快速成型弹性风洞模型高速气动特性研究

利用光固化快速成型技术加工了内部金属骨架、外部光敏树脂外形的弹性轻质AGARD-B模型.采用气动与结构并发分析方法对其跨声速气动特性进行了初步研究,完成了风洞验证实验.研究结果表明:在马赫数0.6和1.2、较小攻角(α≤4°)的条件下,弹性轻质模型气动力特性与金属模型基本吻合;较大攻角(α>4°)条件下,因弹性轻质模型刚度比全金属模型小,试验过程中受气动载荷作用,特别是升力的影响,结构机翼变形较大,导致气动力特性与全金属模型差异较大,故气动力系数需要进行弹性变形修正.初步实验结果指出:在跨声速范围内,弹性轻质模型可直接用于气动布局选型设计与研究、基本状态等研究;但同时弹性轻质模型刚度不足,易变形.     

翼型跨声速气动特性的不确定性及全局灵敏度分析

针对马赫数和仰角的随机不确定性会导致气动性能波动的现象, 采用非嵌入式的混沌多项式方法对绕NACA0012 翼型跨声速随机气动特性进行不确定性及全局灵敏度分析. 具体分析了飞行状态的不确定性对气动载荷分布、流场及气动力系数的影响并通过全局灵敏度分析找出重要因素. 不确定性分析结果表明翼型上表面的激波以及激波后分离泡是造成气动性能剧烈波动的主要原因. 灵敏度分析结果表明在跨声速区域马赫数对激波处气动性能影响最大, 此外, 虽然马赫数和仰角相互耦合作用对气动力系数贡献比较小, 但对于激波位置处的流场, 这种互耦合作用不可忽略.      

基于POD和代理模型的静气动弹性分析方法

静气动弹性问题考虑弹性结构与定常气动力间的相互耦合作用,对飞行器的性能和安全具有显著的影响.在现代飞行器设计阶段,计算流体力学(CFD)/计算结构力学(CSD)直接耦合方法是精确考察静气动弹性影响的重要手段.然而,基于CFD技术的气动力仿真手段在耦合过程中计算量大且耗时长,难以满足设计阶段的需求.因此,为了兼顾计算精度与效率,文章采用本征正交分解(POD)和Kriging代理模型相结合的模型降阶方法,替代CFD求解过程并耦合有限元分析(FEA)方法,建立了高效、准确的静气动弹性分析框架.相较于传统的以模态法为主的静气动弹性分析方法,该方法能够解决更为复杂的静气动弹性问题以及提供静气动弹性变形过程中的气动分布载荷.针对典型三维跨声速HIRENASD机翼模型开展的马赫数、迎角变化的算例验证表明:由建立的静气动弹性分析方法与CFD/CSD直接耦合方法计算得到机翼翼梢处的静变形量间的相对误差在5%以内;同时该方法预测静平衡位置处的气动分布载荷的误差在5%以内,静气动弹性分析的计算效率至少提升了6倍.     

跨声速双曲型喷管流动

本文采用保角曲线坐标方法分析双曲型喷管喉部跨声速流动特性,给出了跨声速双曲型喷管流动的一般解.这个解适用于不同的喉部壁面曲率半径,适用于不同的比热比.通过计算给出了不同比热比下喉部跨声速流场的主要参数与曲率半径的关系以及典型跨声速流场的等马赫数线分布.本方法计算简单,精度较高,可作喷管设计,特别是气动激光喷管设计参考.     

高超声速飞行器气动防热新概念研究

传统乘波构型的高超声速飞行器尖锐的前缘存在严重的气动加热问题,而简单的前缘钝化气动防热方法由于造成很大的升阻比损失,难以发挥实质性作用. 引入``人工钝前缘(ABLE)'概念,拟以一种新的思路解决这一矛盾. 通过定义ABLE构型的外形参数,并采用CFD数值计算方法研究了各参数对气动力和气动热特性的影响规律,在流场分析的基础上进行了外形优化,最终得到令人满意的新型高超声速飞行器头部外形,总结了运用ABLE概念进行气动防热的相关设计原则和规律.      

滑动蒙皮变后掠气动力非定常滞回与线性建模

针对低速不可压条件下滑动蒙皮方式变后掠过程中非定常动态气动特性开展了3方面的研究工作: (1)飞行器变形过程中非定常动态气动特性风洞试验技术研究;(2)变形过程中滞回效应研究和机理分析; (3)基于风洞试验结果开展变形过程中非定常动态气动力线性建模. 初步研究表明: (1)采用强迫振荡法可以有效地获取变形过程中非定常动态气动力滞回效应; (2)造成变形过程中气动滞回效应的机理有两个即``动边界效应'和``流场结构滞回效应', 造成滞回效应的机理可能主要在于后者; (3)引入升力系数和俯仰力矩系数随后掠角变化率的动导数概念, 可以建立变形过程中非定常动态气动力线性模型.      

叶轮机械非定常流动研究进展

本文就叶片排进出口流场畸变型动力响应、压缩系统气动稳定性、叶轮机械非定常气动问题的数值模拟以及失速颤振轴流压气机系列转子实验等４个方面问题,从非定常气动力学角度作一概述和展望      

CFD结合降阶模型预测阵风响应

传统的阵风响应主要在频域内进行分析,气动载荷基于线性方法计算,不能考虑黏性和跨声速流动影响. 飞机设计需考虑不同频率和不同形状阵风的响应,基于CFD的阵风响应预测由于计算工况太多,工作量巨大. 本文发展了一种CFD结合非定常气动力ARMA(autoregressive-moving-averagemodel)降阶模型的阵风响应分析方法,CFD只要针对给定频率和形状的一种阵风响应进行计算,对获得的气动力时间历程运用线性最小二乘法参数辨识ARMA降阶模型的系数,则对任意频率和形状的阵风,代入降阶模型即可确定该阵风的响应,大大提高了计算效率. 为效验发展的方法,先计算NACA0012翼型在低马赫数0.11的阵风响应,通过对比CFD、ARMA降阶模型及早期发展的不可压阵风响应预测方法的结果,验证了方法的有效性. 再对比CFD、ARMA在跨声速马赫数0.8的阵风响应预测结果,证实所发展的方法对跨声速阵风响应预测亦是有效的.      

具有迟滞非线性的高超声速机翼颤振分析

本文采用两自由度的二元机翼模型,研究高超声速机翼由于气动弹性引起的机翼颤振问题.考虑了由于机翼连接部位的松弛和摩擦引起的机翼迟滞非线性特性的影响,采用三阶活塞理论给出高超声速机翼的非线性气动力和气动力矩.通过数值模拟,获得系统的时域响应曲线和Poincare图,分析发现,随着系统参数的变化,二元机翼会出现极限环、分岔等复杂的动力学行为,并发现迟滞非线性参数对系统极限环幅值、分岔和混沌特性有较大影响.     

转捩位置对全动舵面热气动弹性的影响

高超声速附面层的转捩预测一直是流体力学研究中的难点,转捩前后物面的摩擦系数和传热系数会发生改变,转捩位置的不同会影响到飞行器表面热环境,进而使得飞行器的气动弹性特性发生显著变化.鉴于高超声速附面层转捩预测的不确定性,本文分析了转捩位置对高超声速全动舵面热气动弹性的影响.首先分别用层流模型和湍流模型求解N-S方程,得到气动热环境,并对气动热进行参数化;然后在不同转捩位置情况下构造出不同转捩位置的热分布模型,基于此种温度分布,结合热应力和材料属性的影响分析结构的热模态,将结构模态插值到气动网格上,采用基于CFD的当地流活塞理论进行气动弹性分析.以M=6,H=15 km的某舵面为对象进行计算,结果表明:(1)随着转捩位置向后缘移动,结构频率上升,结构颤振速度呈增大趋势,转捩位置的变化能够带来颤振临界速度最大6%的变化量;(2)当转捩位置位于舵轴附近时,结构的颤振特性变化剧烈.通过刚度特性的分解和分析发现,导致颤振特性变化的主要因素在于舵轴的刚度特性变化,舵轴的影响量占整个结构刚度特性变化量的80%以上.     

Nonlinear dynamics of an aeroelastic airfoil with free-play in transonic flow

Nonlinear dynamic behaviors of an aeroelastic airfoil with free-play in transonic air flow are studied. The aeroelastic response is obtained by using time-marching approach with computational fluid dynamics (CFD) and reduced order model (ROM) techniques. Several standardized tests of transonic flutter are presented to validate numerical approaches. It is found that in time-marching approach with CFD technique, the time-step size has a significant effect on the calculated aeroelastic response, especially for cases considering both structural and aerodynamic nonlinearities. The nonlinear dynamic behavior for the present model in transonic air flow is greatly different from that in subsonic regime where only simple harmonic oscillations are observed. Major features of the responses in transonic air flow at different flow speeds can be summarized as follows. The aeroelastic responses with the amplitude near the free-play are dominated by single degree of freedom flutter mechanism, and snap-though phenomenon can be observed when the air speed is low. The bifurcation diagram can be captured by using ROM technique, and it is observed that the route to chaos for the present model is via period-doubling, which is essentially caused by the free-play nonlinearity. When the flow speed approaches the linear flutter speed, the aeroelastic system vibrates with large amplitude, which is dominated by the aerodynamic nonlinearity. Effects of boundary layer and airfoil profile on the nonlinear responses of the aeroelastic system are also discussed.     

跨音速极限环型颤振的高效数值分析方法

事先建立一个低阶的非线性、非定常气动力模型是开展非线性流场中气动弹性问题研究的一个捷径. 基于CFD方法, 通过计算结构在流场中自激振动的响应来获得系统的训练数据. 采用带输出反馈的循环RBF神经网络, 建立时域非线性气动力降阶模型.耦合结构运动方程和非线性气动力降阶模型, 采用杂交的线性多步方法计算结构在不同速度(动压)下的响应历程, 从而获得模型极限环随速度(动压)变化的特性. 两个典型的跨音速极限环型颤振算例表明, 基于气动力降阶模型方法的计算结果与直接CFD仿真结果吻合很好, 与后者相比其将计算效率提高了1~2个数量级.      

Unsteady aerodynamic reduced-order modeling of an aeroelastic wing using arbitrary mode shapes

Computational fluid dynamics (CFD) based unsteady aerodynamic reduced-order model (ROM) can offer significant improvements to the efficiency of transonic aeroelastic analysis. To construct a ROM based on mode shapes, one run of CFD solver is needed to compute aerodynamic responses corresponding to mode excitations. When mode shapes change with structure, another run of the CFD solver is required to construct the new ROM. The typically large computational cost associated with repeated runs of the CFD solver impedes the application of existing unsteady aerodynamic reduced-order modeling methods to transonic aeroelastic design optimization and aeroelastic uncertainty analysis. This paper demonstrates a method that can replace the CFD solver used in the process of existing unsteady aerodynamic reduced-order modeling. It can produce aerodynamic responses corresponding to mode excitations for arbitrary mode shapes within a few seconds. Computational cost can be reduced by two orders of magnitude using the mode excitations and the corresponding aerodynamic responses computed by the method to construct the ROMs used for flutter analyses in aeroelastic design optimization or aeroelastic uncertainty analysis in transonic regime compared with the existing unsteady aerodynamic reduced-order modeling methods. Results show that the method can accurately produce the aerodynamic responses corresponding to the mode excitations and predict the flutter characteristics of AGARD 445.6 wings root-attached in three different ways.     

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。     

Nonlinear aeroelastic stability analysis of wind turbine blade with bending–bending–twist coupling

In this study, the nonlinear aeroelastic stability of wind turbine blade with bending–bending–twist coupling has been investigated for composite thin-walled structure with pretwist angle. The aerodynamic model used here is the differential dynamic stall nonlinear ONERA model. The nonlinear aeroelastic equations are reduced to ordinary equations by Galerkin method, with the aerodynamic force decomposition by strip theory. The nonlinear resulting equations are solved by a time-marching approach, and are linearized by small perturbation about the equilibrium point. The nonlinear aeroelastic stability characteristics are investigated through eigenvalue analysis, nonlinear time domain response, and linearized time domain response.     

An improved nonlinear reduced-order modeling for transonic aeroelastic systems

In this study, an improved nonlinear reduced-order model composed of a linear part and a nonlinear part is explored for transonic aeroelastic systems. The linear part is identified via the eigensystem realization algorithm and the nonlinear part is obtained via the Levenberg–Marquardt algorithm. The impulsive signal is chosen as the training signal for the linear part and the sinusoidal signal is used to determine the order of the linear part. The training signal for the nonlinear part is selected as the filtered white Gaussian noise with the maximal amplitude and frequency range to be designed via the aeroelastic responses. An NACA64A010 airfoil and an NACA0012 airfoil are taken as illustrative examples to demonstrate the performance of the presented reduced-order model in modeling transonic aerodynamic forces. The aeroelastic behaviors of the two airfoils are obtained via computational fluid dynamics to solve the Euler equation and the Navier–Stokes equation, respectively. The numerical results demonstrate that the presented reduced-order model can successfully predict the nonlinear aerodynamic forces with and without viscous flows. Moreover, the presented reduced-order model is capable of capturing the flutter velocity and modeling complex aeroelastic behaviors, including limit-cycle oscillations, beat phenomena and nodal-shaped oscillations at the transonic Mach numbers with high accuracy.     

超音速气流中受热壁板的稳定性分析

采用Galerkin方法建立二维壁板的非线性气动弹性运动方程，用一阶活塞理论模拟壁板 受到的气动力. 基于李雅普诺夫间接法分析了平壁板的稳定性，得到了壁板失稳的边界 曲线；采用牛顿迭代法分析了壁板的屈曲变形，进而分析了后屈曲状态下壁板的稳定性； 在时域中分析了后屈曲状态下壁板的颤振边界. 分析结果表明，为了保证计算精度， 在二维壁板的静态失稳及过屈曲变形分析中，至少要取二阶谐波模态；在平壁板的超音速颤 振(动态失稳)边界分析中至少应取四阶模态. 还对壁板的温升，壁板长厚比、壁板密 度和气流马赫数作了无量纲变参分析，研究了这些参数的变化对壁板稳定性的影响规律. 研 究中发现，当气流速压较低时壁板一般会稳定在低阶谐波模态的屈曲变形位置，但是如果系 统出现多个渐近稳定的不动点，即使作用在壁板上的气流速压很低，壁板也有可能在较低速 压下发生二次失稳型颤振.     

Aeroelastic analysis of large horizontal wind turbine baldes

A nonlinear aeroelastic analysis method for large horizontal wind turbines is described. A vortex wake method and a nonlinear finite element method (FEM) are coupled in the approach. The vortex wake method is used to predict wind turbine aerodynamic loads of a wind turbine, and a three-dimensional (3D) shell model is built for the rotor. Average aerodynamic forces along the azimuth are applied to the structural model, and the nonlinear static aeroelastic behaviors are computed. The wind rotor modes are obtained at the static aeroelastic status by linearizing the coupled equations. The static aeroelastic performance and dynamic aeroelastic responses are calculated for the NH1500 wind turbine. The results show that structural geometrical nonlinearities significantly reduce displacements and vibration amplitudes of the wind turbine blades. Therefore, structural geometrical nonlinearities cannot be neglected both in the static aeroelastic analysis and dynamic aeroelastic analysis.     

平面叶栅气动试验研究进展与展望

平面叶栅气动试验传统上是验证压气机、涡轮的基元性能的主要手段, 近年来国内外研究人员利用平面叶栅开展了大量的流动测量试验, 以揭示叶栅内部复杂流动现象的本质和规律、探索减小叶栅内流动损失的方法. 本文从试验装置、测试技术和研究内容三个方面, 综述了近年来平面叶栅气动试验研究的进展情况. 首先介绍了平面叶栅试验装置的发展及提高平面叶栅试验段流场品质的措施; 其次介绍了叶栅气动试验采用的部分流场测试技术, 包括叶片表面压力场、叶片表面温度场、内流速度场及流场可视化等测试技术, 分析了这些测试技术的进展和存在的问题; 然后梳理了近年来平面叶栅试验研究的相关科学问题及进展, 包括跨音速叶栅中的激波研究, 叶顶间隙泄漏流动研究, 叶型优化研究, 多尺度非定常旋涡结构研究, 振动环境下叶栅流场研究等; 最后对平面叶栅气动试验研究方向进行了展望. 通过了解叶栅内复杂流动现象及本质, 为进一步探索和提高压气机、涡轮的气动性能提供技术支撑.