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.     

高超声速全动舵面的热气动弹性研究

根据分层求解原理对考虑舵轴及舵轴与机身间隙影响下的高超声速飞行器全动舵面进行了热气动弹性分析. 采用计算流体力学（CFD）方法求解N-S 方程计算舵面周围的热环境,在该温度分布下根据结构壁面温度计算热流,应用傅里叶（Fourier）定律确定结构热传导过程及其内部温度分布,进而分析结构考虑热应力和温度对材料属性的影响下的模态固有特性,结合基于CFD 技术的当地流活塞理论,在状态空间中对舵面进行了热气动弹性分析. 结果表明,气动加热效应改变了结构的固有频率以及弯扭耦合频率之间的间距,进而改变了结构的颤振速度和颤振频率;随着热传导的进行,结构固有频率和颤振频率先快速减小后基本保持不变,弯扭耦合频率之间的间距和颤振速度则先快速减小后略有上升;舵轴及舵轴与机身间隙的存在对舵面的固有频率、颤振频率、颤振速度都产生了影响,使其最大下降了6%.      

螺桨转子颤振涡动的一种算法

介绍螺桨转子系统颤振涡动的一种算法。本算法考察桨叶的振动变形，桨轴－支承系统的振动特性，以及螺转子的不平衡力。利用本算法对一模型螺桨转子和一实际螺桨转子进行了分析计算，对螺桨转子轴头动刚度、浆叶弹性变形、桨盘不平衡度等因素对螺桨转子系统颤振涡动的影响进行了分析，表明螺桨转子轴头动刚度下降时，螺浆发生颤振涡动的极限飞行速度下降。模型螺桨转子的计算结果与风洞试验结果相当吻合，证明本算法是正确的。     

LIMIT CYCLE FLUTTER CHARACTERISTICS RELATED TO CONTROL SURFACE OF LARGE AIRCRAFT1)

操纵面间隙会引起结构非线性,容易诱发极限环颤振。根据设计需要,考虑操纵面中心间隙的影响,采用最小状态拟合技术对频域非定常 气动力进行有理函数拟合,采用分段函数描述间隙引起的非线性刚度,研究操纵面在间隙作用下的极限环颤振响应的行为特点。结果表明,由于 中心间隙的影响,系统会在低于线性颤振速度时就产生极限环振荡,同时,振荡幅值随飞行速度或中心间隙的增大而增大。     

一类二自由度系统振动的黄金分割率

作为数学史上一个重要的比例关系,黄金分割理论已在美学、建筑学甚至工程学中发挥了一定的作用.为了研究一类二自由度系统振动的黄金分割效应,首先介绍了黄金分割的基本理论,然后分别分析了该类二自由度体系的自由振动特征,以及简谐载荷作用下受迫振动的共振机制.结果表明,结构圆频率与层刚度和质量之比、两结构质点振幅之比都符合黄金分割率,结构在振动中具有和谐之美.     

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.      

一类新型多方向准零刚度隔振平台

本文提出了一种新的多自由度非线性隔振平台．利用一组预压的三角机构和曲面边界同时实现了竖直-旋转多自由度上的负刚度特性,结合正刚度原件,实现竖直-旋转多自由度准零刚度特性．首先,文章基于平面问题建立竖直-旋转两自由度隔振平台的力学模型,确定结构参数与非线性刚度之间的关系．可以看到,通过设计预压弹性元件的结构参数可以同时实现两自由度的准零刚度特性．然后,利用谐波平衡法建立振动响应与频率之间的关系,确定有效的振动带隙的宽度,由此确定结构参数的最优取值．本文提出的隔振平台可以用于大型装备的隔振,也适用于微振动的工况,还可以作为教学的演示实验．     

大型飞机操纵面极限环颤振特性研究

操纵面间隙会引起结构非线性,容易诱发极限环颤振。根据设计需要,考虑操纵面中心间隙的影响,采用最小状态拟合技术对频域非定常气动力进行有理函数拟合,采用分段函数描述间隙引起的非线性刚度,研究操纵面在间隙作用下的极限环颤振响应的行为特点。结果表明,由于中心间隙的影响,系统会在低于线性颤振速度时就产生极限环振荡,同时,振荡幅值随飞行速度或中心间隙的增大而增大。     

螺桨盘转子轴头动刚度实验测量方法及技术处理

在螺桨盘转子系统的颤振涡动研究中,系统的安装刚度对转子的颤振涡动失稳有着重要的作用.对于飞机发动机,实际安装情况十分复杂,发动机短舱.安装节、机翼等对螺桨盘转子的运动均有影响.所以,在颤振涡动研究中,必须考虑轴头的动刚度.轴头的动刚度是通过动柔度转换而来的,而在动柔度的实验测量中必须解决几个技术问题,首先是提高信噪比.其次是消除工艺夹具带来的附加质量和附加转动惯量的影响,从而提高动刚度系数的测量精度.本文通过对模型转子以及某实际桨轴发动机转子轴头动刚度系数的测量及处理,阐述轴头动刚度矩阵的测量方法,以及有关技术问题的处理过程.     

机床非线性颤振的描述函数分析

本文采用描述函数方法分析机床的非线性颤振.以描述函数刻划切削过程复杂的非线性特性,并将非线性振动分析所依赖的复平面推广到三维空间进行稳定性分析。从而求出颤振振幅和颤振频率。该法不仅可揭示切削过程等效刚度系数和等效阻尼系数的变化,而且还可考察各切削参数对颤振频率和振幅的影响.结果表明,描述函数方法是分析机床颤振这个极其复杂的非线性系统的一个有效的手段.     

AN ASYMPTOTIC METHOD FOR ANALYZING THE STRESS IN A FUNCTIONALLY GRADIENT MATERIAL LAYER ON A SURFACE OF A STRUCTURAL COMPONENT

A simple and effective method for analyzing the stress distribution in a FunctionallyGradient Material(FGM)layer on the surface of a structural component is proposed in this paper.Generally,the FGM layer is very thin compared with the characteristic length of the structural compo-nent,and the nonhomogeneity exists only in the thin layer.Based on these features,by choosing asmall parameter λ which characterizes the stiffness of the layer relative to the component,and expand-ing the stresses and displacements on the two sides of the interface according to the parameter λ,thenasymptotically using the continuity conditions of the stresses and displacements on the interface,a de-coupling computing process of the coupling control equations of the layer and the structural componentis realized.Finally.two examples are given to illustrate the application of the method proposed.     

Stability of shock waves with finite relaxation region

A theoretical investigation is made into the amplification of sound in a moving nonequilibrium medium and it is shown that an instability can arise in a sufficiently strong shock wave accompanied by an exothermic process with finite relaxation region, the instability being due to the spontaneous growth of fluctuations resulting from amplification of acoustic waves in the region of exothermic relaxation and their trapping in a narrow layer near the shock wave.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 176–179, September–October, 1982.I thank S. V. Iordanskii for posing the problem and great interest in the work.     

Supercritical as well as subcritical Hopf bifurcation in nonlinear flutter systems

The Hopf bifurcations of an airfoil flutter system with a cubic nonlinearity are investigated, with the flow speed as the bifurcation parameter. The center manifold theory and complex normal form method are Used to obtain the bifurcation equation. Interestingly, for a certain linear pitching stiffness the Hopf bifurcation is both supercritical and subcritical. It is found, mathematically, this is caused by the fact that one coefficient in the bifurcation equation does not contain the first power of the bifurcation parameter. The solutions of the bifurcation equation are validated by the equivalent linearization method and incremental harmonic balance method.     

A simple method for calculating thermal expansion of crystals

Summary A simple method based on the classical statistical mechanics is suggested for the calculation of thermal expansion of crystals. The adequacy of the procedure is tested for alkali halide crystals in conjunction with the interatomic potential of the modified Born-Mayer Type.     

联接刚度对机翼／外挂系统颤振边界特性的影响

本文对带外挂物二元机翼的颤振特性进行了理论和实验研究,主要分析机翼与外挂物之间俯仰联接刚度对颤振边界的影响。在大量算例的分析基础上,给出了颤振频率及颤振边界变化的一般规律及对颤振边界类型的一般判别方法,颤振模型的风洞实验验证了理论分析结果的正确性。     

Dynamic stability analysis of shear-flexible composite beams

Dynamic stability behavior of the shear-flexible composite beams subjected to the nonconservative force is intensively investigated based on the finite element model using the Hermitian beam elements. For this, a formal engineering approach of the mechanics of the laminated composite beam is presented based on kinematic assumptions consistent with the Timoshenko beam theory, and the shear stiffness of the thin-walled composite beam is explicitly derived from the energy equivalence. An extended Hamilton’s principle is employed to evaluate the mass-, elastic stiffness-, geometric stiffness-, damping-, and load correction stiffness matrices. Evaluation procedures for the critical values of divergence and flutter loads of the nonconservative system with and without damping effects are then briefly introduced. In order to verify the validity and the accuracy of this study, the divergence and flutter loads are presented and compared with the results from other references, and the influence of various parameters on the divergence and flutter behavior of the laminated composite beams is newly addressed: (1) variation of the divergence and flutter loads with or without the effects of shear deformation and rotary inertia with respect to the nonconservativeness parameter and the fiber angle change, (2) influence of the internal and external damping on flutter loads whether to consider the shear deformation or not.     

A phase field model for failure in interconnect lines due to coupled diffusion mechanisms

We describe a diffuse interface, or phase field model for simulating electromigration and stress-induced void evolution and growth in interconnect lines. Microstructural evolution is tracked by defining an order parameter, which takes on distinct uniform values within solid material and voids, and varying rapidly from one to the other over narrow interfacial layers associated with the void surfaces. The order parameter is governed by a form of the Cahn-Hilliard equation. An asymptotic analysis demonstrates that the zero contour of order parameter tracks the motion of a void evolving by coupled surface and lattice diffusion, driven by stress, electron wind and vacancy concentration gradients. Efficient finite element schemes are described to solve the modified Cahn-Hilliard equation, as well as the equations associated with the accompanying mechanical, electrical and bulk diffusion problems. The accuracy and convergence of the numerical scheme is investigated by comparing results to known analytical solutions. The method is applied to solve various problems involving void growth and evolution in representative interconnect geometries.     

Flutter analysis of rotating beams with elastic restraints

The aeroelastic stability of rotating beams with elastic restraints is investigated. The coupled bending-torsional Euler-Bernoulli beam and Timoshenko beam models are adopted for the structural modeling. The Greenberg aerodynamic model is used to describe the unsteady aerodynamic forces. The additional centrifugal stiffness effect and elastic boundary conditions are considered in the form of potential energy. A modified Fourier series method is used to assume the displacement field function and solve the governing equation. The convergence and accuracy of the method are verified by comparison of numerical results. Then, the flutter analysis of the rotating beam structure is carried out, and the critical rotational velocity of the flutter is predicted. The results show that the elastic boundary reduces the critical flutter velocity of the rotating beam, and the elastic range of torsional spring is larger than the elastic range of linear spring.     

Constitutive model for high speed tillage using narrow tools

Dynamic effects on soil–tool cutting forces are important when operating at elevated speeds. The rate-dependent behavior of narrow tillage tools was investigated in this study. A hypoelastic soil constitutive relationship with variable Young's modulus and Poisson's ratio was developed to describe the dynamic soil-tool cutting problem. An initial finite element formulation with viscous components incorporated in the stiffness matrix resulted in severe numerical oscillations. A modified model that incorporated lumped viscous components in the equation of motion (independent of the stiffness matrix) was proposed. Numerical oscillations still occurred, but at sufficiently high tool displacements (1–10 mm) to enable the determination of peak draft forces. Experimental data for flat and triangular edged narrow tools were obtained using a 9-m long linear monorail system designed to accelerate narrow tools through a linear soil bin to high speeds. Steady-state speeds from 0.5 to 10.0 m/s over a distance of 1 to 3 m were attained using this system. A reference-tool inverse procedure was used to estimate the dynamic soil parameter in the soil model using draft data obtained for the flat tool. Predictions of triangular tool draft produced correct trends but overestimated experimental data. Draft was overpredicted by less than 1% at a tool speed of 2.8 m/s and by 25% at 8.4 m/s.