匝道斜桥台翼墙角度的计算方法

本文分析了珠江路立交桥B—B匝道桥台翼墙原设计的角度计算及台尾偏差问题，指出了设计中的不足，并以弦线代替曲线布置翼墙重新推导出了翼墙角度计算的通用公式．     

Wing crack model subjected to high hydraulic pressure and far field stresses and its numerical simulation

By considering the effect of hydraulic pressure filled in wing crack and the connected part of main crack on the stress intensity factor at wing crack tip, a new wing crack model exerted by hydraulic pressure and far field stresses was proposed. By introducing the equivalent crack length l _eq of wing crack, two terms make up the stress intensity factor K _I at wing crack tip: one is the component K _I⁽¹⁾ for a single isolated straight wing crack of length 2l subjected to hydraulic pressure in wing crack and far field stresses, and the other is the component K _I⁽²⁾ due to the effective shear stress induced by the presence of the equivalent main crack. The FEM model of wing crack propagation subjected to hydraulic pressure and far field stresses was also established according to different side pressure coefficients and hydraulic pressures in crack. The result shows that a good agreement is found between theoretical model of wing crack proposed and finite element method (FEM). In theory, an unstable crack propagation is shown if there is high hydraulic pressure and lateral tension. The wing crack model proposed can provide references for studying on hydraulic fracturing in rock masses.     

Aerodynamic Analysis and Simulation of Flapping Wing Aerial Vehicles on Hovering

In order to design and verify control algorithms for flapping wing aerial vehicles(FWAVs),calculation models of the translational force,rotational force and virtual mass force were established with the basis on the modified quasi-steady aerodynamic theory and high lift mechanisms of insect flight.The simulation results show that the rotational force and virtual mass force can be ignored in the hovering FWAVs with simple harmonic motions in a cycle.The effects of the wing deformation on aerodynamic forces were investigated by regarding the maximum rotational angle of wingtip as a reference variable.The simulation results also show that the average lift coefficient increases and drag coefficient decreases with the increase of the maximum rotational angle of wingtip in the range of 0-90°.     

Shock control bump optimization for a low sweep supercritical wing

Shock control bumps are a promising technique in reducing wave drag of civil transport aircraft flying at transonic speeds.This paper investigates the optimization of 3D shock control bumps on a supercritical wing with a sweep angle of 16°at the1/4 chord.A similar supercritical wing with a higher sweep angle of 24.5°at the 1/4 chord has been adopted as a baseline for the study.Numerical results show that the drag coefficient of the low sweep wing with the optimized 3D shock control bumps is reduced below that for the high sweep wing,indicating shock control bumps can be used as an effective means to reduce the wave drag caused by reducing the wing sweep angle.From the point of view of the wing structure design,lower sweep angle will also bring the benefits of weight reduction,resulting in further fuel reduction.     

蜻蜓翅膀微观结构及其润湿性

利用视频光学接触角测量仪对6种蜻蜓翅膀表面的接触角进行了测量,发现蜻蜓翅膀具有疏水性能,接触角在135.14°~149.85°之间,其值与测量部位无关,与蜻蜓种类有关。用扫描电子显微镜对蜻蜓翅膀表面微观结构进行观测,发现蜻蜓翅膀上布满柱状纳米级结构形态,柱直径分布范围为66.90~200.73 nm,柱间距为20.00~650.00 nm,翅膜厚度为1.58~4.08μm。分析了蜻蜓翅膀表面疏水机理,研究表明:蜻蜓翅膀的疏水机理满足Cassie模型,其疏水性能主要由体表纳米级别的柱状结构与体表成分共同作用的结果。蜻蜓翅膀润湿性能的研究为微型飞行器及自清洁材料的制备提供了理论依据。     

Wing load investigation of the plunge-diving locomotion of a gannet Morus inspired submersible aircraft

In this paper,we studied the wing root pivot joint’s radial load of a submersible airplane which imitates the locomotion of gannet’s Morus plunge-diving,by implementing a test device name Mimic-Gannet.The housing of the device was designed by mimicking the morphology of a living gannet,and the folding wings were realized by the mechanism of variable swept back wing.Then,the radial loads of the wing root were obtained under the conditions of different dropping heights,different sweptback angles and different water-entry inclination angles(i.e.,the angle between the longitudinal body axis and the water surface),and the relationships between the peak radial load and the above three parameters were analyzed and discussed respectively.In the studied areas,the minimum peak radial load of the pivot joint is 50.93 N,while the maximum reaches up to1135.00 N.The largest peak load would be generated for the situation of vertical water entry and zero wing sweptback angle.And it is of great significance to choose the three parameters properly to reduce the pivot joint’s radial load,i.e.,larger wing sweptback angle,smaller dropping height and water-entry inclination angle.It is also concluded that the peak radial load on the wing root is closely linear with the water-entry dropping height and the wing sweptback angle with a significant correlation.Eventually,the relationship between the wing load and the dropping height,water-entry inclination angle or wing sweptback angle,could be used to calculate the wing load about plunge-diving of a submersible aircraft,and the conclusions reveal the wing load characteristic of the gannet’s plunge process for the biologists.     

翼型厚度和弯度对前飞扑翼气动性能的影响

扑翼飞行器是一种模仿鸟类和昆虫飞行方式的新型飞行器.翼型参数设计对提高扑翼飞行器性能至关重要,为研究扑翼翼型厚度和翼型弯度对前飞扑翼气动性能的影响,基于自然界中飞行生物的实验观测结果建立了前飞扑翼气动特性计算模型,针对不同厚度和弯度的NACA系列标准翼型,采用计算流体力学方法求解二维不可压缩非定常Navier-Stokes方程,基于有限体积法并结合动态网格技术,分析了低雷诺数条件下对应不同来流速度的刚性前飞扑翼气动力、能耗、气动效率以及周围流场结构随翼型厚度和弯度的变化规律.结果表明,不同来流速度条件下扑翼推力和能耗均随翼型厚度的增大而逐渐减小,随着翼型厚度的增大,扑翼推进效率最大降幅达15.9%;翼型厚度的增加,降低了前缘涡强度并延迟了前缘涡的脱落.翼型弯度可以改变翼型的有效气动攻角,翼型弯度的增加可以显著提高翼型升力和升举效率,并促使尾流中心线向右下方倾斜;正向弯度扑翼在下扑行程能产生更大的升力,而负向弯度扑翼则在上挥行程中产生了更大的推力.     

Numerical simulations of leading-edge vortex core axial velocity for flow over delta wings

Numerical simulations have been performed to investigate the characteristics of leading-edge vortex core axial velocity over two delta wings with leading edge swept angles Λ =50°and 76°, respectively. It is obtained that Reynolds number has the most important effect on the axial velocity of the primary leading-edge vortex core. At Reynolds numbers larger than 105, the jet-like flow of the vortex core is the most common type for both the large and the moderate swept delta wings. While if Reynolds number decr...     

蝗虫翅表面微观结构及疏水耦合机理

使用体视显微镜、扫描电子显微镜、傅立叶红外光谱仪和视频光学接触角测量仪,研究了4种蝗虫(黄胫小车蝗Oedaleus infernalis、异翅负蝗Atractomorpha heteroptera、花胫绿纹蝗Aiolopus tamulus、中华稻蝗Oxya chinensis)翅表面的微观结构、化学成分及疏水性,建立了蝗虫翅表面的微观结构疏水模型,分析了蝗虫翅表面疏水耦合机理。结果表明,蝗虫翅表面具有规则排列的微米级柱状乳突结构,乳突直径为1.6～2.3μm,高为2.3～3.2μm,间距为6.8～7.6μm。翅表面为长链烃类、脂肪酸酯和脂肪酸醇构成的蜡质层,是天然疏水表面,具有较强疏水性(接触角为139.0°～150.4°)。液滴与翅表面呈复合接触,符合Cassie方程。翅表面的高疏水性是微米级粗糙结构(结构耦元)与蜡质晶体(材料耦元)协同作用的结果。     

平行连杆式变形翼结构设计及分布式驱动配置

为提高飞机飞行效率和多任务适应能力,设计一种兼顾高低速工况的变形翼骨架,并研究变形翼内部分布式驱动器的位置优化和数量布置问题。基于翼肋摆动变形方式,设计变弦长、变后掠、变面积、变展弦比的平行连杆式变形翼机构,以单元尺寸为参数,对翼肋摆动程度与展弦比进行分析,得到机翼参数变化曲线;以包含机翼骨架、驱动器和柔性蒙皮的单元为研究对象,通过实验法测定柔性蒙皮的等效弹簧刚度,并基于虚功原理,采用准静态力学分析方法,得到单元的力学模型,以单元变形量为目标优化函数,通过matlab优化工具箱fmincon函数求解,得到最优驱动器位置和蒙皮初始状态,并进行实验验证;采用Ansys软件模拟多个单元机构运动与弹性变形的耦合作用,得到多种驱动器布局下机构的最终平衡状态;设计了变形翼详细结构,完成了样机加工装配。结果表明:机翼平衡时的变形量与驱动器布局和结构刚度有关,当机翼结构刚度增强时,分布式驱动与单个驱动所做的变形量均收敛在理想值。采用分布式驱动会最大化变形量,更适合低刚度结构机翼,设计的变形翼样机可以实现连续变形。     

定子预旋角对泵喷推进器敞水脉动特性影响

为改善某泵喷推进器（简称泵喷）低频压力脉动,降低泵喷噪声辐射,在原有泵喷基础上分别调整定子进流角、出流角及安装角,并数值分析了前置泵喷一定范围内定子预旋角下的性能。分析表明:推力、扭矩和最高效率都随预旋角增大而增大,其中安装角影响最大,出流角次之,进流角最小;分析桨叶推力脉动频域结果,发现单叶片推力脉动受定子影响,其对应频率主要为BPF_s（定子叶频）倍频,并在1BPF_s最大;而桨叶总推力脉动频率受定子和转子共同影响,在4BPF_r达到最大。通过分析叶片表面压力标准差,发现桨脉动最强位置为前缘及叶梢附近,而定子则位于后缘;进一步分析定子和转子周围监测点压力脉动特性,得到主要频率信息为1BPF_r,并且在泵喷尾部中高半径处脉动最强。结果表明,泵喷低频脉动幅度随角度增加而增加,但角度调整方式对其影响规律在正、负角不同;此外,探究了桨叶前缘同一轴向、不同径向位置的相位关系,出流角和安装角对相位影响较大,并且相位关系依预旋角正、负分别呈两极化分布。     

The Influence of Additives on Crystallization of Polyvinyl Chloride

Acetanilide, adipic acid and potassium hydrogen phthalate were chosen as nucleating agents of polyvinyl chloride（PVC）, and their effects on PVC crystallization were studied by differential scanning calorimetry, wide angle X-ray diffraction and fourier transform infrared spectroscopy. The experimental results indicate that all of the three additives are compatible with PVC to some extent, but adipic acid＇s compatibility with PVC is less satisfactory. The three additives can improve PVC crystallinity, and acetanilide can decrease PVC glass transition temperature（T）and narrow PVC melting range, while adipic acid and potassium hydrogen phthalate rise T of PVC and widen its melting range. All additives do not affect PVC crystal system and all g samples are in orthorhombic system. All additives can improve （200）, （110）, （210） and （201, 111） planes growing. Moreover, acetanilide and adipic acid can shrink PVC spacings and improve the crystal perfection of PVC, but potassium hydrogen phthalate swells spacings and reduces the perfection of PVC crystal.     

Regularities of formation of ternary intermetallic compounds between two transition elements and one non-transition element

The pattern recognition methods and a four-parameter model, based on extended Miede-ma's cellular model of alloy phases, are used to study the regularities of formation of ternary compounds between two transition elements (T,T ') and one non-transition element (N) (T-T '-N system) . The criterion of formation can be expressed as some functions of φ (electronegativity), n1/3ws (valence electron density in Wagner-Seitz cell), R (Pauling's metallic radii) and Z (number of valence electrons in atom).     

Real-time accurate hand path tracking and joint trajectory planning for industrial robots (I)

Previously, researchers raised the accuracy for a robot’s hand to track a specified path in Cartesian space mainly through increasing the number of knots on the path and the number of the path’s segments, which results in the heavier online computational burden for the robot controller. Aiming at overcoming this drawback, the authors propose a new kind of real-time accurate hand path tracking and joint trajectory planning method. Through selecting some extra knots on the specified hand path by a certain rule and introducing a sinusoidal function to the joint displacement equation of each segment, this method can greatly raise the path tracking accuracy of robot’s hand and does not change the number of the path’s segments. It also does not increase markedly the computational burden of robot controller. The result of simulation indicates that this method is very effective, and has important value in increasing the application of industrial robots. Foundation item: Foundation of the Robotics Laboratory, Chinese Academy of Sciences (No. RL200002) Biography of the first author: TAN Guan-zheng, Dr., professor, born in Oct. 1962, majoring in artificial intelligence, robotics and automation.     

射流角度对车辆风窗玻璃除霜性能的影响

利用Fluent计算软件,采用标准kε-紊流模型,通过模拟冲击射流除霜时风窗玻璃外表面上霜层的二维固、液融化现象,研究了射流角度(碰撞角和平面角)对车辆风窗玻璃除霜效果的影响。文章重点阐述了射流角度对流动状态、玻璃表面温度、平均液相率、液态分数等参数的影响。结果表明,射流碰撞角和平面角对除霜效果的影响是非单调性的,存在最有利的作用参数区间;在约定条件下存在最佳效果的碰撞角(60°)和平面角(10°)。     

Erosion Resistance of CaO-AI203-SiO2 System Glass-Ceramics

The erosion resistance tests were used to research the erosion wear behavior of CaO-Al2O3-SiO2 system glass-ceramic. With the orthogonal test method, the factors thai affect the erosion wear of CaO-Al2O3-SiO2 system galss-ceramic such as pacticles property, impact angle, impact time, size of particles were discussed. The results show that erosion rate rises along a straight line at the early period of erosion wear. With the impact time increased, the erosion rate deviates from original staight line, tendency of the erosion rate increases, With the size of paricle increased , it will have more kinetic energy, the erosion rate of the surface of glass-ceramics ploate rises.     

平面非均质性对面积波及系数的影响

以五点井网渗流单元为例,应用二维两相黑油模型对均质地层和六种不同平面非均质分布地层的水驱面积波及系数进行了数值模拟计算。结果表明,不同的平面非均质分布可导致非均质地层在同一含水率下的面积波及系数大于或小于均质地层的面积波及系数,并且使其达到完全驱替时的含水率高于或低于均质地层的含水率。在实际的油田开发方案设计中。根据不...     

Experimental Study on Young′s Modulus of Concrete

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Impact of strain relaxation of AlGaN barrier layer on the performance of high Al-content AlGaN/GaN HEMT

Owing to large direct bandgap energy, high saturation drift velocity, large conduction band discontinuities, high thermal stability and strong piezoelectric and spontaneous po- larization[1-4], AlGaN/GaN HEMTs have advantages over electronic devices based on Si, GaAs and their alloys in high-frequency, -temperature and -power applications. Many researches show[5,6] that the characteristics of AlGaN/GaN HEMTs depend on two-dimensional gas (2DEG) in heterostructures which has intimate r…     

飞机总体设计阶段机翼结构质量分配方法研究

提出了一种机翼结构质量分配方法,能根据飞机总体设计参数,把机翼结构质量分配到承弯结构、承剪结构、分布气动载荷所需结构、起落架安装影响结构等12个功能结构部分。建立了飞机总体设计阶段机翼结构质量分配的分析模型,然后根据现有飞机机翼的质量和飞机总体几何参数,用参数优化方法确定了该分析模型中的结构修正系数,从而得到一个机翼结构质量分配模型,用8架飞机的机民办所完成的算例证明了该方法的有效性和合理性。