桥梁颤振气动导数在均匀流与紊流作用下的统一辨识理论研究

桥梁断面颤振气动导数的准确识别是桥梁空气动力稳定性研究的基础,一直是桥梁风工程研究领域的前沿课题。基于工况模态分析理论,本文首先导出了紊流条件下桥梁颤振气动导数辨识的完整方法;其次,将上述数据处理方式运用到由均匀流条件引起的自由衰减振动中,得出与紊流情况类似的结果。本文提出的方法能够用同样的辨识原理、同一个数据处理程序统一地对紊流和均匀流下的桥梁气动导数进行辨识;最后,利用数值仿真算例验证上述理论。     

主动格栅紊流场对典型主梁颤振导数影响的研究

为研究紊流积分尺度对桥梁颤振导数的影响,选取了理想平板、流线型箱梁以及高宽比1∶6矩形断面三种气动外形渐变的典型断面,采用主动格栅模拟了二维大积分尺度紊流场,利用强迫振动装置测试了主动格栅紊流场中三种断面节段模型的颤振导数,并与均匀流场试验值进行了对比。试验结果表明,紊流积分尺度对颤振导数的影响随断面钝化逐渐减弱;主动格栅二维紊流对流线型断面颤振导数影响较小,无明显趋势性变化;对钝体矩形断面影响显著,并且随折减风速增加而加剧,其气动阻尼项导数由正向负衰减显著,有利于改善结构颤振性能。     

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.     

线振动硅微机械陀螺结构误差参数分离和辨识

推导了线振动微机械陀螺的三自由度误差力学方程,并详细分析了陀螺耦合误差的产生机理。分析结果表明,各种结构误差是导致陀螺耦合误差信号的主要原因。在此基础上,利用振动和模态理论给出了陀螺结构误差参数的分离和辨识的试验方法和结果。试验结果表明,同相耦合分量和正交耦合分量是微机械陀螺的两种主要误差信号,造成正交耦合的主要原因是驱动轴和检测轴之间的刚度耦合以及驱动轴和检测轴各自的刚度不对称,造成同相耦合的主要原因是驱动轴和检测轴之间的阻尼耦合以及检测轴刚度不对称和驱动力不对称。结构误差参数的分离和辨识试验方法将为下一步的陀螺结构优化、微加工工艺改进以及耦合误差抑制提供基础。     

机抖激光陀螺敏感轴动态偏移误差参数估计与补偿

针对振动环境下机抖激光陀螺敏感轴产生动态偏移造成惯导系统精度下降的问题,从理论上推导了机抖激光陀螺敏感轴动态偏移误差模型,并结合工程实际建立了简化的误差模型;在此简化误差模型基础上,推导了陀螺敏感轴动态偏移造成的等效陀螺漂移与比力、角速度的耦合关系;将机抖激光陀螺敏感轴动态偏移误差归结为9个待辨识参数,针对该模型中的待辨识参数设计了标定方法,并给出了标定实验设计原则;以姿态误差为观测量进行振动实验对待辨识参数进行估计,振动实验结果表明,在10 min线振动时间内,机抖激光陀螺敏感轴动态偏移误差补偿后,捷联惯导系统纯惯导速度误差减小30%以上。     

不同交通流状态下桥梁气动导数的风洞试验研究

为了考虑实际运营车辆对桥梁气动导数的影响,根据车辆密度模拟了三种交通流状态,基于强迫振动装置,分别对每个交通流和无车状态下的桥梁气动导数进行风洞试验研究,讨论了不同攻角下不同车流的车辆对桥梁气动导数的影响,探究了车辆对气动导数影响的百分比以及气动导数变化量的变化规律。研究结果表明:不同攻角下不同车流的车辆均对直接导数A*2、H*4和交叉导数A*4、H*2影响显著,A*2、A*3变化量随着折减风速有一定的变化规律。虽然不同攻角下不同车流的车辆对气动导数的影响程度及影响规律不同,并且车流的繁忙程度对大多数气动导数的影响规律不明显,但是车辆对桥梁气动导数的影响不容忽略。     

考虑悬架非线性的变截面连续梁桥车桥耦合振动分析

以三跨变截面连续梁桥为研究对象,将其看作Euler-Bernoulli梁并划分为有限个微段推导出桥梁振动方程,再建立考虑悬架非线性的1/4车辆振动方程,得到车桥耦合振动方程并化简,借助Runge-Kutta法求解获得桥梁任意位置的振动响应.结果表明:考虑悬架非线性后,车辆行驶于桥梁前段时跨中竖向位移与忽略悬架非线性时不...     

具有组合非线性阻尼的非线性能量阱振动抑制响应分析

非线性能量阱是一种振动能量吸收装置,其在结构振动抑制中具有十分重要的作用.文章对具有组合非线性阻尼非线性能量阱的系统进行振动抑制相关的分析.首先对具有组合非线性阻尼非线性能量阱的系统进行理论模型的描述,对系统模型的运动方程利用复变量平均法进行推导,得到系统的慢变方程.其次对系统的慢变方程运用多尺度法进行强调制响应的分析,通过对系统进行慢不变流形和相轨迹的研究,描述系统强调制响应发生的条件基础.此外,还利用一维映射对系统进行分析,揭示外激励幅值对强调制响应存在时频率失谐系数取值区间的影响规律.最后利用能量谱、时间响应和庞加莱映射对耦合组合非线性阻尼非线性能量阱系统进行了振动抑制的相关研究,揭示组合非线性阻尼的非线性能量阱不同阻尼比、阻尼和刚度对其振动抑制效果的影响规律,得出组合非线性阻尼非线性能量阱和主结构响应存在一致性的现象,并验证所提出的组合非线性阻尼非线性能量阱模型具有较好的振动抑制能力.     

基于移动载荷响应的多跨连续桥梁损伤检测

应用有限元法将连续桥梁结构离散为两跨弱耦合欧拉-伯努利梁模型,研究了该弱耦合梁系统由于局部损伤而引起的振动模态局部化现象.利用Newmark直接积分法求出在移动车载作用下桥梁的动态响应,并进一步推导出动态响应桥梁对物理参数(如杨氏模量)的时域灵敏度.在反问题中利用基于响应灵敏度的有限元模型修正法识别出桥梁的局部损伤,并讨论了人工测量噪声对损伤识别结果的影响.算例表明该方法能够快速有效地检测具有相重频率的弱耦合系统的局部损伤,并具有精度高、对测量噪声不敏感等特点.     

含裂纹梁非线性静动力特性及简化动力学建模Static and dynamic behaviour of cracked beam and simplified dynamic model

主要研究裂纹对梁结构动力特性的影响规律,进而为含裂纹梁结构状态监测提供理论依据。首先,对裂纹影响区域进行分析,建立含裂纹梁二维接触非线性有限元模型,阐明含裂纹梁具有拉压不同刚度的静力特性;其次,通过对机理模型的分析,指出拉压不同刚度会引起轴向与弯曲的耦合振动;然后,通过非线性动力学分析方法研究其动力特性,观察到含裂纹梁在冲击荷载下会产生轴向与弯曲的耦合振动现象,并指出这种轴向与弯曲耦合振动的一个重要特征是轴向振动频谱图中含有弯曲振动基频的两倍频成分;最后,通过引入非线性弹簧建立一种新颖的含裂纹梁简化动力学模型,通过与精细有限元分析对比,验证了模型的合理性。该简化动力学模型将接触非线性问题转换为材料非线性问题,避免了费时的接触非线性动力学求解过程。     

适用于几何非线性气动弹性分析的结构动力学降阶模型方法研究

几何非线性是壁板颤振和大展弦比机翼气动弹性等问题的一个主要特征,在进行数值仿真分析时往往需要采用商业非线性有限元求解器,存在计算量大和耦合迭代策略不易控制等问题。本文发展了一种适用于几何非线性的结构动力学降阶模型(CSD-ROM),利用广义坐标的非线性多项式表征非线性内力,采用参数识别方法获取多项式系数,并通过增加额外的线性模态来改善模型预测精度。基于此方法,分别针对壁板颤振、切尖三角翼的CFD/CSD-ROM非线性颤振问题开展了时域响应分析。计算结果表明,通过CSD-ROM计算出的壁板颤振速度为590 m/s,颤振频率为174 Hz,与有限元结果误差分别为0.8%和1.7%。马赫数0.879时切尖三角翼的颤振动压预测结果为2.25 psi,与非线性有限元相比的误差为3.8%。本文采用的非线性和线性模态基底组合方法,在保证计算精度的基础上可有效降低训练样本数量,一定程度上可替代非线性有限元开展气动弹性分析。     

采用分布式压电驱动器升力面的颤振主动抑制

对采用分布式压电驱动器升力面的颤振主动抑制进行了理论与试验研究.应用 LQG最优控制法设计了主动控制律,在控制律降阶时提出了平衡实现与LK法结合使用的新途径,在对不定常气动力进行有理函数拟合时对LS法进行了改进.试验中利用激光测速仪非接触测量模型的速度响应并在地面共振试验中用压电驱动器激振模型.颤振风洞试验结果表明,理论计算合理并与试验结果吻合良好.     

高超声速舵面颤振的数值模拟影响因素研究

针对某高超声速舵面颤振风洞试验模型开展了数值模拟研究,采用多种气动力模型和耦合迭代策略,研究对颤振预测结果的影响。计算结果表明,采用三阶活塞理论、统一升力面理论、Euler方程和N-S方程的颤振动压预测结果较接近,与试验值误差均在7%以内。采用时域方法计算时,松耦合方法的误差较大,超过15%。同时还发现,支撑机构会带来激波边界层干扰效应,一定程度上提高了颤振动压,考虑该因素的预测结果与试验值更接近。     

Parametric studies on relationships between flutter derivatives of slender bridge （Ⅰ）

Relationships between flutter derivatives of slender bridge are investigated based on our previously proposed semi-analytical flutter derivatives of flexible structure. The intrinsic relations are validated with test data of flutter derivatives of two bridges. Changes in flutter derivatives with the aerodynamic center, rotation speed, and angle variation are also studied by using a parametric method. The results show correctness of the proposed expressions of flutter derivatives given by authors in Ref. [1], and indicate that certain relations exist between these derivatives. It is also shown that semi-analytical flutter derivatives are applicable to bridges with a streamlined cross-section.     

翘翘板摆式MEMS加速度计振动整流误差

MEMS加速度计凭借其体积小、成本低、可靠性高及可批量生产等优势,已经在战术级精度的武器领域得到了广泛应用。但是,在振动环境下的输出误差(振动整流误差)成为其向导航级精度发展的主要指标瓶颈。为了减小MEMS加速度计的振动整流误差,对传感器芯片结构不对称性和电路零位误差引起的力矩器结构非线性进行了理论分析,然后按照振动法测非线性的方式对上述误差源引起的系统级误差模型进行了仿真试验验证,确定了各误差源与加速度计非线性系数间的影响关系。最后,对主要误差源(电路零位)优化前后的MEMS加速度计振动整流误差和非线性系数进行了测试对比,结果表明:优化后,在50~1500 Hz频率范围内MEMS加速度计二阶非线性的最大值可由1E-4g/g~2降至5E-6g/g~2。     

A nonlinear microbeam model based on strain gradient elasticity theory with surface energy

A microscale nonlinear Bernoulli–Euler beam model on the basis of strain gradient elasticity with surface energy is presented. The von Karman strain tensor is used to capture the effect of geometric nonlinearity. Governing equations of motion and boundary conditions are obtained using Hamilton’s principle. In particular, the developed beam model is applicable for the nonlinear vibration analysis of microbeams. By employing a global Galerkin procedure, the ordinary differential equation corresponding to the first mode of nonlinear vibration for a simply supported microbeam is obtained. Numerical investigations show that in a microbeam having a thickness comparable with its material length scale parameter, the strain gradient effect on increasing the beam natural frequency is higher than that of the geometric nonlinearity. By increasing the beam thickness, the strain gradient effect decreases or even diminishes. In this case, geometric nonlinearity plays the main role on increasing the natural frequency of vibration. In addition, it is shown that for beams with some specific thickness-to-length parameter ratios, both geometric nonlinearity and size effect have significant role on increasing the frequency of nonlinear vibration.     

A theoretical and experimental investigation of the effects of a steady angle of attack on the nonlinear flutter of a delta wing plate model

Limit cycle oscillations (LCO) of wings on certain modern high performance aircraft have been observed in flight and in wind tunnel experiments. Whether the physical mechanism that gives rise to this behavior is a fluid or structural nonlinearity or both is still uncertain. It has been shown that an aeroelastic theoretical model with only a structural nonlinearity can predict accurately the limit cycle behavior at low subsonic flow for a plate-like wing at zero angle of attack. Changes in the limit cycle and flutter behavior as the angle of attack is varied have also been observed in flight. It has been suggested that this sensitivity to angle of attack is due to a fluid nonlinearity. In this investigation, we study the flutter and limit cycle behavior of a wing in low subsonic flow at small steady angles of attack. Experimental results are compared to those predicted using an aeroelastic theoretical model with only a structural nonlinearity. Results from both experiment and theory show a change in flutter speed as the steady angle of attack is varied. Also the LCO magnitude increased at a given velocity as the angle of attack was increased for both the experiment and theory. While not proving that the observed sensitivity to angle of attack of LCO in aircraft is due to a structural nonlinearity, the results do show that a change in the aeroelastic behavior at angles of attack can be caused by a structural nonlinearity as well as a fluid nonlinearity. In this paper, only structural nonlinearities are considered, but an extension to include aerodynamic nonlinearities would be very worthwhile.     

翼型颤振压电俘能器的输出特性研究

压电俘能器能够为自然界中低功率的微机电系统持续供能. 为了模拟机翼的沉浮?俯仰二自由度运动和有效俘获气动弹性振动能量, 本文提出一种新颖的翼型颤振压电俘能器. 基于非定常气动力模型, 推导翼型颤振压电俘能器流?固?电耦合场的数学模型. 建立有限元模型, 模拟机翼的沉浮?俯仰二自由度运动, 获得机翼附近的涡旋脱落和流场特性. 搭建风洞实验系统, 制作压电俘能器样机. 利用实验验证理论和仿真模型的正确性, 仿真分析压电俘能器结构参数对其气动弹性振动响应和俘获性能的影响. 结果表明: 理论分析、仿真模拟和实验研究获得的输出电压具有较好的一致性, 验证建立数学和仿真模型的正确性. 仿真分析获得机翼附近的压力场变化云图, 表明交替的压力差驱动机翼发生二自由度沉浮?俯仰运动. 当风速超过颤振起始速度时, 压电俘能器发生颤振, 并表现为极限环振荡. 当偏心距为0.3和风速为16 m/s时, 可获得最大输出电压为17.88 V和输出功率为1.278 mW. 功率密度为7.99 mW/cm3, 相比较于其他压电俘能器, 能实现优越的俘获性能. 研究结果对设计更高效的翼型颤振压电俘能器提供重要的指导意义.      

Modal analysis of cantilever plate flutter

This study illustrates the mechanism of modal coupling in cantilever plate flutter using the full Theodorsen airfoil theory within the linear framework. An accurate, pseudo-spectral method is employed to calculate the fluid loading and the eigenvalue problem is solved numerically following the Galerkin procedure. For plates with a structure-to-fluid mass ratio around unity, the first two in vacuo modes are dominant and the Kutta condition at the trailing edge plays a central role in the flutter mechanism. The fluid loading induced by the first mode excites significant second and higher order modes. The fluid loading on the second mode is coupled strongly with the structural vibration velocity of the first mode, which is identified as the main mechanism of energy transfer from flow to plate. It is demonstrated that the response of the second mode is suppressed and the plate is stabilized when a concentrated mass is added near the middle of the plate length. Theoretical prediction is supported by experimental data although the latter is affected by many practical factors that are difficult to model precisely.     

两种湍流模型时域颤振计算方法研究

采用时域计算分析方法进行了机翼跨音速颤振特性研究。在结构运动网格的基础上,采用格点格式有限体积方法进行空间离散和双时间全隐式方法进行时间推进求解雷诺平均N-S方程。针对流动粘性分别应用了SST湍流模型和SSG雷诺应力模型,通过对跨音速标模算例AGARD445.6机翼的计算结果与实验值的对比分析,其中应用SST湍流模型得到的颤振速度与实验值最为接近,特别是在跨音速段平均相对误差在3%以内;并且计算结果整体上反映了跨音速颤振"凹坑"物理特性,验证了方法的有效性。