柔性双尾鳍效率的测量和优化

建立了仿生拍动推进推力和效率的测量平台,通过电机的转动扭矩、转动角速度及推进力计算得到仿生推进系统的推进效率.对本课题组研制的组合仿生无人水下航行器中柔性双尾鳍模型进行了测量与分析,结果表明柔性尾鳍推进时小摆幅摆动运动效率要高于大摆幅运动;双尾鳍推进方式在小摆幅模式下无论在推进力还是在效率方面都要优于单尾鳍.最后根据模型实验数据,优化了双尾鳍推进的运动参数,并用于优化UUV性能.     

大变形柔性多体系统非线性动力学数值仿真与实验研究

提出了一种作大范围运动柔性梁的非接触动态测试技术.在基于位移的柔性多体系统几何精确建模及非线性有限元分析技术的基础上,利用EAGLE-500运动分析系统及其相应的分析软件对作大范围运动钛合金柔性梁作了实验研究,并且利用之前提出的几何精确梁理论进行数值仿真.数值仿真结果与实验结果完全吻合,验证了作者所提的几何精确梁理论及...     

SD振子的设计及非线性特性实验研究初探

具有光滑与不连续转迁特征的SD振子发现和提出以来, 引起了广泛关注. 基于双稳系统大位移特征的测量法困难, SD振子的实验研究还未见报道. 该文提出并设计了具有SD振子系统光滑特征的非线性实验装置, 用实验的方法揭示由几何关系产生的强非线性系统的非线性动力学行为. 设计的非线性实验装置基本振动参数均有良好的可调性和可测量性, 对SD振子在不同频率及幅值的简谐激励作用下的非线性动力学响应进行了实验研究. 为克服大位移测量难题, 研究采用高速摄像机采集振子振动视频信号并进行分析. 结果表明, SD振子系统在一定的参数条件下会产生周期振动、周期5振动及混沌运动等复杂非线性动力学现象, 在相同实验参数条件下进行了数值仿真, 仿真结果与实验结果一致.      

HE PRELIMINARY INVESTIGATION ON DESIGN AND EXPERIMENTAL RESEARCH OF NONLINEAR CHARACTERISTICS OF SD OSCILLATOR

具有光滑与不连续转迁特征的SD振子发现和提出以来,引起了广泛关注.基于双稳系统大位移特征的测量法困难,SD振子的实验研究还未见报道.该文提出并设计了具有SD振子系统光滑特征的非线性实验装置,用实验的方法揭示由几何关系产生的强非线性系统的非线性动力学行为.设计的非线性实验装置基本振动参数均有良好的可调性和可测量性,对SD振子在不同频率及幅值的简谐激励作用下的非线性动力学响应进行了实验研究.为克服大位移测量难题,研究采用高速摄像机采集振子振动视频信号并进行分析.结果表明,SD振子系统在一定的参数条件下会产生周期振动、周期5振动及混沌运动等复杂非线性动力学现象,在相同实验参数条件下进行了数值仿真,仿真结果与实验结果一致.     

两关节压力驱动柔性仿生机器鱼的设计与仿真

为研究设计一种柔软度高、环境适应性强的新型仿生机器鱼, 模仿鲨鱼外形及鲔科鱼类的游动姿态, 设计了一种采用液压柔性驱动结构的仿生机器鱼. 针对单关节液压驱动柔性机器鱼存在其C型摆动姿态不符合鲔科鱼类摆动规律的问题, 采用两关节液压柔性驱动模拟鱼类S型摆动, 并根据液压柔性驱动器原理设计仿生鱼的内部结构. 依据理论波动方程确定机器鱼的摆动幅值, 借助数值模拟计算施加在柔性驱动器内部的压强载荷大小, 并分析计算液压柔性驱动器的驱动效率. 应用有限元分析软件模拟仿生鱼在流体中的自主游动过程, 并将两关节机器鱼与单关节机器鱼的自主巡游过程进行对比仿真, 获得两种机器鱼在流体中自主巡游时的运动姿态、游动速度及流场情况. 结果表明, 在相同的频率与尾鳍摆幅下, 两关节柔性机器鱼的巡游平均速度为0.29 BL/s (BL为鱼体体长), 高于单关节机器鱼巡游平均速度0.15 BL/s, 且由速度矢量图可得出两关节仿生鱼的S型摆动姿态更接近真实鱼类摆动规律, 并在运动过程中会产生一系列离散的反向卡门涡街, 推进效率高.      

两关节压力驱动柔性仿生机器鱼的设计与仿真

为研究设计一种柔软度高、环境适应性强的新型仿生机器鱼,模仿鲨鱼外形及鲔科鱼类的游动姿态,设计了一种采用液压柔性驱动结构的仿生机器鱼.针对单关节液压驱动柔性机器鱼存在其C型摆动姿态不符合鲔科鱼类摆动规律的问题,采用两关节液压柔性驱动模拟鱼类S型摆动,并根据液压柔性驱动器原理设计仿生鱼的内部结构.依据理论波动方程确定机器鱼的摆动幅值,借助数值模拟计算施加在柔性驱动器内部的压强载荷大小,并分析计算液压柔性驱动器的驱动效率.应用有限元分析软件模拟仿生鱼在流体中的自主游动过程,并将两关节机器鱼与单关节机器鱼的自主巡游过程进行对比仿真,获得两种机器鱼在流体中自主巡游时的运动姿态、游动速度及流场情况.结果表明,在相同的频率与尾鳍摆幅下,两关节柔性机器鱼的巡游平均速度为0.29 BL/s(BL为鱼体体长),高于单关节机器鱼巡游平均速度0.15 BL/s,且由速度矢量图可得出两关节仿生鱼的S型摆动姿态更接近真实鱼类摆动规律,并在运动过程中会产生一系列离散的反向卡门涡街,推进效率高.     

不锈钢点焊车体性能仿真模型的有效性分析

依据点焊车体结构传力特点,提出点焊车体性能有限元仿真模型的创建方法;以某不锈钢点焊地铁车为研究对象,在BS EN12663-2010标准中静态载荷的作用下,对其车体结构进行刚度和静强度有限元分析与评价,并将仿真结果与测试结果进行对比分析.结果表明:车体各位移测点的测试值与计算值的相对误差最大为9.5％;各区域应力测点的测试值与计算值的变化趋势基本一致,96％的数值较大应力测点的相对误差百分比在0.3％～15％之间.该车体有限元分析模型能很好地反映车体结构的实际刚度和传力特性,其建模方法可以推广到其他点焊结构性能仿真中.     

基于仿生人工关节的评价装置及磨损试验研究

基于仿生人工关节结构,利用连杆机构模拟关节弯曲/拉伸运动方式建立了仿生人工关节评价装置,同时对以小牛血清作为润滑介质的氧化锆-超高分子量聚乙烯(ZrO-UHMWPE)人工关节配副进行磨损性能测试.结果表明:所建立的装置不仅可以加速考察人工关节配副的磨损特性,还能够加速评价仿生关节囊的动态疲劳性能,同时实现转速、载荷以及运动角度等参数可调并具有较强可操作性; UHMWPE的磨损量与运动周期近似呈线性关系,UHMWPE的体积磨损率相对稳定,约为70～80 mm3/106周期,且具有较好的重复性与可靠性.     

自升式抛石整平装置自存工况抗滑移抗倾覆分析

对自升式抛石整平装置暴风自存工况下抗滑移和抗倾覆能力进行了分析.参考CCS《海上移动式平台入级规范》对暴风自存工况的环境载荷进行定义,运用ABAQUS中Subroutine子程序模块来进行环境载荷的施加.根据《移动式平台入级与建造规范》中对自升式平台抗滑移和抗倾覆的要求,对自升式抛石整平装置进行了校核.岩石基床采用基于Mohr-Coulomb屈服准则的理想弹塑性本构模型,位移和转角采用Swipe加载方法.经分析,设计的自升式抛石整平装置满足《规范》抗滑移和抗倾覆要求.     

弹丸侵彻混凝土加速度信号测试及分析

针对弹丸侵彻混凝土加速度信息获取及实测信号失效问题,采用弹载存储测试系统进行了实验,并基于LS-DYNA进行了高速碰撞过程的数值模拟,经处理后的数据曲线与实测侵深符合较好,数值模拟计算结果与实验结果较吻合。通过实验分析与理论推导相结合的方式对应力波、测试装置的基础运动和安装结构刚度、加速度计安装方式等部分影响因素进行了实测加速度信号的影响分析,分析结果对高g值冲击测试问题具有一定的参考价值。     

Effects of mass and chordwise flexibility on 2D self-propelled flapping wings

A self-propelled flexible flapping wing 2D numerical model undergoing a combined pitching and heaving motion is presented. Since such freely moving foil experiences zero net thrust, a definition of efficiency for this kind of problem is proposed and discussed against other formulations found in the literature. It is also shown that the deviation motion of wings such as that found in natural flyers is likely a consequence of the fluid–structure dynamics of the wings. The passive deviation motion observed in numerical simulations is either a consequence of a feathering mechanism referred to as rigid feathering or of the inertial displacement caused by the wing deformation. The effects of flexibility on the performance of the wing are also presented. It is found that flexibility may significantly enhance the efficiency in pressure-driven deformation cases. The rigid feathering mechanism is found to have an effect similar to that of the feathering caused by wing flexibility on the performances of pressure-driven deformation cases.     

Propulsion velocity of a flapping wing at low Reynolds number

This paper presents a computational fluid–structure interaction analysis for free movements with a flapping wing in a quiescent fluid. We demonstrated the moving velocity of a flapping wing according to the phase difference between the angle of attack and the positional angle in the case of a fruit fly with a Reynolds number of 136. If we considered the moving velocity of the flapping wing, the physics were different from that of hovering flight of previous studies, which did not consider the propulsive velocity and presented the advanced rotation of the angle of attack as the best mechanism for propulsion force, as compared to symmetric rotation and delayed rotation. We found that symmetric rotation produced a better propulsion velocity with less fluctuation in other direction than the advanced rotation. The hairpin vortex generated at the end of a stroke did not clearly contribute to the enhancement of propulsion; the wake capture is considered to be one of the main enhancements of the advanced rotation in a previous studies. We studied the effects of the angle of attack to determine why the fruit fly uses a large angle of attack during a constant angle of attack period. Larger angles of attack produced greater propulsion velocities. Further, larger angles of attack did not generate greater peak force during the rotation of the angle of attack at the reversal of stroke, but they produced less fluctuation at the reversal of the stroke and greater force during the constant angle of attack period.     

Force production and asymmetric deformation of a flexible flapping wing in forward flight

Insect wings usually are flexible and deform significantly under the combined inertial and aerodynamic load. To study the effect of wing flexibility on both lift and thrust production in forward flight, a two-dimensional numerical simulation is employed to compute the fluid–structure interaction of an elastic wing section translating in an inclined stroke plane while pitching around its leading ledge. The effects of the wing stiffness, mass ratio, stroke plane angle, and flight speed are considered. The results show that the passive pitching due to wing deformation can significantly increase thrust while either maintaining lift at the same level or increasing it simultaneously. Another important finding is that even though the wing structure and actuation kinematics are symmetric, chordwise deformation of the wing shows a larger magnitude during upstroke than during downstroke. The asymmetry is more pronounced when the wing has a low mass ratio so that the fluid-induced deformation is significant. Such an aerodynamic cause may serve as an additional mechanism for the asymmetric deformation pattern observed in real insects.     

A parametric investigation of the propulsion of 2D chordwise-flexible flapping wings at low Reynolds number using numerical simulations

This paper presents a numerical investigation of the effects of chordwise flexibility on flapping wings at low Reynolds number. The numerical simulations are performed with a partitioned fluid–structure interaction algorithm using artificial compressibility stabilization. The choice of the structural dimensionless parameters is based on scaling arguments and is compared against parameters used by other authors. The different regimes, namely inertia-driven and pressure-driven wing deformations, are presented along with their effects on the topology of the flow and on the performance of a heaving and pitching flapping wing in propulsion regime. It is found that pressure-driven deformations can significantly increase the thrust efficiency if a suitable amount of flexibility is used. Significant thrust increases are also observed in zero pitching amplitude cases. The effects of the second and third deformation modes on the performances of pressure-driven deformation cases are discussed. On the other hand, inertia-driven deformations generally deteriorate aerodynamic performances of flapping wings unless the behavior of the wing deformation is modified by the presence of sustainable superharmonics in a way that produces slight improvements. It is also shown that wing flexibility can act as an efficient passive pitching mechanism that allows fair thrust and better efficiency to be achieved when compared to a rigid pitching–heaving wing.     

摩擦自激振动引起摩擦面波状磨耗的试验研究

在销-盘摩擦磨损试验机上进行金属干摩擦试验,研究摩擦自激振动对盘试件磨痕表面轮廓的影响,采用激光位移传感器测量盘试件摩擦表面轮廓尺寸,用加速度传感器测量销试件的摩擦自激振动.试验结果表明：在干摩擦状态下,销-盘系统容易发生持续的摩擦自激振动,当摩擦时间达到一定数值后,盘试件的磨痕表面轮廓会出现明显的波浪形磨耗,波浪形磨损机理主要是疲劳磨损.分析表明波浪形磨耗的波长近似等于摩擦自激振动的周期与滑动速度的乘积,由此推断摩擦自激振动引起了摩擦表面的波浪形磨耗.     

翼型、机翼非定常运动模式下动态数值模拟

基于RANS方程,通过刚性动网格技术实现对翼型和机翼典型运动模式的描述,采用双时间推进方法和Roe空间离散格式对流场求解,构建了一个非定常气动计算平台;以NACA0012翼型为算倒进行了动态数值模拟可信度验证。数值模拟结果与试验数据吻合较好,升力和俯仰力矩的最大计算误差分别为3％和10％,表明了该平台的可靠性。另外,还数值模拟了M6机翼的动态非定常流场,并分析了两种湍流模型对非定常流场激波的捕捉能力。结果表明非定常流动中S-A湍流模型对激波的捕捉较B-L模型更敏感。文中开发的非定常计算平台对进一步解决三维复杂流场的流动问题有很高的工程应用价值。     

A numerical investigation into the effects of Reynolds number on the flow mechanism induced by a tubercled leading edge

Leading-edge modifications based on designs inspired by the protrusions on the pectoral flippers of the humpback whale (tubercles) have been the subject of research for the past decade primarily due to their flow control potential in ameliorating stall characteristics. Previous studies have demonstrated that, in the transitional flow regime, full-span wings with tubercled leading edges outperform unmodified wings at high attack angles. The flow mechanism associated with such enhanced loading traits is, however, still being investigated. Also, the performance of full-span tubercled wings in the turbulent regime is largely unexplored. The present study aims to investigate Reynolds number effects on the flow mechanism induced by a full-span tubercled wing with the NACA-0021 cross-sectional profile in the transitional and near-turbulent regimes using computational fluid dynamics. The analysis of the flow field suggests that, with the exception of a few different flow features, the same underlying flow mechanism, involving the presence of transverse and streamwise vorticity, is at play in both cases. With regard to lift-generation characteristics, the numerical simulation results indicate that in contrast to the transitional flow regime, where the unmodified NACA-0021 undergoes a sudden loss of lift, in the turbulent regime, the baseline foil experiences gradual stall and produces more lift than the tubercled foil. This observation highlights the importance of considerations regarding the Reynolds number effects and the stall characteristics of the baseline foil, in the industrial applications of tubercled lifting bodies.     

爆破开挖扰动下锚固节理岩质边坡位移突变特征与能量机理

针对白鹤滩水电站左岸坝基河谷底部边坡岩体爆破开挖,采用现场岩体位移监测、锚索轴力监测及数值模拟的手段,研究了爆破开挖扰动下锚固节理岩质边坡的位移突变特征及其能量机理。研究结果表明:对于深切河谷底部高地应力边坡岩体爆破开挖,爆炸荷载挤压及地应力作用下,岩体所积聚的应变能快速释放,导致了节理岩质边坡的位移突变,突变位移包括节理张开位移和岩体回弹位移两部分;地应力水平越高、岩体弹性模量越低,总的突变位移量越大;预应力锚索主要通过抑制节理张开位移来控制边坡岩体的位移突变,锚索预应力等级越高,其吸能和释能速率越高,对节理岩体位移突变的控制效果越好,当锚索的预应力等级高到一定程度后,节理岩体的突变位移不再随锚索预应力等级的升高而显著减小。     

HEAT-PIPE-COOLED THERMAL PROTECTION FOR THE LEADING EDGE OF THE WING

针对高超声速飞行器飞行时翼前缘存在着严重的气动加热问题,为了保证翼前缘的尖锐外形,提出疏导式热防护结构,利用内置高温热管结构为翼前缘提供热防护。采用数值模拟和电弧风洞试验的方法对翼前缘疏导式结构进行了分析,得到翼前缘内置高温热管具有的防热效果。数值模拟结果表明在一定热环境条件下,翼前缘驻点温度下降了304K,尾部最低温度升高了130K,实现了热流从高温区到低温区的疏导,减弱了翼前缘的热载荷,强化了翼前缘的热防护能力。通过电弧风洞试验可以获得相同的热防护结果,并且在一定飞行条件下高温热管可以自适应启动,验证了数值模拟方法的准确性以及翼前缘内置高温热管疏导式热防护结构的可行性。     

Moving line crack accompanied with damage zone subject to remote tensile loading

In the 1920s, a closed-form solution of the moving Griffith crack was first obtained by Yoffe. Based on Yoffe's solution, the Dugdale model for the moving crack case gives a good result. However, the Dugdale model fails when the crack speed is closed to the Rayleigh wave speed because of the discontinuity occurred in the crack opening displacement (COD). The problem is solved in this paper by introducing a restraining stress zone ahead of the crack tip and two velocity functions. The restraining stresses are linearly distributed and related to the velocity of the moving crack. An analytical solution of the problem is obtained by use of the superposition principle and a complex function method. The final result of the COD is continuous while the crack moves at a Rayleigh wave speed. The characteristics of the strain energy density (SED) and numerical results are discussed, and conclusions are given.