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根据抗拉刚度等效及抗弯刚度等效将换热器管束简化为当量圆筒以考察其对 斜锥壳应力状况的影响,同时根据轴向载荷等效及泊松效应等效,对作用在管板布管限定圆 内的压力载荷及作用在管束外表面的压力载荷进行了当量转换,建立了考虑管板及管束影响 的斜锥壳应力分析简化模型. 有限元计算结果表明,大端转角过渡区存在较大的弯曲应力. 对一系列结构尺寸的斜锥壳进行了计算,整理了斜锥壳大端转角过渡区基于分析设计的应力 强度水平系数.     

拉压性能不同材料全量型本构关系及厚壁筒的应力分析

将经典全量理论作了推广，考虑了应力状态及塑性体积变形对拉压性能不同材料的塑性行为的影响。应用该本构模型分别计算了厚壁筒在内压和外压作用下的应力分布。给出了径向应力、环向应力和轴向应力沿壁厚的分布图。将本文的计算解与拉压性能相同(不考虑体积变形、强化曲线唯一)的幂函数强化材料的厚壁筒的理论解进行了比较。结果表明，材料的拉压性能不同对厚壁筒的环向应力和轴向应力影响较大。因此，对于拉压性能不同材料，考虑到其对应力状态及塑性体积变形敏感时，是不能将其简化成拉压性能相同、体积不可压缩、强化曲线唯一的理想材料。     

考虑温度效应的起落架落震缓冲性能研究

为了研究环境温度对起落架缓冲性能的影响，以某型飞机起落架为研究对象，考虑温度对起落架动力学模型中空气弹簧力和油液阻尼力的影响，提出了一个包含温度效应的起落架动力学分析模型，并通过试验在一定温度范围内(-35℃～60℃)进行了验证。结合试验数据和仿真模型给出了空气多变指数、油液阻尼系数的设计指导值，并研究了温度对起落架缓冲性能的影响规律。结果表明：环境温度对起落架缓冲性能影响显著，表现为起落架落震动载荷的变化；同时发现缓冲器腔内气体较油液受温度影响更为敏感，低温状态时气压的变化以及油液物理状态的改变会使得缓冲器性能明显恶化，缓冲支柱行程变化率达到25%;对于可能工作在复杂环境下的起落架，设计阶段需要充分考虑温度对缓冲器内气压和油液的影响，确保飞机着陆安全。     

初应力对单向复合材料圆柱板周向波的影响

基于“增量变形力学”理论,研究了径向和轴向均匀初应力作用下单向复合材料圆柱板中周向波的传播特性,应用Legendre多项式方法求解了耦合波动方程。讨论了单向复合材料纤维方向分别为周向和轴向时,初应力对圆柱板中的周向类Lamb波和SH波的影响。数值分析结果表明初应力对周向类Lamb波和周向SH波的影响是非常不同的;轴向初应力对频散曲线、位移和应力分布的影响与径向初应力的影响也不相同。     

管道封堵机器人的大变形橡胶筒静态密封特性仿真与试验研究

在管道封堵机器人中大变形橡胶筒是实现密封的核心部件,其在使用中常出现密封失效和撕裂失效等问题.为了明晰上述原因和解决问题,本文中研究了不同橡胶材料以及不同橡胶筒轴向长度、径向长度和倾斜边角等结构参数对管道封堵机器人的静态密封特性影响.基于橡胶材料的高弹性和大变形特性,进行了橡胶筒的多阶段变形力学分析.对橡胶材料进行单轴拉伸压缩试验,得到橡胶材料的本构关系参数.建立管道封堵机器人橡胶筒密封特性分析的有限元计算模型,通过多因素分析方法,获得橡胶筒关键结构参数的最优方案.并设计了室内试验来进一步确定最优橡胶筒材料.研究结果表明集中在橡胶筒肩部的应力直接影响橡胶筒的形变损伤.经过橡胶筒的密封效果对比分析后得出最优的橡胶筒结构为轴向长度180 mm、径向厚度55 mm、倾斜边角28°,橡胶材料硬度为85 HA.     

不同加载速率下煤的侧向变形特征研究

利用TAW-2000型电液伺服岩石力学试验系统开展了5种不同加载速率下的单轴压缩试验,分析了加载速率对煤体侧向变形特性的影响。研究结果表明:在裂纹闭合压密阶段、弹性变形至裂纹稳定扩展阶段,煤样变形以轴向压缩为主,侧向变形很小;在裂纹非稳定扩展阶段侧向应变开始加速增大,并在峰前应力调整阶段出现小幅陡增现象;在峰后扩容阶段煤样侧向应变急剧增大,呈现扩容与脆性破坏多次交替出现的特征,这一阶段大多数试件的侧向应变占总侧向应变的70%～90%。在加载初期煤样侧轴比处于较低水平,当轴向应力出现第一次跌落以后,煤样侧向应变快速增大,而轴向应变增加速度较小,导致试件侧轴比呈现快速增大直至试验结束。不同加载速率下煤样第一次出现轴向应力跌落时的侧向应变保持在3.0×10-3左右,表明在不同加载速率下煤样出现第一次轴向应力跌落时的侧向应变基本相同,可将侧向应变作为预测煤体破坏的控制变量。     

关于铸铁受压时破坏方向问题的探讨

 用应力理论以及莫尔强度理论，分析试样在均匀轴向受压和非均匀轴向受压时的受 力状态，讨论铸铁受压时的破坏方向和破坏原因.     

边界受限下的轴向压缩超弹性圆管的失稳分析

橡胶制品广泛应用于社会生产和日常生活。本文主要研究外边界受限的超弹性圆管受轴向压缩时的稳定性问题,在非线性弹性理论框架下推导控制方程,对其进行线性分岔分析。考虑沿轴向对称分布的失稳模态,得到临界模态以及对应的临界主伸长,同时刻画出临界主伸长以及临界应力与壁厚之间的关系。结果表明,圆管壁越薄,发生分岔时的临界主伸长更小,更不容易发生失稳。此外,结合封隔器的密封原理,推导出封隔器圆筒在进行油液密封时轴向应力与接触应力的表达式,修正了此前的推导结果,为封隔器在密封性能的判断上提供理论依据。     

着陆冲击力对起落架摆振的影响

为了分析着陆冲击力对起落架摆振特性的影响,考虑支柱缓冲器的负油孔面积,在ADAMS中建立了某飞机起落架的虚拟样机模型,并对该模型进行了动力学分析,得到了起落架缓冲系统负油孔面积对轮胎与地面之间接触力的影响曲线、对前轮摆角的影响曲线、在不同垂直降落速度下摆幅的对比曲线,并结合摆振基本理论进行分析。结果表明：负油液阻尼孔面积减小或飞机触地垂直降落速度增大时,对应的着陆冲击力增大,使摆幅增大;当负油孔面积小于50.5mm2或飞机着陆时的垂直降落速度大于1773mm/s时,由于着陆冲击力过大,使摆振极不稳定。     

初始应力对碳纳米管横波传播的影响

本文研究初始应力对碳纳米管在极高频率（大于1THz）下横波传播的影响。计算结果表明：轴向初始应力的存在除了改变碳纳米管的横向波速和管间振幅比的大小（压应力时横向波速降低，管间振幅比增加，拉应力时结论相反）外，还会影响其横向波速的数目。双层碳纳米管受轴向初始压应力时，在某个频率区域存在最多三个横向波速，与受轴向初始拉应力和未受轴向应力时最多只存在两个横向波速有所不同。     

飞机起落架着陆撞击动力分析

根据现有沿－气式缓冲器结构形式,针对模拟起落架着陆撞击过程的落 震试验模型,考虑起落架航向刚度和阻尼的影响,依据撞击过程中各变量间的运动关系,建立了描述着陆过程中的运动微分方程组,并采用龙格库塔法对运动微分方程组进行求解。最后采用该方法对Ｋ８飞机主起落架（单腔）和某机起落架（双腔）落震试验过程进行了模拟,并与试验结果进行了比较,发现计算结果与试验结果吻合较好。     

Transverse Elastic–Friction Vibrations of a Running Aircraft

An analytical model of the plane-parallel running of an aircraft under crosswind load is proposed. The compliance of the internal constraints of the aircraft and the nonlinearity of the side force on the landing gear wheels are taken into account. The model is intended to study the transverse elastic friction vibrations of the aircraft hull and landing gears. The steady motion of the aircraft is considered. The dependence of the lateral friction force on the slip angle is assumed to have the form of a sinusoidal segment. The Routh–Hurwitz instability conditions are derived in an explicit form     

Interaction of torsion and lateral bending in aircraft nose landing gear shimmy

In this paper we consider the onset of shimmy oscillations of an aircraft nose landing gear. To this end we develop and study a mathematical model with torsional and lateral bending modes that are coupled through a wheel-mounted elastic tyre. The geometric effects of a positive rake angle are fully incorporated into the resulting five-dimensional ordinary differential equation model. A bifurcation analysis in terms of the forward velocity and the vertical force on the gear reveals routes to different types of shimmy oscillations. In particular, we find regions of stable torsional and stable lateral shimmy oscillations, as well as transient quasiperiodic shimmy where both modes are excited.     

Mechanical phenomena in ground run of an aircraft with near-critical slip angles

The paper is concerned with mechanical phenomena accompanying ground run of aircraft with near-critical slip angles. Such phenomena (reduced effectiveness of directional control, self-excited frictional vibrations of a landing gear, internal resonance of an aileron, transverse oscillations of the legs of a multileg landing gear) are due to the nonlinear dependence of the side force on the slip angles __________ Translated from Prikladnaya Mekhanika, Vol. 42, No. 6, pp. 128–135, June 2006.     

Landing gear noise control using perforated fairings

Landing gears of commercial aircraft make an important contribution to total aircraft noise in the approach configuration. Using fairings to shield components from high speed impingement reduces noise. Furthermore, perforating these fairings has been confirmed by flight tests to further enable noise reduction. Following an earlier fundamental study of the application of perforated fairings, a study has been performed to investigate and optimize the benefits of bleeding air through landing gear fairings. By means of wind tunnel tests, an aerodynamic and acoustic survey has been performed on a simplified generic main landing gear to explore the influence of （perforated） fairings on the lower part of the gear. The results show that for this specific case, the application of impermeable fairings reduces noise in the mid- and high frequency range by shielding sharp edged components from high velocity impingement. However, below 1 kHz the noise is shown to increase significantly. Application of the perforations is shown to diminish this low frequency increase whilst maintaining the reduction in the mid- and high frequency range. The aerodynamic and acoustic measurements point in the direction of the separated flow of the fairings interacting with the downstream gear components responsible for the low frequency noise increase. Bleeding of the air through the fairings reduces the large scale turbulence in the proximity of these components and hence diminishes the low frequency noise increase.     

Multi-parameter bifurcation study of shimmy oscillations in a dual-wheel aircraft nose landing gear

We develop and investigate a mathematical model of an aircraft nose landing gear with a dual-wheel configuration. The main aim here is to study the influence of a dual-wheel configuration on the existence of shimmy oscillations. To this end, we consider a model that describes the torsional and lateral vibrational modes and the non-linear interaction between them via the tyre-ground contact. More specifically, we perform a bifurcation analysis (with the software package auto) of the model in the two-parameter plane of forward velocity of the aircraft and vertical load on the nose landing gear. This two-parameter bifurcation diagram allows one to identify regions of different dynamics, and the question addressed here is how it depends on two key parameters of the dual-wheel configuration. Namely, we consider the influence of, first, the separation distance between the two wheels and, second, of gyroscopic effects arising from the inertia of the wheels. For both cases, we find that with increasing separation distance and wheel inertia, respectively, the lateral mode becomes more stable and the torsional mode becomes less stable. More specifically, we present associated bifurcation scenarios that explain the transitions between qualitatively different two-parameter bifurcation diagrams. Overall, we find that the separation distance and gyroscopic effects due to wheel inertia may have a significant influence on the quantitative and qualitative nature of shimmy oscillations in aircraft nose landing gears. In particular, the torsional and the lateral modes of a dual-wheel nose landing gear may interact in a quite complicated fashion.     

Aeroelastic analysis of an idealized landing gear door in subsonic potential flow

Landing gear doors on aircraft have experienced flutter during preliminary flight testing. While designs vary widely, landing gear doors are typically plate-like structures with a relatively rigid actuator attached to their inside surface. To better understand the aeroelasticity of landing gear doors, this study investigates the aeroelastic stability of an idealized model. The model consists of a hinged plate with an interior constraint approximating the actuator attachment. The plate is subject to uniform flow, and an unsteady vortex lattice model is coupled to the structural model to predict critical flow velocities. The location and footprint area of the internal constraint, along with plate aspect and mass ratios, are varied to investigate a large parameter space. Results reveal that the critical flow speed and instability mechanism are sensitive to the postulated actuator placement. In general, flutter is the dominant mode of instability when the actuator is postulated in the leading quarter of the plate. In other postulated locations, divergence dominates. However, the exact shape and location of the boundary between flutter and divergence is configuration dependent and found to be especially sensitive to changes in aspect ratio.     

Fiber Remodeling During Torsion of a Fiber Reinforced Hyperelastic Cylinder��Unloading Behavior

Previous studies introduced a constitutive theory for fiber reinforced hyperelastic materials that allows the fibers to undergo microstructural changes. In this theory, increasing deformation of the matrix leads to increasing stretch of the fibers that causes their gradual dissolution. The dissolving fibers reassemble in the direction of maximum principal stretch of the matrix. The implications of the constitutive theory were first studied for two homogeneous deformations: uniaxial extension along the fibers and simple shear in the direction normal to the fibers. The constitutive theory was then used in treatment of the non-homogeneous deformation of combined axial stretch and twisting. The emphasis was on the determination of the influence of increasing axial stretch and twist on the spatial distribution of fiber dissolution and reassembly within the cylinder and also on the axial force and torque applied to the end faces of the cylinder. The present work is concerned with another aspect of combined axial stretch and twisting of the cylinder, namely unloading following dissolution and reassembly of some of the fibers. In this case, the cylinder is given an initial twist until there is an inner core of original fiber/matrix material and an outer sheath of remodeled fiber/matrix material. A condition is established that determines the combinations of axial stretch and twist that cause no additional dissolution and reassembly of fibers during unloading. It is also shown that there is a residual axial stretch and twist if the axial force and torque become zero. A numerical example illustrates this for a particular choice of matrix and fiber properties.     

基于落震试验的油—气式起落架气体压缩多变指数变化规律研究

气体压缩多变指数是油气式起落架缓冲性能计算中的重要参数。通过对某型飞机油气式起落架落震试验中气腔压力数据的监测,对不同落震投放高度下气体压缩多变指数进行识别。利用最小二乘法,对多变指数变化曲线进行三次拟合,得出活塞杆压缩过程中气体多变指数的变化规律。本文建立了某型飞机起落架落震试验仿真分析模型,将拟合曲线引入仿真计算模型,对比了定常多变指数计算模型和非定常多变指数计算模型仿真结果。相对于定常多变指数模型,非定常多变指数计算模型仿真结果和试验对比误差小于定常多变指数计算模型,提高了仿真分析精度。     

Numerical simulation of Taylor Couette flow of Bingham fluids

The Bingham fluid flow between two concentric cylinders is studied using numerical simulation. The cylinders are assumed to rotate independently, and with an imposed axial sliding. The flow field is decomposed with linearity arguments of the base circular Couette shear flow and corresponding deviation field. The numerical methods are based on the expression of the deviation field in terms of complete sets of orthogonal functions and Chebyshev series. The Galerkin projection method is used with the pressure term being eliminated. The Adams Bashforth scheme is adopted for time marching. The results show that the vortices are squeezed toward the inner cylinder due to the effect of yield stress. When the outer cylinder is held stationary, the yield stress plays a role in weakening the vortex flow. However, for the co-rotation situation, the vortex flow is initially strengthened with an increase of yield stress, and then weakened as the yield stress is raised large enough. The annular unyielded regions emerge and stick to the outer cylinder. In case of Taylor Couette flow with an imposed axial sliding, a spiral vortex flow is visible with spiral unyielded region being obtained.