昆虫飞行的空气动力学

昆虫是最早出现、数量最多和体积最小的飞行者. 它们能悬停、跃升、急停、快速加速和转弯, 飞行技巧十分高超. 由于尺寸小, 因而翅膀的相对速度很小, 从而进行上述飞行所需的升力系数很大. 但昆虫翅膀的雷诺数又很低. 它们是如何在低雷诺数下产生高升力的, 是流体力学和生物学工作者都十分关心的问题. 近年来这一领域有了许多研究进展. 该文对这些进展进行综述, 并对今后工作提一些建议. 因2005 年前的工作已在几篇综述文章有了详细介绍, 该文主要介绍2005 年以来的工作. 首先简述昆虫翅的拍动运动及昆虫绕流的基本方程和相似参数; 然后对2005 年之前的工作做一简要回顾. 之后介绍2005 年后的进展, 依次为: 运动学观测; 前缘涡; 翅膀柔性变形及皱褶的影响; 拍动翅的尾涡结构; 翼/身、左右翅气动干扰及地面效应; 微小昆虫; 蝴蝶与蜻蜓; 机动飞行. 最后为对今后工作的建议.      

昆虫飞行——非常规空气动力学

<正> 许多证据表明,昆虫飞行的机理与飞机及直升机的机理大不相同。zanker&Gotz测出了被系住的果蝇所产生的瞬时力。并发现这些力不能用常规空气动力学理论来解释。这些力也是这些果蝇使用不一般的方法来产生升力的证据。 在飞机稳态飞行时,空气在机翼上方流动比下方快。这时绕机翼周围有一纯环流。正是具有附体环流的机翼在空气中的运动产生了升力。可是,如果机翼从静止开始加速,那么它必须移动比它本身宽度长几倍的距离,才会有环流绕流机翼而产生足够的升力以使飞机达到稳态飞行。这一现象叫做Wagner效应。     

昆虫是怎样飞行的

简述昆虫翅的拍动运动及昆虫飞行的控制方式, 介绍昆虫飞行的空气动力学原理和人们对这些原理的认识过程.     

模型昆虫翼作非定常运动时的气动力特性

基于Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程的数值解,研究了一模型昆虫翼在小雷诺数（Ｒｅ＝１００）下作非定常运动时的气动力特性,这些运动包括：翼启动后的常速转动,快速加、减速转动,常速转动中快速上仰（模拟昆虫翼的上挥或下拍、翻转等运动）有如下结果：在小雷诺数下,模型昆虫翼以大攻角（α＝３５°）作常速转动运动时,由于失速涡不脱落,可产生较大的升为系数。其机理是：翼转动时,翼尖附近（该处线速度大）上翼面压强比翼根附近（该处线速度小）的小得多,因而存在展向压强梯度,同时存在着沿展向的离心力,此展向压强梯度和离心力导致的展向流动在失速涡的轴向方向,其可避免失速涡脱落。模型昆虫翼在快速加、减速转动和快速上仰运动中,虽然雷诺数小,但由于在短时间内产生了大涡量,也可产生十分大的气动力,例如在快速上仰运动中,升力系数可大于１０。     

昆虫自由飞行参数的双棱镜虚拟双目测量

通过像机前加一个双棱镜实现单像机的虚拟双目拍摄,根据立体视觉原理可以获取空间点三维信息,该装置被用于测量昆虫自由飞行运动参数。如果双棱镜和像机摆放得当,可以简化立体视觉测量中对应点匹配这一最难步骤。实验获得了蜻蜓直飞过程中的一系列运动参数,将这些参数结合起来考察对于研究昆虫飞行机理非常有意义。特别地,我们对昆虫飞行中翅膀的柔性效应进行了初步讨论。     

昆虫飞行的高升力机理

对近年来关于昆虫产生非定常高升力的研究进行了综述和归纳.这方面的工作对生物学研究和微型飞行器等微型机械的仿生设计有重要意义.研究表明:果蝇等昆虫翅膀的拍动运动可产生很大的非定常升力,其平均值是定常值的2~3倍,足够平衡昆虫的重量,并有较大的富余用于机动飞行;产生高升力有三个因素:一是拍动开始阶段翅的快速加速运动,二是拍动中的不失速机制,三是拍动结束阶段翅的快速上仰运动.人们从能耗的角度考察了这些非定常高升力机制的正确性和可行性.当作悬停飞行的果蝇用以上机制产生平衡其重量的升力时,其比功率(支持单位身体质量所需的功率)约为29W/kg, 生化/机械效率约为17%. 这些值与人们基于对昆虫肌肉力学特性的研究所预估的值接近.果蝇前飞时,其比功率随速度变化的曲线是一J形曲线,而不是象飞机或鸟的那样是一U形曲线;这与人们基于昆虫新陈代谢率的测量数据所推断的结果一致.对于蜻蜒等(功能上)有前、后两对翅膀的昆虫,有以下初步结果:翅的下拍主要产生升力,上挥主要产生推力;下拍时的平均升力系数可达2~3,十分大,上挥时的平均推力系数可达1~2, 也很大,它们主要由非定常效应产生;前、后翅的相互干扰并未起增大升力和推力的作用,反而有一定的不利作用.      

运动参数惯性测量模拟弹设计与实验

在研制弹射式发射架的过程中,为了确保在高速飞行器上发射导弹的安全,需要预先在实验室内对发射架的弹射运动参数进行测试研究。而弹射分离过程时间短(仅为30～40 ms)、测量参数多(共18个运动和姿态参数),如何对其参数进行测量就成为一个研究重点。设计完成的弹射实验用模拟导弹是一种专用测试设备,它完全模拟真实导弹的机械特性,内部设计装有微型惯性测量系统(MIMS),可以在弹射过程中完全自主地对所有运动参数和姿态变化进行惯性测量,实验表明测量精度达到3%以内。其中应用的MIMS是惯性测量技术在该领域的创新型应用,具有测量范围大(±500(°)/s)、动态性能好(最高可达4 kHz)、操作简便等优势。     

卫星振动实验中台面加速度控制与过实验研究

针对航天飞行器振动台环境实验中的"过实验"问题与振动台控制方式展开研究.本文以被试结构和振动台为统一研究对象进行组合系统动力学建模,详细导出了"真实环境"、"台面加速度控制"和"界面力控制"等三种模式下的台面加速度、界面力、结构测点加速度响应等表达公式,并讨论了加速度控制和力控制下各自形成过实验的原因和频率位置,定义并解释了"双控"模式及其对过实验现象的补偿机理.借助离散算例仿真计算,解释了文中提出的各种概念及其数值效果.     

Johnson-Cook材料模型参数的实验测定

介绍一种通过Hopkinson拉伸实验、圆筒爆炸试验和计算机仿真来确定Johnson-Cook材料模型中相关常数的方法．     

TC材料的低压Hugoniot参数实验测量研究

采用高阻值锰铜压阻传感器,并通过一级轻气炮实验对TC材料的低压Hugoniot参数C0,λ进行了测量,实验得到的压力曲线与理论分析基本一致,并对压力曲线与密实材料的理论波形进行了比较和分析。通过对实验结果进行最小二乘法拟合,得到了该材料低压冲击时的Hugoniot压缩线以及低压Hugoniot参数C0,λ。拟合结果表明:该多孔材料的低压D-u线具有较大的分散性。     

Effects of Body Cross-sectional Shape on Flying Snake Aerodynamics

Despite their lack of appendages, flying snakes (genus Chrysopelea) exhibit aerodynamic performance that compares favorably to other animal gliders. We wished to determine which aspects of Chrysopelea’s unique shape contributed to its aerodynamic performance by testing physical models of Chrysopelea in a wind tunnel. We varied the relative body volume, edge sharpness, and backbone protrusion of the models. Chrysopelea’s gliding performance was surprisingly robust to most shape changes; the presence of a trailing-edge lip was the most significant factor in producing high lift forces. Lift to drag ratios of 2.7–2.9 were seen at angles of attack (α) from 10–30°. Stall did not occur until α > 30° and was gradual, with lift falling off slowly as drag increased. Chrysopelea actively undulates in an S-shape when gliding, such that posterior portions of the snake’s body lie in the wake of the more anterior portions. When two Chrysopelea body segment models were tested in tandem to produce a two dimensional approximation to this situation, the downstream model exhibited an increased lift-to-drag ratio (as much as 50% increase over a solitary model) at all horizontal gaps tested (3–7 chords) when located slightly below the upstream model and at all vertical staggers tested (±2 chords) at a gap of 7 chords.     

两种椭圆翼型高速气动特性实验研究

新概念旋转机翼飞机的主机翼既能高速旋转作为旋翼,又可锁定作为固定翼,所以只能使用特殊的前后对称翼型。针对主机翼翼型的这一特殊要求,对16％相对厚度,相对弯度分别为0％和3％的两种椭圆翼型的高速气动特性进行了风洞实验研究,试验分别在中国空气动力研究发展中心FL-21风洞和荷兰代尔夫特大学TST-27风洞进行,采用表面测压和尾排型阻测量技术。试验结果的对比分析表明,有弯度椭圆翼型的升力和力矩特性优于无弯度椭圆翼型,而阻力特性和最大升阻比劣于无弯度椭圆翼型。试验结果为旋转机翼飞机主机翼翼型的选取提供了参考。     

Experimental analysis of pre-compressed circular cylindrical shell under axial harmonic load

In this paper the nonlinear dynamics of circular cylindrical shells under axial static (compressive) and periodic resonant loads have been experimentally investigated, the goal is to study the dynamic scenario and to analyze nonlinear regimes. A special test rig has been developed for the experiment in order to apply a static axial load combined with a dynamic axial load. The setup allows for investigating the linear behavior under static preload by means of the usual modal testing techniques; moreover, it allows for analyzing the nonlinear response which occurs when the dynamic axial load is periodic and gives rise to complex resonances. The complex dynamics, arising when a periodic axial load excites the asymmetric (shell like) modes, are analyzed by means of amplitude frequency diagrams, waterfall spectrum diagrams, bifurcation diagrams of Poincaré maps; a deep analysis of time histories, spectra, phase portraits and Poincaré maps completes the study of the complex dynamic scenario.     

Experimental and numerical investigations on flashing-induced instabilities in a single channel

During the start-up phase, natural circulation BWRs (NC-BWRs) need to be operated at low pressure conditions. Such conditions favor flashing-induced instabilities due to the large hydrostatic pressure drop induced by the tall chimney. Moreover, in novel NC-BWR designs the steam separation is performed in the steam separators which create large pressure drops at the chimney outlet, which effect on stability has not been investigated yet.In this work, flashing-induced oscillations occurring in a tall, bottom heated channel are numerically investigated by using a simple linear model with three regions and an accurate implementation for estimating the water properties. The model is used to investigate flashing-induced instabilities in a channel for different values of the core inlet friction value. The results are compared with experiments obtained by using the CIRCUS facility at the same conditions, showing a good agreement. In addition, the experiments on flashing-induced instabilities are presented in a novel manner allowing visualizing new details of the phenomenon numerical stability investigations on the effect of the friction distribution are also done. It is found that by increasing the total restriction in the channel the system is destabilized. In addition, the chimney outlet restriction has a stronger destabilizing effect than the core inlet restriction. A stable two-phase region is observed prior to the instabilities in the experiments and the numerical simulations which may help to pressurize the vessel of NC-BWRs and thus reducing the effects of flashing instabilities during start-up.     

Experimental analysis of the flow characteristics of a pressure-atomised spray

An experimental setup has been created to allow measurements of the properties of the gas phase, the liquid phase and the mixture in a pressure-atomised spray of water, in terms of both mean quantities and Reynolds stresses. This setup involves laser Doppler velocimetry for determining the velocity of either the gas or liquid phase, according to the parameters used, such as seeding or no-seeding of the ambient air, laser source power, or photo-multiplier gains, droplet tracking velocimetry for determining the velocity and characteristic size of the droplets, and a single optical probe for determining the mean volume fraction of the liquid, from which the liquid mean mass fraction and the mean density of the mixture are inferred. The experimental conditions, in particular in terms of liquid and gas Weber numbers, were chosen in a range for which the liquid phase turbulent kinetic energy should be mainly responsible for the liquid-jet primary break-up, these flow conditions lying within the second wind-induced atomization regime. Results reported herein are more specifically focused on the region ranging from 400 nozzle diameters to 800 nozzle diameters, where the liquid core is disrupted. They provide new information about the formation and properties of such pressure-atomised sprays, in particular in terms of the role played by the Reynolds stresses resulting from the slip velocity between the liquid and the gas. The mean slip velocity is directly related to the turbulent flux of liquid. Such information will be used in the future to develop new turbulence models since very limited experimental information is so far available for these terms.     

单纤维实验技术的现状和展望

本文综述了目前流行的测量纤维／树脂界面力学性能的单纤维实验技术。重点介绍了三种单纤维实验技术——单纤维拔出法、单纤维段埋入法和单纤维压出法的基本原理。讨论了三种单纤维实验技术在理论和应用上的发展重点     

Experimental study of large amplitude vibrations of a thin plate in contact with sloshing liquids

The linear and geometrically nonlinear (large amplitude) dynamical response of a thin plate in contact with water on one or both sides has been experimentally studied, considering different filling levels. The free liquid surface is free to slosh and the water is delimited by practically rigid walls, except for the thin plate. An experimental method for monitoring and measuring the free surface waves of the fluid has been also used in order to analyze the behavior of the liquid free surface during the nonlinear vibration of the plate forced by harmonic excitation. The plate deflection due to hydrostatic pressure plays a significant role in changing the plate nonlinearity, but tests with liquid on both sides eliminating this effect have been also presented. For excitation in the frequency neighborhood of the fundamental mode of the plate, the oscillation of the free surface of the liquid is characterized by a very large 1/2-subharmonic component.     

Experimental study of two-phase flow in three sandstones. II. Capillary pressure curve measurement and relative permeability pore space capillary models

By means of the porous plate method and mercury porosimetry intrusion tests, capillary pressure curves of three different sandstones were measured. The testing results have been exploited jointly with three relative permeability models of the pore space capillary type (Burdine’s model type), these models are widely used and in rather distinct fields. To do so, capillary pressure has been correlated to saturation degree using six of the most popular relations encountered in the literature. Model predictions were systematically compared to the experimentally measured relative permeabilities presented in the first part of this work. Comparison indicated that the studied models underestimate the water relative permeability and over-estimate that of the non-wetting phase. Moreover, this modeling proves to be unable to locate the significant points that are the limits of fields of saturation where the variation of the relative permeabilities becomes consequent. We also showed that, if pore structure is modeled as a “bundle of capillary tubes”, model predications are independent of the capillary pressure curve measuring method.