某飞机机翼颤振模型模态测试及分析

以某飞机机翼颤振缩比模型为研究对象,通过纯模态测试得到试验件前九阶模态参数。建立机翼梁架有限元模型并进行计算,得到各阶模态振型及频率。将各阶模态的计算结果与试验结果进行对比,频率的计算结果与纯模态试验值的误差均在5%以内,主要模态的振型计算结果与试验结果也基本一致,验证了有限元计算模型的准确性。在此基础上可以进行下一步的颤振分析,且试验结果可以作为机翼颤振模型风洞试验的参考依据。     

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。     

航空发动机模拟机匣动力学模型修正研究

针对有限元建模中由于各种误差(如建模误差等)会给计算结果精度带来影响的问题,提出了一种利用模型修正来提高有限元计算结果精度的方法。首次使用了一阶优化方法,以所测试的模态频率和振型为参考,对有限元模型进行修正。首先,以某航空发动机模拟机匣为研究对象,对其进行模态测试,得到其模态频率和振型。然后,以机匣的前10阶计算模态频率与测试模态频率之间误差最小为优化目标,使用Nastran软件对各部件有限元模型中单元的弹性模量进行了修正,并计算了模型修正前后的机匣模态频率和振型,同时与测试模态频率和振型进行对比。结果表明,修正后的有限元模型计算结果与测试结果吻合良好,二者模态振型一致,模态频率的最大误差不超过1%。由此说明修正弹性模量的模型修正方法合理、可行,适用于工程上大型复杂结构的有限元准确建模。     

超声速飞行器壁板非线性颤振响应分析的时域法与频域法对比研究

为考查基于假设模态法在时域中开展壁板非线性颤振分析的可行性,在相同的参数下,分别采用时域方法和频域方法研究了超声速飞行器壁板的非线性颤振响应,并从壁板的颤振幅值、颤振频率和颤振型态三个方面对时域和频域分析结果的一致性作了较详细的比较。首先,基于von Karman应变－位移关系和Mindlin板理论建立考虑几何非线性的壁板力学模型,应用一阶活塞理论分析壁板上单面承受的超声速准定常气动力,基于虚功原理和有限单元法推导壁板的运动微分方程。然后,用壁板的线性固有模态作为假设模态,减缩系统的自由度而得到降阶模型。采用四阶龙格-库塔法对降阶模型作时域数值积分,得到壁板的非线性颤振响应。另一方面,假设壁板的极限环颤振为简谐振荡,可对壁板的非线性刚度作等效线性化处理,进而在频域中直接在有限元（未降阶）模型的基础上分析壁板的颤振幅值、颤振频率和颤振型态。数值分析表明,当极限环颤振为简谐振荡时,时域方法和频域方法的计算结果符合一致。本文最后讨论了时域法和频域法应用在壁板非线性颤振分析中各自的优点和局限性。     

基于CFD/CSD耦合含间隙三维全动舵面气动弹性研究

发展了一种考虑间隙非线性的三维计算流体力学/计算结构力学(CFD/CSD)耦合气动弹性算法。结构分析采用虚拟质量法,即把含间隙的非线性系统划分为三个线性子系统,采用虚拟质量模态作为统一的坐标架去表示各线性子系统。结果表明,虚拟质量法计算的线性子系统模态和动力学响应均与有限元直接计算结果一致。结构运动方程积分采用自适应时间步长法,即当线性子系统发生切换时,通过时间步长的自适应使得切换点可以准确捕捉。切换点和自适应时间步长的搜索采用二分法,计算表明二分法能有效地捕捉切换点并保证了数值稳定性。在此基础上与非定常CFD技术结合,在跨音速条件下对三维全动舵面开展气动弹性响应研究。计算表明结构在低于和高于线性颤振速度下均会形成极限环振荡。由于间隙非线性的影响,跨音速极限环的临界速度比线性颤振的跨音速凹坑下降了20%。     

波导结构频散分析的特征频率法及在板条结构中的应用

提出一种求解波导结构频散特性的有限元特征频率法,该方法基于振动问题的特征频率计算理论,根据模态振型识别波数与模态类型,建立了相速度及群速度的求解方法。该方法可适用于任意波导结构的频散关系求解。首先分析满足收敛精度要求的最大网格单元尺寸与最小模型长度,并用该方法对简支板条结构的频散特性进行了计算。结果表明,有限元特征频率法适合求解波动频散关系,板条结构中模态受边界影响会产生同阶高次模态,边界尺寸决定新模态的截止频率;随频率的增大,同阶低次反对称模态会趋于一致;对称模态能量分布受边界影响较大。本文也为板条类结构导波实验结果的分析提供了理论依据。     

基于聚合多重网格方法的跨音速颤振的数值模拟

采用流固耦合方法对跨音速颤振进行了数值模拟。流体方面在非结构网格上用有限体积方法求解了Euler方程;结构方面则求解了后掠机翼典型剖面的结构模态方程。时间推进采用双时间步长：对每一真实时间步,都通过基于聚合多重网格方法的伪时间步推进,对流体和结构方程交替迭代．得到一个稳态的流固耦合的解。文章最后给出了NACA64A010翼型剖面的跨音速颤振边界．与相关文献的计算结果符合良好。     

高速小展弦比机翼颤振的微分求积法分析

引入微分求积法,分析高速小展弦比机翼的气动弹性问题。将小展弦比机翼等效为悬臂板,基于一阶活塞气动力理论建立机翼颤振偏微分方程,采用微分求积法将偏微分方程转化为常微分方程,根据频率重合理论对颤振问题进行求解。分析了机翼的固有频率及颤振速度,并与有限元软件计算结果进行比较,误差在2％以内,很好的验证了微分求积法求解小展弦比机翼颤振问题的有效性。分析了机翼面积、展弦比及厚度对颤振速度的影响,结果表明,小展弦比机翼的颤振速度受结构尺寸的影响较大,颤振速度随面积和展弦比的增大而减小,随机翼厚度的增大而增大。     

随机激励下受热翼面的模态频率特性试验研究

现代高速飞行器结构热模态频率特性试验研究,对这类飞行器设计校核和飞行安全具有重要意义。根据飞行过程中遭受的气动加热特性设计了瞬态热环境模拟系统,同时,根据高温环境的特点对测试中的激励和测量方式进行了重新设计,成功地将普通激振器应用于高温结构模态试验,最终将热环境模拟系统与振动测试系统组合,形成一套考虑瞬态热影响的热模态试验系统,实现了瞬态热环境下结构模态的地面测试。对一个切尖三角翼测量了各个加热区的温度随加热时间的变化,验证了加热温度控制的精确性;在纯随机激励下对测得的激励和振动响应信号采用短时傅里叶变换(Short Time Fourier Transformation,STFT)进行时变模态参数辨识,获得了前四阶模态频率随加热时间的变化,并与结构有限元数值计算结果进行了比较,试验与计算结果吻合得很好,验证了该试验方法对热模态测试问题的有效性和准确性。通过分别对瞬态和稳态热环境下结构模态频率试验和计算结果的分析,探讨了结构瞬态温度场对模态频率影响的机理,揭示了结构内部存在的热应力和材料属性的变化,是决定模态频率随加热时间变化趋势的内在原因。     

分布振子复合板的模态阻尼及多点激励下阻尼减振相关性

分布阻尼振子可拓宽结构减振频带,因此可将振子分布于板中以形成复合板（简称“分布振子复合板”）,进而实现较宽的减振频带．对于多点支撑处受到宽频非一致激励（例如在不同激励点处的激励频率、幅值与相位有差异）的分布振子复合板,目前还缺乏有效简便的优化控制指标．在作者之前的研究中,针对含分布振子的梁推导了基于模态应变能的模态阻尼计算理论,讨论了模态阻尼与单点激励下梁的减振效果的相关性,并应用于宽频减振设计优化．本文进一步将模态阻尼计算理论推广到分布振子复合板,并将研究从梁的单点激励扩展到板的多点非一致激励下的阻尼减振相关性．首先,在利用模态应变能法推导得到分布振子复合板的模态阻尼计算公式后,从理论上讨论了不同边界条件与模态阶次对计算结果的影响,以及计算理论的适用性．而后,进一步通过有限元参数分析了边界条件、频率比、模态阶次与质量比的影响．最后,通过算例分析了无振子板或分布振子复合板在四个激励点具有多种幅值与相位组合情况下的稳态响应．结果表明,推导的模态阻尼计算公式可正确预测不同边界条件下的模态阻尼,且理论预测的模态阻尼与基板的稳态平均加速度减小率、稳态峰值应变能减小率均有较高的相关性．     

基于DEM的推土机铲刀曲面参数化设计分析

为合理地选择推土机铲刀曲面参数,本文利用基于离散单元法(DEM)的EDEM软件模拟铲运过程．模拟中选用三种形状的石块混合物料作为被铲运介质,对三种曲率半径的圆弧面铲刀和两种形式的直线-圆弧复合式铲刀在水平铲运工作时所受的工作阻力进行了对比分析,发现不同曲面参数的铲刀在水平铲运时的工作阻力主要来自于水平前进方向,圆弧面铲刀的水平阻力随曲率半径的减小而增大,而竖直向阻力会随着曲率半径增大而由向上逐渐转变为向下;直线在上-圆弧在下复合式铲刀所受的水平阻力始终大于直线在下-圆弧在上复合式铲刀所受的水平阻力,铲刀曲面几乎不受侧向力．     

Modeling soil-bulldozer blade interaction using the discrete element method (DEM)

Limited studies have been conducted to establish scaling relationships of soil reaction forces and length scales of bulldozer blades using the Discrete Element Method (DEM) technique. With a DEM-based similitude scaling law, performance of industry-scale blades can be predicted at reduced simulation efforts provided a calibrated and validated DEM soil model is developed. DEM material properties were developed to match soil cone penetration testing. The objectives of the study were to develop a DEM soil model for Norfolk sandy loam soil, establish a scaled relationship of soil reaction forces to bulldozer blade length scales (n = 0.24, n = 0.14, n = 0.10, and n = 0.05), and validate the DEM-predicted soil reaction forces on the scaled bulldozer blades to the Norfolk sandy loam soil bin data. Using 3D-scanned and reconstructed DEM soil aggregate shapes, Design of Experiment (DOE) of soil cone penetration testing was used to develop a soil model and a soil-bulldozer blade simulation. A power fit best approximated the relationship between the DEM-predicted soil horizontal forces and the bulldozer blade length scale (n) (R² = 0.9976). DEM prediction of soil horizontal forces on the bulldozer blades explained the Norfolk sandy loam soil data with a linear regression fit (R² = 0.9965 and slope = 0.9634).     

Effects of non-smooth characteristics on bionic bulldozer blades in resistance reduction against soil

The phenomenon of soil adhesion occurs widely when terrain machines and construction machines work; this adhesion increases their working resistance. Bionics is one of the most effective methods to reduce resistance against soil. Several non-smooth convex form bulldozer blades were tested to study the effects of non-smooth characteristics on resistance reduction against soil. Under the same soil and test conditions, the draft forces of different non-smooth samples were obtained, and were lower than those of smooth samples. The sample with largest convex base diameter had the lowest draft force. The experiments with smooth and non-smooth samples were repeated to observe soil adhesion and test resistance. A minimum amount of soil adhered to the surface of the non-smooth sample, and the draft force varied smoothly. The smooth sample was different in soil adhesion and draft force.     

3-D DEM simulation of cohesive soil-pushing behavior by bulldozer blade

A numerical simulation based on discrete element method (DEM) was conducted on the excavation and pushing processes of soil by a bulldozer blade. Soil contains water and the resistance acting on the bulldozer blade is largely influenced by the cohesive force due to liquid bridges formed among soil particles. In the present study, a cohesive bond force model proposed by Utili and Nova [5] was introduced in which the microscopic behavior of cohesive force was modeled analogously with macroscopic shear failure characteristics. The dependency on the magnitude of microscopic cohesive force was verified. The behavior of particles changed greatly by taking into account the cohesive bond force. The characteristic behavior of excavated soil aggregates, such as rolling motion and intermittent collapsing, were observed in front of the blade surface.     

轴流泵参数化设计及应力与模态特征分析

以船用轴流式喷水推进泵为对象,探索了轴流泵参数化设计、水动力性能、静强度和结构声学特征分析的数值途径。轴流泵叶轮采用升力法设计,导叶采用流线法设计,叶片三维造型在NUMECA参数化设计平台中完成。轴流泵水动力性能校核由粘性CFD计算完成,CFD计算同时提取得到叶片分布式水动力载荷。叶片静强度校核由ANSYS有限元计算叶片应力和应变特征完成,应力分析时同时考虑水动力载荷、重力载荷和离心力载荷。叶片结构声学特征分析由NASTRAN有限元计算叶片模态振型和振型频率完成。计算结果表明,轴流泵扬程和功率满足设计指标,效率达87.13%;叶轮叶片形变相对于叶顶间隙来说为极小量,可忽略不计,叶片存在局部应力集中现象,最大应力小于许用应力,满足静强度要求;叶片前四阶振型特征与分析经验一致,且振型频率远离轴频、叶频及其谐频特征频率,能够避免共振产生。     

Study of direct force measurement and characteristics on blades of Savonius rotor at static state

Experiments were conducted to measure and to clarify quantitative variations of fluid force on three kinds of setting blade configuration on a Savonius rotor at the static state in the steady uniform flow. In the experiments, by splitting both the end-disks of the blades into two half parts, the two blades were independent on each other and the one blade attached to both the half end-disks was only connected to the axis rod of the rotor, and the other blade connecting to the other half end-disks was free from the axis rod. Hence, the drag and lift forces acting on the former blade were directly measured in a short time at every phase angle and every overlap ratio of the two blades using the force balance meter. The experiment for the rotor of the diameter 160 mm and the height 160 mm was conducted in the steady wind flow of the Reynolds number, about 0.64 × 10⁵ which based on the rotor diameter and the upstream velocity. From the experiment, value of the drag coefficient of the one blade in two blades with the overlap ratio of zero was taken from about −0.3 to 1.6, and the lift coefficient of it from about −1.0 to 1.4 in a cycle. The minus value of drag only appears in the setting of one blade in two blades, however the minus value does not exist in the distribution of tangential force on every overlap. And it was shown that the force distributions on the one blade in a cycle were very different in the first and second half cycle and interfered by the other blade, and strongly dependent on the overlap ratio between the blades.     

Numerical Simulation of the 3D Laminar Viscous Flow on a Horizontal-axis Wind Turbine Blade

The aim of this paper is to describe the methodology followed in order to determine the viscous effects of a uniform wind on the blades of small horizontal-axis wind turbines that rotate at a constant angular speed. The numerical calculation of the development of the three-dimensional boundary layer on the surface of the blades is carried out under laminar conditions and considering flow rotation, airfoil curvature and blade twist effects. The adopted geometry for the twisted blades is given by cambered thin blade sections conformed by circular are airfoils with constant chords. The blade is working under stationary conditions at a given tip speed ratio, so that an extensive laminar boundary layer without flow separation is expected. The boundary layer growth is determined on a non-orthogonal curvilinear coordinate system related to the geometry of the blade surface. Since the thickness of the boundary layer grows from the leading edge of the blade and also from the tip to the blade root, a domain transformation is proposed in order to solve the discretized equations in a regular computational 3D domain. The non-linear system of partial differential coupled equations that governs the boundary layer development is numerically solved applying a finite difference technique using the Krause zig-zag scheme. The resulting coupled equations of motion are linearized, leading to a tridiagonal system of equations that is iteratively solved for the velocity components inside the viscous layer applying the Thomas algorithm, procedure that allows the subsequent numerical determination of the shear stress distribution on the blade surface.     

Supercritical and subcritical dynamic flow-induced instabilities of a small-scale wind turbine blade placed in uniform flow

There is a growing interest in extracting more power per turbine by increasing the rotor size in offshore wind turbines. As a result, the turbine blades will become longer and therefore more flexible, and a flexible blade is susceptible to flow-induced instabilities. In order to design and build stable large wind turbine blades, the onset of possible flow-induced instabilities should be considered in the design process. Currently, there is a lack of experimental work on flow-induced instabilities of wind turbine blades. In the present study, a series of experiments were conducted and flow-induced instabilities were observed in wind turbine blades. A small-scale flexible blade based on the NREL 5 MW reference wind turbine blade was built using three-dimensional printing technique. The blade was placed in the test section of a wind tunnel and was subjected to uniform oncoming flow, representing the case of a parked wind turbine blade. The blade׳s tip displacement was measured using a non-contacting displacement measurement device as the oncoming wind speed was increased. At a critical wind speed, the blade became unstable and experienced limit cycle oscillations. The amplitude of these oscillations increased with increasing wind speed. Both supercritical and subcritical dynamic instabilities were observed. The instabilities were observed at different angles of attack and for blades both with and without a geometric twist. It was found that the blade twist had a significant influence on the observed instability: a blade without a twist experienced a strong subcritical instability.     

碳纤维复合材料冲击模型率相关修正方法与试验研究

目前先进航空发动机的风扇叶片均采用复合材料结构,为了研究其在工作过程中可能受到的冲击损伤,即碳纤维增强树脂基复合材料受到高速冲击后的损伤与破坏过程,对其准静态下的正交各向异性本构模型和失效准则进行修正,建立了应变率相关的三维动态本构及损伤模型．该模型考虑了材料模量、强度和断裂韧性与应变率的相关性,并采用基于断裂韧性的渐进损伤模式对刚度进行折减来控制破坏过程．开展了不同应变率下的动态试验,得到基体方向拉伸与剪切的动态响应数据,拟合得到相应的动态修正因子．将该模型结合修正因子植入数值软件进行仿真计算,分析结果表明,所建立的率相关本构及损伤模型能够更准确地模拟层合板受冲击过程的损伤和破坏,与试验吻合较好．     

Bulldozer blade control

A simple control system for controlling a bulldozing blade was developed and tested. Both controls of the bulldozing load acting on the bulldozer blade and the blade position control were validated through an operational test. It was observed that the application of this control system could not only reduce the frequent up and down actions of adjusting the bulldozer blade considering the conditions of the load applied and the irregularity of terrain surface, but also could allow the operator to concentrate on the steering during the operation of earth moving.