Reduced order nonlinear aeroelasticity of swept composite wings using compressible indicial unsteady aerodynamics

Nonlinear dynamic aeroelasticity of composite wings in compressible flows is investigated. To provide a reasonable model for the problem, the composite wing is modeled as a thin walled beam (TWB) with circumferentially asymmetric stiffness layup configuration. The structural model considers nonlinear strain displacement relations and a number of non-classical effects, such as transverse shear and warping inhibition. Geometrically nonlinear terms of up to third order are retained in the formulation. Unsteady aerodynamic loads are calculated according to a compressible model, described by indicial function approximations in the time domain. The aeroelastic system of equations is augmented by the differential equations governing the aerodynamics lag states to derive the final explicit form of the coupled fluid-structure equations of motion. The final nonlinear governing aeroelastic system of equations is solved using the eigenvectors of the linear structural equations of motion to approximate the spatial variation of the corresponding degrees of freedom in the Ritz solution method. Direct time integrations of the nonlinear equations of motion representing the full aeroelastic system are conducted using the well-known Runge–Kutta method. A comprehensive insight is provided over the effect of parameters such as the lamination fiber angle and the sweep angle on the stability margins and the limit cycle oscillation behavior of the system. Integration of the interpolation method employed for the evaluation of compressible indicial functions at any Mach number in the subsonic compressible range to the derivation process of the third order nonlinear aeroelastic system of equations based on TWB theory is done for the first time. Results show that flutter speeds obtained by the incompressible unsteady aerodynamics are not conservative and as the backward sweep angle of the wing is increased, post-flutter aeroelastic response of the wing becomes more well-behaved.     

自锚式悬索桥主缆状态影响参数分析

对自锚式悬索桥主缆的空缆状态和成桥状态进行了影响参数分析。以主缆线形、主缆对主索鞍水平分力和合力作用点位置为控制目标,定义了主缆合理成桥状态;以吉林市雾凇大桥为例,建立了主缆有限元模型。改变模型参数,计算主缆在不同参数下的空缆状态和成桥状态,并将其与基准状态进行比较,具体研究各影响参数对主缆状态的影响情况。主缆自重和空缆架设温度均对主缆状态影响甚微,中跨主缆无应力索长主要影响其自身线形,而边跨无应力索长会对各控制目标均造成较大影响;以空缆架设线形为控制条件时,发生在空缆架设前的主索鞍和后锚面位置偏差对主缆成桥状态不构成影响,但其发生在成桥运营阶段的变形会严重影响主缆成桥状态。工程实例分析结果表明,主缆抗拉刚度和成桥吊杆力均会对主缆成桥状态造成一定影响,建议在空缆架设前实测主缆抗拉刚度和梁段标准节间重量,控制两者偏差在合理范围内;建议对空缆架设线形设置预抬高,以抵消主索鞍和后锚面在成桥阶段的变形,该结论对自锚式悬索桥的空缆架设工作具有较强的指导意义和参考价值。     

悬索桥主缆过三定点的精确线形数值解析计算方法

系统阐述了悬索桥分段悬链线理论及其基本方程,对变化刚度迭代法计算主缆线形进行了深入分析,发现了其不收敛的情况。对此,提出主缆过三定点的精确线形E-M解析计算方法,通过主缆平衡方程分别推导出末点和中间点标高与主缆左端水平和竖向分力H和V的解析关系式,得出综合考虑末点和中间点标高误差影响的H和V的修正迭代式。算例验证与有限元方法吻合较好,在吊索索力极不均匀的情况下,E-M计算方法仍能有效满足主缆线形过三定点的要求,收敛速度快精度高。     

具有滑移式散索鞍的悬索桥主缆架设分析

为分析悬索桥的主缆架设,首先建立了滑移式索鞍纵向复合圆曲线的数学描述方法,进而利用弹性悬链线的精确解,建立了两索鞍间索跨的分析方法,并用于确定由成桥几何控制参数确定的悬索桥成桥状态,随后通过移动鞍座寻找平衡位置,可得到空载时索鞍预偏量、各跨垂度、索股张力和索夹位置等重要参数。这种解析迭代法可以考虑散索鞍重量的影响,以及主梁的架设对索鞍支承面的弹性压缩。算例表明本文所建立的方法是正确的。工程算例还表明具有不同纵向曲线的索鞍对悬索桥结构的整体静力分析结果影响甚微,且忽略散索鞍的重量将使架设时锚跨侧索股的张拉力偏大。     

悬索桥结构分析中的索-鞍座单元

为在悬索桥结构的有限元分析中真实、简洁、高效地模拟索鞍,本文建立了一类新的单元。新单元包括索段的一端固定在与其接触部分为单一半径圆弧的索鞍上,另一端分别位于索鞍两侧的两节点“左索-鞍座单元”和“右索-鞍座单元”,以及索段两端点分别位于索鞍两侧,中间一点固定于鞍座上的三节点“索-鞍座单元”,后者的鞍槽可为两不同半径圆弧的组合。根据要求的成桥状态几何参数确定结构的无应力状态时,可利用前二者进行悬索桥的单跨分析。新单元通过自动调整索与鞍座的脱离点而处于平衡状态,从而简化了计算。单元算法的推导基于有限元分析的基本原理和弹性悬链线的精确解,并利用了处于平衡状态时索与鞍座之间的内力关系。新单元可象常规单元一样直接用于成桥状态或施工过程中悬索桥结构的有限元分析。设计的算例验证了新单元的正确性,并举例说明了新单元在悬索桥结构分析中的应用。     

双缆悬索桥空缆状态主缆抗滑安全性研究

为指导双缆悬索桥上下缆垂跨比的取值，明确双缆悬索桥施工阶段主缆抗滑稳定性，提出一种主缆在施工阶段空缆状态下的抗滑安全系数计算方法。基于上缆变下缆的主缆布置方式，通过双缆悬索桥成桥状态反推空缆状态主缆垂度，根据空缆状态下主缆线形为悬链线计算中塔塔顶鞍座处缆力及包角，并据此计算空缆状态抗滑安全系数。建立多塔悬索桥有限元模型对提出的公式进行验证，分析成桥状态上下缆垂跨比和桥梁跨度的取值对空缆到成桥状态主缆垂度变化以及抗滑安全系数的影响。结果表明，采用本文公式计算的双缆悬索桥空缆状态下抗滑安全系数精度较高；上下缆垂跨比对空缆状态主缆抗滑安全性影响较大，抗滑安全系数随着上下缆垂跨比差值的增大迅速减小；空缆状态主缆抗滑安全系数受跨度影响不大，其随跨度增大略有提高。在实际的双缆悬索桥初步设计过程中应考虑施工阶段主缆抗滑稳定性，选择适宜的上下缆垂跨比，采取措施提高施工阶段主缆抗滑安全性。     

Analysis of self-excited forces for a box-girder bridge deck through unsteady RANS simulations

This paper presents the results of two-dimensional numerical simulations of the flow field around a trapezoidal box-girder bridge section with later cantilevers, experiencing small-amplitude heaving or pitching harmonic oscillations. Unsteady Reynolds-averaged Navier–Stokes equations are solved in conjunction with an eddy-viscosity and an explicit algebraic Reynolds stress model. Flutter derivatives are determined and compared with wind tunnel results, showing fairly good agreement. The degree of sharpness of the deck lower edges is found to play a key role in the aeroelastic behavior of the profile. In particular, the bridge section fully behaves as a bluff body and is prone to low-reduced-wind-speed torsional galloping in the case of perfectly sharp edges. By contrast, the presence of a small radius of curvature in the section lower corners changes the nature of the instability to coupled flutter and significantly postpones the stability threshold, in line with a quasi-streamlined body behavior. Moreover, a wide sensitivity study is carried out, investigating the influence on the self-excited forces of the amplitude of oscillation, mean angle of attack and Reynolds number. In particular, the numerical simulations for the geometry with smooth lower edges highlight the regime transition occurring when the Reynolds number is varied, with significant effects on the flutter derivatives. Finally, the numerical flow visualizations provide a physical explanation of some phenomena observed in the wind tunnel experiments.     

LES of the flow around several cuboids in a row

This paper presents Large Eddy Simulations (LES) of flow around a four-vehicle platoon when one of the platoon members was forced to undergo in-line oscillations. The LES were made at the Reynolds number of 10⁵ based on the height of the vehicles. Combinations of two different frequencies corresponding to non-dimensional frequencies at the Strouhal numbers St₁ = 0.025 and St₂ = 0.013 and two oscillation amplitudes were used in this study. The methodology was validated by comparisons with data from previous experimental investigations. In order to highlight the dynamic effects, comparisons were made with steady results on a single vehicle and on a four-vehicle platoon. Large differences were found in the flow structures between quasi-steady and dynamic results. Furthermore, the behavior of the drag coefficient of the upstream neighbor of the oscillating model was investigated.     

The influence of the wake of a flapping wing on the production of aerodynamic forces

The effect of the wake of previous strokes on the aerodynamic forces of a flapping model insect wing is studied using the method of computational fluid dynamics. The wake effect is isolated by comparing the forces and flows of the starting stroke (when the wake has not developed) with those of a later stroke (when the wake has developed). The following has been shown. (1) The wake effect may increase or decrease the lift and drag at the beginning of a half-stroke (downstroke or upstroke), depending on the wing kinematics at stroke reversal. The reason for this is that at the beginning of the half-stroke, the wing ``impinges' on the spanwise vorticity generated by the wing during stroke reversal and the distribution of the vorticity is sensitive to the wing kinematics at stroke reversal. (2) The wake effect decreases the lift and increases the drag in the rest part of the half-stroke. This is because the wing moves in a downwash field induced by previous half-stroke's starting vortex, tip vortices and attached leading edge vortex (these vortices form a downwash producing vortex ring). (3) The wake effect decreases the mean lift by 6%–18% (depending on wing kinematics at stroke reversal) and slightly increases the mean drag. Therefore, it is detrimental to the aerodynamic performance of the flapping wing. The project supported by the National Natural Science Foundation of China (10232010) and the National Aeronautic Science Fund of China(03A51049) The English text was polished by Xing Zhang     

Bianalytic functions, biharmonic functions and elastic problems in the plane

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The effects of corrugation and wing planform on the aerodynamic force production of sweeping model insect wings

The effects of corrugation and wing planform (shape and aspect ratio) on the aerodynamic force production of model insect wings in sweeping (rotating after an initial start) motion at Reynolds number 200 and 3500 at angle of attack 40° are investigated, using the method of computational fluid dynamics. A representative wing corrugation is considered. Wing-shape and aspect ratio (AR) of ten representative insect wings are considered; they are the wings of fruit fly, cranefly, dronefly, hoverfly, ladybird, bumblebee, honeybee, lacewing (forewing), hawkmoth and dragonfly (forewing), respectively (AR of these wings varies greatly, from 2.84 to 5.45). The following facts are shown. (1) The corrugated and flat-plate wings produce approximately the same aerodynamic forces. This is because for a sweeping wing at large angle of attack, the length scale of the corrugation is much smaller than the size of the separated flow region or the size of the leading edge vortex (LEV). (2) The variation in wing shape can have considerable effects on the aerodynamic force; but it has only minor effects on the force coefficients when the velocity at r ₂ (the radius of the second moment of wing area) is used as the reference velocity; i.e. the force coefficients are almost unaffected by the variation in wing shape. (3) The effects of AR are remarkably small: when AR increases from 2.8 to 5.5, the force coefficients vary only slightly; flowfield results show that when AR is relatively large, the part of the LEV on the outer part of the wings sheds during the sweeping motion. As AR is increased, on one hand, the force coefficients will be increased due to the reduction of 3-dimensional flow effects; on the other hand, they will be decreased due to the shedding of part of the LEV; these two effects approximately cancel each other, resulting in only minor change of the force coefficients. The project supported by the National Natural Science Foundation of China (10232010 and 10472008) and Ph. D. Student Foundation of Chinese Ministry of Education (20030006022) The English text was polished by Keren Wang.     

Unsteady aerodynamic forces and power requirements of a bumblebee in forward flight

Aerodynamic forces and power requirements in forward flight in a bumblebee (Bombus terrestris) were studied using the method of computational fluid dynamics. Actual wing kinematic data of free flight were used in the study (the speed ranges from 0 m/s to 4.5 m/s; advance ratio ranges from 0–0.66). The bumblebee employs the delayed stall mechanism and the fast pitching-up rotation mechanism to produce vertical force and thrust. The leading-edge vortex does not shed in the translatory phase of the half-strokes and is much more concentrated than that of the fruit fly in a previous study. At hovering and low-speed flight, the vertical force is produced by both the half-strokes and is contributed by wing lift; at medium and high speeds, the vertical force is mainly produced during the downstroke and is contributed by both wing lift and wing drag. At all speeds the thrust is mainly produced in the upstroke and is contributed by wing drag. The power requirement at low to medium speeds is not very different from that of hovering and is relatively large at the highest speed (advance ratio 0.66), i.e. the power curve is J-shaped. Except at the highest flight speed, storing energy elastically can save power up to 20%–30%. At the highest speed, because of the large increase of aerodynamic torque and the slight decrease of inertial torque (due to the smaller stroke amplitude and stroke frequency used), the power requirement is dominated by aerodynamic power and the effect of elastic storage of energy on power requirement is limited.The project supported by the National Natural Science Foundation of China (10232010) and the National Aeronautic Science fund of China (03A51049)The English text was polished by Xing Zhang.     

大跨径悬索桥空气静力和动力分析的影响因素研究

随着悬索桥跨径的增大,缆索直径以及作用在其上的风荷载、风与结构相互作用的非线性效应以及风速空间分布的非均匀性都将显著增强。以润扬长江大桥为背景,进行了缆索风荷载、风与结构相互作用的非线性效应以及风速空间非均匀分布等因素对大跨径悬索桥空气静力和动力特性影响的数值分析。分析结果表明:这些因素对大跨径悬索桥空气静力特性的影响比较大;但是对于空气动力稳定性而言,风与结构相互作用的非线性效应的影响比较显著,而其它两个因素则基本没有影响。     

基于MTMD的大跨度人行悬索桥人致振动控制

大跨度人行悬索桥柔度大且阻尼小,易在人群荷载激励下产生过大振动,导致舒适度不满足规范要求.对于此类结构,需要采取有效减振措施控制其动力响应.本文介绍了多重调谐质量阻尼器(MTMD)对主跨600 m人行悬索桥的人致振动控制性能.利用有限元软件建立了某大跨度人行悬索桥模型,以德国EN03规范为计算依据,计算了悬索桥的人致振...     

Analysis of hysteresis and phase shifting phenomena in unsteady three-dimensional wakes

The aerodynamic characteristics of automobiles are greatly influenced by the unsteady change in the direction of relative airflow. The aim of this paper is to analyse how such a change influences vehicle wake flow patterns. An analysis was conducted on a simplified model capable of reproducing the typical structures encountered under the aerodynamic conditions of an automobile. The results were processed by mapping the steady and unsteady total pressure losses around the model. The findings should enable automobile development engineers inter alia to identify and analyse the physical phenomena that occur when a vehicle is subjected to a sudden gust of side wind.List of symbols B rod - l length of rod B (m) - angle of rod B (degrees) - D disk - P connection point between disk D and rod B - M _o drive motor of disk D - O centre of rotation of disk D - e radius of disk D (m) - angle of disk (degrees) - t moment of time t (s) - _o angle (degrees) at instant of time t=0 - d diameter of model (m) - C centre of rotation of model - x _c abscissa of centre of rotation C of model (m) - M connection point between model and rod B - pi value=3.14159 - incidence of model (degrees) - _M maximum value of incidence (degrees) - _m minimum value of incidence (degrees) - angular amplitude (degrees) - _c critical angle of incidence (degrees) for steady evolutions - critical angle of incidence (degrees) for the unsteady evolutions - ̄ mean angle of incidence (degrees) - angle (degrees) of the model such that =+ - pulse (rad s^–1) - T period (s) - f frequency (Hz) - R radius of model in meter (m) - velocity vector of incident airflow - V _o intensity of velocity vector (m s^–1) - P _io total pressure associated with upstream airflow velocity (Pa) - P _i local total pressure (Pa or J m^–3) - density (kg m^–3) - C _x drag coefficient - total pressure coefficient - (m, n) dimensions of grid: lines m, columns n - x X coordinate of sampling plane (m) - y _j Y coordinate of point of index j for j[1,n] - z _k Z coordinate of point of index k for k[1,m] - P _i (x,y _j ,z _k ,(t)) continuous data of unsteady total pressure (Pa) - discrete data of unsteady total pressure (Pa) - N number of tomographic images, from 1 upwards over an oscillation period T - maximum value of total pressure coefficients for steady evolutions - maximum value of total pressure coefficients for unsteady evolutions and increasing incidences - maximum value of total pressure coefficients for unsteady evolutions and decreasing incidences - differential between and - differential between and - phase shifting (degrees)     

Monitoring of the Alamillo cable-stayed bridge during construction

The Alamillo Bridge is one of the long-span bridges crossing the Guadalquivir River. It was built on the occasion of Expo '92 in 1992 in Sevilla, Spain. The bridge is a cable-stayed structure spanning 200 m without any intermediate supports. Its originality is the lack of back stays and the balancing of the front stays through the backward inclination of a massive pylon. This paper shows the importance of experimental in situ techniques when applied to unconventional civil engineering structures and how—with the help of an important amount of accurate instrumentation, monitoring the most important experimental variables—it was possible to build the bridge correctly, safely, and on schedule.     

基于综合非线性优化方法的倒张型悬索桥非线性优化设计

提出随机优化、零阶优化和一阶优化相结合的综合非线性优化方法,并通过对ANSYS程序的二次开发编制全面优化设计和非线性有限元分析的综合辅助程序,从而对倒张型悬索桥进行非线性优化设计,以更合理地确定倒张型悬索桥设计中的关键因素,最终使倒张型悬索桥的受力和变形达到均匀合理的状态,以利于实际工程设计和应用.从优化设计前后的对比可以看出,本文的综合非线性优化方法和综合辅助程序简单有效,优化的效果显著.     

Comparison of three spectral methods for the Benjamin-Ono equation: Fourier pseudospectral, rational Christov functions and Gaussian radial basis functions

The Benjamin-Ono equation is especially challenging for numerical methods because (i) it contains the Hilbert transform, a nonlocal integral operator, and (ii) its solitary waves decay only as O(1/|x|²). We compare three different spectral methods for solving this one-space-dimensional equation. The Fourier pseudospectral method is very fast through use of the Fast Fourier Transform (FFT), but requires domain truncation: replacement of the infinite interval by a large but finite domain. Such truncation is unnecessary for a rational basis, but it is simple to evaluate the Hilbert Transform only when the usual rational Chebyshev functions TB_n(x) are replaced by their cousins, the Christov functions; the FFT still applies. Radial basis functions (RBFs) are slow for a given number of grid points N because of the absence of a summation algorithm as fast as the FFT; because RBFs are meshless, however, very flexible grid adaptation is possible.