气动耦合扭转非线性振动的稳定性分析

本文在新的非线性气动力模型的基础上，推导出结构与风耦合作用的新非线性扭转气动力项，研究了桥梁的非线性稳定性问题，不仅给出了桥梁发生颤振的临界风速，还在时域内给出了扭转位移与速度的时程曲线，并得到了有益的结论。     

采用压电材料提高超声速飞行器壁板结构的颤振特性

采用压电材料对结构进行振动主动控制已经进行了广泛研究,论文进一步采用压电材料改进超声速壁板结构的气动弹性颤振特性,研究中考虑压电材料力电耦合效应的影响.采用Hamilton原理和Rayleigh-Ritz方法建立壁板及压电材料整体结构的运动方程,采用超声速活塞理论模拟气动力,利用加速度反馈控制策略对压电材料施加外电压,获得结构的主动质量.求解运动方程的特征值问题获得固有频率,进而确定气动弹性颤振边界,分析了反馈控制增益对超声速飞行器壁板结构主动颤振特性的影响,研究表明,采用压电材料可以提高超声速壁板结构的气动弹性颤振特性.     

热环境下壁板非线性颤振分析

基于一阶活塞气动力理论,采用Von Karman大变形应变-位移关系建立了无限展长壁板热环境下颤振方程,采用伽辽金方法对方程进行离散处理.取温度为分叉参数,研究壁板颤振时的分叉及混沌等复杂动力学特性.结果表明:温度载荷降低了系统的颤振临界动压,改变了颤振特性.在整个分岔参数范围内,系统呈现出较为复杂的变化,包括衰减振动、极限环振动、拟周期振动和混沌型振动.当考虑材料热效应时,系统的颤振动压将进一步降低,其响应也表现出更为丰富的非线性动态力学行为.     

基于流场定常化的桥梁颤振分析简化数值方法

基于数值方法实现快速有效地分析评价大跨桥梁颤振稳定性.针对强迫振动法识别颤振导数试验中的大跨桥梁二维节段模型.利用RNG κ-ε湍流模型并采用有限体积法求解桥梁模型绕流二维不可压缩流体Navier-Stokes方程.通过计算桥梁断面模型在周期运动中少数离散时刻的气动力,利用最小二乘法计算颤振导数,采用SCANLAN方法求解颤振临界风速,最终进行颤振稳定性分析.通过该方法计算出了丹麦Great Belt East桥和我国虎门大桥的颠振临界风速.计算结果与已有试验结果十分接近,进而验证了该数值方法的有效性和可靠性.     

地面颤振试验系统气动插值点优化配置方法研究

地面颤振试验(ground flutter test, GFT)系统采用少量激振器模拟连续分布气动力，为实现气动插值点的缩聚，推导了地面颤振试验系统的控制方程，对比了GFT系统和原颤振系统控制方程在广义力项区别，定义了激/测振点位置优化的目标函数；为了提高插值精度，充分利用结构振动已知信息，提出了虚拟激/测振点技术；采用分群粒子群算法兼顾局部寻优和全局寻优，搭建优化流程，对插值点进行优化配置。基于平板机翼开展了GFT系统激/测振点位置优化计算，构建了地面集中气动力并进行了颤振特性测试试验。试验结果表明，本研究提出的方法精度较高，满足地面颤振试验的需求。     

风力机叶片压电振动的主动控制研究

提出了将智能材料粘贴在叶片表面或嵌入叶片内部形成新结构的概念。本文将智能材料作为传感器和作动器,通过机电耦合抑制叶片的振动;利用有限元软件 Algor 分析在气动力作用下叶片的应力、应变;基于压电陶瓷第一压电方程,将风电叶片简化成柔性悬臂梁,建立了压电智能悬臂梁状态空间的动力学模型;针对此系统利用最优控制理论进行主动振动控制,设计了在系统低阶模态空间的振动控制器。最后通过计算机仿真得出：系统振动幅度缩小了约20%,振动时间减少了约80%,从而说明了此主动振动控制方法的有效性和可行性,对防止叶片这一弹性体发生颤振也起到一定的作用。     

安装固定气动翼板的大跨桥梁抖振分析

建立了安装固定气动翼板的大跨桥梁多模态耦合抖振分析框架，推演了作用在整个桥梁-气动翼板系统上的抖振力和自激力的显式表达式，考虑了多模态耦合效应．基于有限元法，作用在主梁-气动翼板系统上的抖振力转化为节点力，进一步得到作用在整个桥梁上的抖振力并导出了其功率谱密度矩阵；作用在主梁．气动翼板系统上的气弹自激力转化为节点力，并将其表达为气弹刚度矩阵和气弹阻尼矩阵．通过组集得到系统的运动方程，然后运用虚拟激励法在频域计算系统的抖振响应．以某大跨斜拉桥为例进行研究，结果表明：在主梁下方安装-对固定气动翼板后，主梁的扭转角位移、角加速度以及侧向加速度响应能够得到有效控制。     

尾流激励的叶片气动力降阶模型

气动力降阶模型是研究叶片气动弹性振动快速高效的新方法。现有气动力降阶模型的研究主要集中在叶片颤振方面,没有涉及更为常见的上游尾流激励的叶片振动问题。本文提出基于Volterra级数的尾流激励叶片气动力降阶模型,为尾流激励下叶片振动和动静叶干涉振动研究提供了新的思路。采用行波法简化尾流的参数个数,用阶跃信号法识别降阶模型的核函数。二维叶片的算例结果表明,本文方法可以较准确地描述尾流激励引起的叶片气动力振荡,而且计算效率极高。     

基于主动控制策略的机翼颤振特性模拟

航空航天飞行器舵翼类结构的气动颤振是一种灾难性的动力学行为.在基于偶极子理论的气动弹性动力学模型中,气动载荷可表达为基于结构动力学响应的一种状态反馈的闭环控制力,控制律取决于翼型的几何参数、材料参数、结构动力学特性以及来流速度等多种条件,通常需通过实际飞行或风洞实验进行辨识与检验.在实验室条件下,以系统动力学响应的模态特征等效为前提,提出了一种基于人工主动控制的方式进行气动载荷下舵翼类结构自激颤振的特征值跟踪策略.建立并讨论了等效系统的非自伴随动力学微分方程及其特征方程的求解过程,并与通用软件的计算结果进行了对比,二者具有较好的一致性.通过优化搜索分别获得了位移和速度的最优反馈点、最优作动点位置及最优反馈增益系数,经对比计算拟合得到风速–位移增益曲线和风速–速度增益曲线,从而实现了由单点反馈、单点作动的集中力的闭环控制等效系统的真实气动力分布控制.仿真算例表明,由此预示的实验过程无需辨识和重构非定常气动力的时域波形,无需其他干预即可实现地面模拟实验,主动控制的效果满足预期,初步实现了自激颤振的特征值跟踪,为进一步推动主动控制模拟实验及颤振参数辨识提供了基础.     

尾流激励的叶片气动力降阶模型

气动力降阶模型是研究叶片气动弹性振动快速高效的新方法。现有气动力降阶模型的研究主要集中在叶片颤振方面,没有涉及更为常见的上游尾流激励的叶片振动问题。本文提出基于Volterra级数的尾流激励叶片气动力降阶模型,为尾流激励下叶片振动和动静叶干涉振动研究提供了新的思路。采用行波法简化尾流的参数个数,用阶跃信号法识别降阶模型的核函数。二维叶片的算例结果表明,本文方法可以较准确地描述尾流激励引起的叶片气动力振荡,而且计算效率极高。     

Passive aeroelastic control of a suspension bridge during erection

This study presents a system based on passively controlled leading- and trailing-edge flaps that is designed to suppress wind-induced instabilities such as flutter and torsional divergence. The utility of the approach is demonstrated on a three-dimensional bridge model. Particular emphasis is placed on the early stages of the deck erection process when the bridge is particularly vulnerable to flutter. The flaps are activated by the deck's movements though passive phase-compensating mechanisms comprising of springs, dampers and inerters. It is demonstrated that optimised compensator parameters, and optimum hinge locations, result in a substantially improved deck aerodynamic performance. Particular importance is given to ensuring that the controlled system has good closed-loop ‘robustness’ properties, or in other words, that the controlled system has a high tolerance to parameter variations and uncertainties in the system dynamics. The practical use of a nonlinear optimisation algorithm with a FE bridge aeroelastic model, which includes the flap dynamics, necessitates the use of reduced-order models. A novel model reduction procedure that is based on the retention of dominant poles is introduced into the aeroelastic modelling framework. Multimodal interactions are observed at the various erection stages and conclusions are drawn with regard to the contributions of various modes of vibration to aeroelastic instabilities. The main advantage of this approach lies on the passive system's simplicity and its ability to simultaneously increase the flutter and torsional divergence boundaries. The Humber Bridge in the U.K. is chosen as a study example for numerical simulations.     

A numerical investigation into the aerodynamic characteristics and aeroelastic stability of a footbridge

The results of a numerical investigation into the aerodynamic characteristics and aeroelastic stability of a proposed footbridge across a highway in the north of England are presented. The longer than usual span, along with the unusual nature of the pedestrian barriers, indicated that the deck configuration was likely to be beyond the reliable limits of the British design code BD 49/01. The calculations were performed using the discrete vortex method, DIVEX, developed at the Universities of Glasgow and Strathclyde. DIVEX has been successfully validated on a wide range of problems, including the aeroelastic response of bridge deck sections. In particular, the investigation focussed on the effects of non-standard pedestrian barriers on the structural integrity of the bridge. The proposed deck configuration incorporated a barrier comprised of angled flat plates, and the bridge was found to be unstable at low wind speeds, with the plates having a strong turning effect on the flow at the leading edge of the deck. These effects are highlighted in both a static and dynamic analysis of the bridge deck, along with modifications to the design that aim to improve the aeroelastic stability of the deck. Proper orthogonal decomposition (POD) was also used to investigate the unsteady pressure field on the upper surface of the static bridge deck. The results of the flutter investigation and the POD analysis highlight the strong influence of the pedestrian barriers on the overall aerodynamic characteristics and aeroelastic stability of the bridge.     

大跨度桥梁多模态耦合颤振DTMD控制研究

DTMD是一种具有双频率的调谐质量阻尼器,与普通TMD相比,可以同时实现对主梁竖向和扭转运动的控制,具有较高的控制效率。本文基于多模态耦合颠振理论,导出带有DTMD的桥梁颠振系统运动微分方程,采用PK—F法求解系统颠振运动微分方程,并编制了多模态耦合颠振DTMD控制和参效分析程序,以崖门斜拉桥为算例,分析了DTMD对桥梁颤振控制的有效性并与普通TMD进行了对比,计算结果表明与传统TMD相比,DTMD对桥梁颠振具有更高的控制效率。     

Linear and Nonlinear Aerodynamic Theory of Interaction between Flexible Long Structure and Wind

ＩｎｔｒｏｄｕｃｔｉｏｎＡｌｏｎｇｗｉｔｈｔｈｅｉｎｃｒｅａｓｅｏｆｔｈｅｆｌｅｘｉｂｉｌｉｔｙｏｆｓｌｅｎｄｅｒｓｔｒｕｃｔｕｒｅｓｅｔｉｎｔｈｅｗｉｎｄｆｉｅｌｄ ,ｓｕｃｈａｓｔｈｅｌｏｎｇ＿ｓｐａｎｂｒｉｄｇｅａｎｄｈｉｇｈ＿ｒｉｓｅｂｕｉｌｄｉｎｇ ,ｔｈｅａｃｔｉｏｎｓｏｆｕｎｓｔｅａｄｙａｅｒｏｄｙｎａｍｉｃｆｏｒｃｅｓｗｉｌｌａｃ ｃｅｌｅｒａｔｅ,ａｎｄｈｏｗｔｏｓｏｌｖｅｔｈｅａｅｒｏｅｌａｓｔｉｃｐｒｏｂｌｅｍｓｉｓｇｅｔｔｉｎｇｍｏｒｅｉｍｐｏｒｔａｎｔ.Ｔｈｅａｅｒｏｅｌａｓ…     

An accurate singularity-free geometrically exact beam formulation using Euler parameters

Wind-induced nonlinear oscillations of twin-box girder bridges are very sensitive to the aerodynamic shape of the deck (i.e., slot width ratio (SWR) and wind fairing shape) due to the complicated flow characteristics around the bridge deck. This paper presents a fully integrated finite element (FE) model in time domain, involving a nonlinear aerodynamic force model and a bridge FE model, to allow the investigation of nonlinear oscillation behaviors of long-span twin-box girder bridges with various SWRs and wind fairing shapes. The parameters in integrated FE model were firstly identified by using CFD simulation, and then, the proposed model was validated by conducting wind tunnel testing using sectional models and full-bridge aeroelastic models. It demonstrates that the developed integrated model has the capability of simulating the nonlinear flutter behaviors of twin-box girder bridges with various aerodynamic shapes. Furthermore, the prediction results show that the wind fairing shape has significant impact on the degree of freedom participation in coupled oscillation and failure modes, as well as flutter performance of the bridges. In addition, there is an increase in amplitudes of the limit cycle oscillations with the increase in the SWR of the twin-box girder bridges, and the relationships between the bending-torsional coupled oscillation, failure modes, and SWR of the bridges with anti-symmetric wind fairings are opposite to those with symmetric wind fairings.     

Aeroelastic analysis of swept pre-twisted wings

In this paper, aeroelastic modeling of aircraft wings with variations in sweep angle, taper ratio, and variable pre-twist angle along the span is considered. The wing structure is modeled as a classical beam with torsion and bending flexibility. The governing equations are derived based on Hamilton’s principle. Moreover, Peters’ finite state aerodynamic model which is modified to take into account the effects of the wing finite-span, the wing sweep angle, and the wing pre-twist angle, is used to simulate the aerodynamic loads on the wing. The coupled partially differential equations are discretized to a set of ordinary differential equations using Galerkin’s approach. By solving these equations the aeroelastic instability conditions are derived. The results are compared with some experimental and analytical results of previous published papers and good agreement is attained. Effects of the wing sweep angle, taper ratio, bending to torsional rigidity, and pre-twist angle on the flutter boundary in several cases are studied. Results show that these geometrical and physical parameters have considerable effects on the wing flutter boundary.     

基于主动控制策略的机翼颤振特性模拟

航空航天飞行器舵翼类结构的气动颤振是一种灾难性的动力学行为.在基于偶极子理论的气动弹性动力学模型中,气动载荷可表达为基于结构动力学响应的一种状态反馈的闭环控制力,控制律取决于翼型的几何参数、材料参数、结构动力学特性以及来流速度等多种条件,通常需通过实际飞行或风洞实验进行辨识与检验.在实验室条件下,以系统动力学响应的模态特征等效为前提,提出了一种基于人工主动控制的方式进行气动载荷下舵翼类结构自激颤振的特征值跟踪策略.建立并讨论了等效系统的非自伴随动力学微分方程及其特征方程的求解过程,并与通用软件的计算结果进行了对比,二者具有较好的一致性.通过优化搜索分别获得了位移和速度的最优反馈点、最优作动点位置及最优反馈增益系数,经对比计算拟合得到风速-位移增益曲线和风速-速度增益曲线,从而实现了由单点反馈、单点作动的集中力的闭环控制等效系统的真实气动力分布控制.仿真算例表明,由此预示的实验过程无需辨识和重构非定常气动力的时域波形,无需其他干预即可实现地面模拟实验,主动控制的效果满足预期,初步实现了自激颤振的特征值跟踪,为进一步推动主动控制模拟实验及颤振参数辨识提供了基础.      

Effects of vertical central stabilizers on nonlinear wind-induced stabilization of a closed-box girder suspension bridge with various aspect ratios

The aerodynamic shape of a closed-box girder plays an important role in the wind-induced stabilization of long-span suspension bridges. The purpose of this study is to investigate the effects of the combination of five aspect ratios and a downward vertical central stabilizer (DVCS) on nonlinear flutter and aerostatic behaviors of a super long-span suspension bridge with closed-box girders. Through conducting a series of wind-tunnel tests and nonlinear finite element analysis, the results show that the nonlinear self-excited forces and the critical wind speed (U_cr) gradually increase as the increase of the aspect ratio (i.e. the width to depth ratios). Furthermore, the application of 20% deck depth DVCS could significantly increase the nonlinear self-excited forces and U_cr for small aspect ratios of 7.9 and 7.1. Particularly, the installation of the DVCS could change the flutter divergence patterns of the bridge from soft flutter to hard flutter, especially for a relatively small aspect ratio. In addition, the aerostatic force coefficients and torsional divergence critical wind speeds of the larger aspect ratio with DVCS are significantly larger than that without DVCS. A relatively small aspect ratio of the bridge has better aerostatic performance than that with a larger aspect ratio.