flow. During the appropriate range of initial drop size, the parent droplets would be broken up into small drops with the same magnitude diameter no matter how large the initial drops SMD was.

Numerical Study on Kerosene Spray in Supersonic Flow

Numerical simulation was conducted to study the kerosene spray characteristics injecting into supersonic cross flow. The verification of the simulation was carried out by experimental Schlieren image, and the agreement was obtained by compared the spray plume pictures. Furthermore, the aerodynamic secondary breakup effect of the supersonic cross flow on the initial droplets was investigated. It was revealed that the initial parent drops were broken up into small drops whose diameter is about O(10) micrometers soon after they entered into the supersonic cross flow. During the appropriate range of initial drop size, the parent droplets would be broken up into small drops with the same magnitude diameter no matter how large the initial drops SMD was.