结构参数对串联微环谐振腔编解码器性能的影响

光码分多址系统中, 光编解码器是影响系统性能的关键因素之一.自相关峰值旁瓣比(P/W)、自互相关峰值比(P/C)是衡量编解码器性能的两个重要指标.以硅基SOI微环谐振腔为载体, 提出了一种串联三环阵列的二维相干OCDMA编解码器模型.详细研究了耦合系数、损耗系数、阵列间距以及通道间隔对微环谐振腔编解码器性能的影响.结果表明, 半径为50 μm的微环, 环与直波导间耦合系数在0.6–0.7之间, 环与环间耦合系数在0.1–0.2之间, 损耗系数 < 2 dB/cm, 阵列间距大于3 mm, 通道间隔在25–36 GHz间时, 编解码器能够获得良好的性能.     

CFD analysis of an oscillating wing at various reduced frequencies

The effect of various reduced frequencies has been examined for an oscillating aspect ratio 10 NACA 0015 wing. An unsteady, compressible three‐dimensional (3D) Navier–Stokes code based on Beam and Warming algorithm with the Baldwin–Lomax turbulence model has been used. The code is validated for the study against published experimental data. The 3D unsteady flow field is simulated for reduced frequency values of 0.1, 0.2 and 0.3 for a fixed mean angle of attack position and fixed amplitude. The type of motion is sinusoidal harmonic. The force coefficients, pressure distributions and flow visualization show that at the given conditions the flow remains attached to the wing surface even at high angles of attack with no clear separation or typical light‐to‐deep category of dynamic stall. Increased magnitude of hysteresis and higher gradients are seen at higher reduced frequencies. The 3D effects are even found at midspan locations. In addition, the rate of decrease in lift near the wing tips compared with the wing root is not much like in the static cases. Copyright © 2008 John Wiley & Sons, Ltd.     

机翼变形的双激光器实时测量原理

在飞机机身的上下位置分别安装一个激光器,提出了一种实时测量在飞行过程中机翼弹性变形量的方法。以激光器与安装反射镜的机翼顶端之间的测量距离数据为依据,得到机翼或机身上任意点的实时变形量。机翼或机身上任意点的实时变形量是从机翼变形数据库中提取的数据量计算得到。根据弹性薄板理论,利用理想二维梁为例说明了该方法的实现过程,并且进行仿真说明。该方法对实时测量机翼弹性变形量具有普遍意义和实际应用价值。     

新型高倍显微镜云纹测量技术及其应用

本文介绍了两种新型的高倍显微镜云纹测量技术，即激光扫描共聚焦显微镜（LSCM）云纹法和扫描电子显微镜（SEM）云纹法。阐述了LSCM云纹和SEM云纹的形成及测量原理，同时对此两种云纹法加以对比，比较其各自的特点。此外，还对两种云纹法的应用进行探讨，针对测量物体表面变形和表征物体表面周期性结构特征这两类应用领域，分别以测量多晶铝合金板的残余变形和识别日本纹白蝶翅膀表面结构为例介绍LSCM云纹法的应用，以识别绿带翠凤蝶翅膀表面结构为例介绍了SEM云纹法的应用。实验结果证明了LSCM云纹法和SEM云纹法的可行性、灵活性及高灵敏度特性，均为高效、无损的全场测量技术，在微纳米尺度力学特性测量和表征方面有广泛的应用前景。     

Investigation on vortex shedding of a swept-back wing

Effects of Reynolds number and angle of attack on the vortex shedding of a finite swept-back wing are experimentally studied. The cross-sectional profile of the wing is NACA 0012, and the sweep-back angle is 15° The time series signals detected by hot-wire in the wake region shows four distinct behaviors: laminar, subcritical, transitional, and supercritical. The derived Strouhal number curves are significantly different in these four behaviors. In addition, the statistical properties of turbulence, that is, the power spectrum density function, probability density function, correlation coefficient, Lagrangian integral time scales, and length scales are also presented in this paper.     

Extracting the weak distorted fringes on the dragonfly wing by a correlation algorithm

We have proposed a simple correlation algorithm to extract weak distorted fringes buried in both background noise and random noise. The relationship among threshold value, signal to noise ratio and least frame number was discussed. The method, is efficiency to measure the shape of an object with low diffuse reflectivity. We have successfully applied the method to measure the shape of a dragonfly wing.     

Controlling the near vortex wake of a swept half-wing by means of mini-flaps

The effect of mini-flaps on the flow pattern in the near vortex wake behind a model swept half-wing is investigated. The distributions of the time-average flow velocity were measured in a subsonic wind tunnel, in a section normal to the freestream velocity vector located at a distance of 3.8 wing half-spans from its trailing edge. When mini-flaps are mounted on both upper and lower wing surfaces, two vortices (tip and auxiliary) of the same sign are observable in the above-mentioned flow section; they are separated by an extended region of vorticity of the opposite sign. The model angle-of-attack effect on the intensities of the tip and auxiliary vortices is estimated.     

Spatial solitons in nonlinear liquid waveguides

Spatial solitons are studied in a planar waveguide filled with nonlinear liquids. Spectral and spatial measurements for different geometries and input power of the laser beam show the influence of different nonlinear effects as stimulated scatterings on the soliton propagation and in particular on the beam polarization. The stimulated scattering can be used advantageously to couple the two polarization components. This effect can lead to multiple applications in optical switching.     

A computational study of the wing–wing and wing–body interactions of a model insect

The aerodynamic interaction between the contralateral wings and between the body and wings of a model insect are studied, by using the method of numerically solving the Navier-Stokes equations over moving overset grids, under typical hovering and forward flight conditions. Both the interaction between the contralateral wings and the interaction between the body and wings are very weak, e.g. at hovering, changes in aerodynamic forces of a wing due to the present of the other wing are less than 3% and changes in aerodynamic forces of the wings due to presence of the body are less than 2%. The reason for this is as following. During each down- or up-stroke, a wing produces a vortex ring, which induces a relatively large jet-like flow inside the ring but very small flow outside the ring. The vortex rings of the left and right wings are on the two sides of the body. Thus one wing is outside vortex ring of the other wing and the body is outside the vortex rings of the left and right wings, resulting in the weak interactions.     

Multichanneled hierarchical porous nanocomposite CuO/carbonized butterfly wing and its excellent catalytic performance for thermal decomposition of ammonium perchlorate

To meet the requirement of generating more apparent specific heat release at lower temperatures for ammonium perchlorate (AP)-based composite solid propellants, the development of high-performance catalysts for improving the thermal decomposition properties of AP still remains essential and challenging. Herein, a novel catalyst, multichanneled hierarchical porous nanocomposite of CuO and carbonized butterfly wing (CuO/CBW), has been prepared through an in-situ reaction on original butterfly wing scales. Owing to the high active surface area and the good electrical and thermal conductivity, as well as the synergistic effect of CuO nanoparticles (20–25 nm) and CBW, CuO/CBW nanocomposite exhibits excellent catalytic activity for AP thermal decomposition in reducing the high-temperature decomposition temperature by 88.3°C, lowering the apparent activation energy from 190.0 to 103.1 kJ mol⁻¹ and increasing the heat release from 255 to 1841 J g⁻¹.