Reissner矩形板的弯曲问题

本文根据Rcissncr平板理论,提出了矩形中厚板弯曲问题的解答,应用本文中的(5)、(9)式,可求解通常边界条件下,承受横向均布力q_0以及承受横向均布力和板边法向弯矩等组合荷载共同作用下的矩形中厚板的弯曲问题,而且使这类问题的解答规律化。     

用加权余量法分析固支圆板和环板在Mises屈服条件下的极限荷载

应用加权余量法求出了承受线性荷载的固支圆板和承受均布荷载的内边界支承环板在 Mises屈服条件下的极限荷载的近似值 ,并与最大弯矩极限条件结果进行了比较 ,说明本文计算结果较合理。     

轴向运动SMA层合梁的主共振分析

研究了均布横向载荷作用下轴向运动SMA(形状记忆合金)层合梁的横向非线性振动。考虑轴向运动效应、轴力等因素的综合影响,利用力平衡条件、变形协调方程及SMA多项式函数的本构关系,建立了SMA层合梁在均布横向载荷作用下的动力学方程。针对两端简支边界条件,通过伽辽金积分得到了轴向运动SMA层合梁横向振动微分方程。应用平均法得到了横向载荷作用下系统主共振幅频响应方程,对理论结果进行了数值验证;分析了轴向运动速度、温度、激励参数对系统稳态响应的影响。结果表明:轴向速度、轴向载荷的变化只对系统共振频率产生影响;在外激励幅值较大时,温度增加和SMA层增厚对系统产生了相同的减振效果。     

最小二乘法在薄板塑性动力响应中的应用

本文通过拉普拉斯变换,将最小二乘法应用于薄板的塑性动力响应问题。文中分别以承受均布冲击荷载(中载情形)的简支圆板和方板的塑性动力响应问题为例,说明本文方法的计算方法及步骤,并显示出本文方法的优越性。     

荷载横向变位下变截面连续箱梁剪滞分析的有限梁段法

为研究荷载横向作用位置变化对箱梁剪滞效应的影响,对箱梁顶、底板、悬臂板分别设置了不同的剪滞纵向位移差函数;假定纵向翘曲位移沿横向分布为k次抛物线,并考虑剪滞和剪切双重效应的影响,通过能量变分法推导出了荷载横向变位时梁段单元的平衡控制微分方程组及其闭合解;提出了能对工程中常见的变截面连续箱梁剪滞效应进行分析的有限梁段法。该方法计算结果与有限元模型、已有模型试验结果的最大误差在5.95%~9.74%之间,两种工况下计算结果的叠加与有限元结果相对误差在0.07%~19.18%之间,均吻合良好,说明将基于有限梁段法的剪滞效应变分解和叠加原理用于求解复杂力状态下的剪滞效应是可行的。剪滞翘曲位移横向分布函数精度选择的研究结果表明:均布荷载分别作用于腹板顶部、顶板中心时,翘曲位移横向分布函数宜分别选用三次、二次抛物线。     

拱暨索拱面内稳定性研究的传递矩阵法

为探究拱桥面内稳定问题求解的新途径,应用传递矩阵法对径向均布荷载作用下的圆拱面内屈曲微分方程进行解答,利用边界条件导出其特征方程,从而求得其屈曲荷载。同时,结合力法以及拱上荷载集度与轴力的关系,将该理论方法推广到承受集中荷载的变截面拱以及索拱组合结构的稳定分析中,并和有限元ANSYS计算结果进行对比,验证了本文理论和方法的正确性。最后,研究了不同荷载工况下的边界条件、圆心角和截面惯性矩对拱结构面内稳定性的影响。结果表明,索拱结构的面内稳定性优于纯拱结构。     

最小二乘法在薄板塑性动力响应中的应用

本文通过拉普拉斯变换,将最小二乘法应用于薄板的塑性动力响应问题。文中分别以承受均布冲击荷载(中载情形)的简支圆板和方板的塑性动力响应问题为例,说明本文方法的计算方法及步骤,并显示出本文方法的优越性。     

组合荷载作用下拦污栅栅条稳定性计算通式

根据栏污栅的控制工况，指出栅条倾覆稳定的计算简图为集中力与均布荷载同时作用的双悬臂简支梁，应用瑞利商求解其倾覆稳定微分方程，给出了组合荷载作用时栅条稳定临界荷载计算方法，通过对比分析表明了本文方法的合理性，最后还介绍了该方法的工程应用，可供生产设计及修订规范参考。     

裂纹表面承受均布载荷时的应力强度因子及裂纹张开位移的边界配位法

本文针对裂纹表面承受载荷时的应力条件，提出了新的应力函数，对于各种裂纹模型、各种边界条件、各种边界形状、裂纹表面自由或承受均布载荷等均适用。并利用边界配位法，计算了裂纹表面承受均布载荷时的方型板内中心裂纹的应力强度因子（ＳＩＦ）及裂纹的张开位移（ＣＯＤ）。     

N层弹性连续体系在双圆均布复合荷载作用下的力学计算

本文提出了一种新的计算方法——递推回代法。运用此法,可以从弹性力学基本方程式和定解条件所得到的线性代数方程组解出在单圆均布垂直或水平荷载作用下N层(N为任意正整数)弹性连续体系各层应力、位移积分公式中积分常数的表达式。通过分析,文中得到适用于N层体系的在应力、位移积分计算中所用到的一系列公式。在此基础上,编制了双圆均布垂直荷载和水平荷载共同作用下N层弹性连续体系的电算程序,并列出了一个算例。     

Dynamics of single and twin circular jets in cross flow

2D-PIV is used to investigate the near field jet dynamics of a single and a tandem twin jet in cross flow at a blowing ratio of 3. The flow characteristics that were studied included jet trajectory and penetration, windward and leeward jet spread, and the size, location and magnitude of the reverse flow region. The tandem jet setup resulted in configuration where the rear jet was shielded by the front jet that allowed the rear jet to penetrate deeper into the cross stream. The penetration of front jet was found to be comparable to that of the single jet in the near field. Asymmetric jet spread was observed both in the windward and leeward side with higher jet spread in the leeward side for both the single and tandem jet configuration. Furthermore, for the tandem jet condition, the presence of rear jet was found to affect the windward spread of the front jet minimally. The windward and leeward spreads of the rear jet were observed to be decreased by the presence of the front jet. Reverse flow zones confined between the front and rear jets in tandem setup was also observed to be stronger than that of a single jet. A turbulent kinetic energy (TKE) analysis indicates that the behavior of a jet in tandem setup follows the same trend as that of an axisymmetric turbulent jet with low turbulence in the jet core and higher turbulence in the jet shear layer that subsequently transitions to high turbulence production in the jet core as the jet shear layers on windward and leeward side of the jet coalesce.     

Compressive strength of edge-loaded corrugated board panels

Postbuckling strength of simply supported corrugated board panels subjected to edge compressive loading has been studied experimentally using a specially developed test fixture. Although the load versus out-of-plane displacement response was highly sensitive to the presence of initial imperfections in the panels, the collapse loads did not vary much, which is attributed to the stable postbuckling behavior of the plates. Thin plates collapsed at nearly twice the buckling load, while thick panels collapsed at loads below the elastic critical buckling load. Local buckling of the facing on the concave side of the buckled plate was observed at load levels close to the collapse load. The plate collapse was triggered by compressive failure of the facings that initiated at the unloaded edges. A simplified design analysis was derived based on approximate postbuckling analysis and compared with an existing design formula for corrugated board panels and boxes.     

超音速流动中侧向喷流干扰特性的实验研究

在超音速流动中，进行了侧向喷流干扰特性的实验研究，研究了喷流压力、 攻角、迎风侧及背风侧喷流对侧向喷流干扰特性的影响. 结果表明，随喷流压力增大，喷流 前的高压区向前扩展，喷流的包裹作用加强. 有攻角时，背风侧喷流前的高压区更大，喷流 包裹作用的影响区域前移，喷流的控制效果更好，这一趋势随攻角的增大更加明显.     

支杆-钝头体带攻角流场和“军刺”挡板作用研究

通过三维N-S方程的数值求解, 研究了支杆-钝头体结构在10o攻角M∞=6.0飞行条件下的流场结构和特点, 指出其气动力特性恶化的原因, 提出采用``军刺'挡板改善流场和气动力特性, 并通过对比两种不同挡板作用下的流场和气动力特性变化分析其作用机理, 发现``军刺'挡板结构分割流场抑制三维效应形成的周向流动, 迎风面形成稳定的回流区和剪切层结构, 将迎风面锥激波推离轴线, 降低钝头体肩部流动结构相互作用强度, 并在一定程度上缓解背风面流动干扰, 明显改善支杆-钝头体带攻角飞行时的气动力特性.      

兼顾静动荷载的结构拓扑优化方法

为避免考虑瞬态动力性能时拓扑优化的高计算成本,满足工程快速设计的需求,获得主要静动荷载作用下的合理结构形态,本文提出了一种低计算成本的兼顾静动荷载的结构拓扑优化方法。施加的动荷载是地震等效荷载,用振型分解法和抗震规范中的反应谱曲线确定;通过结构形态、动力特性和地震等效静载的相互反馈和作用实现了考虑结构动力特性的拓扑优化;此外,还提出方法的自动进化策略。算例表明,方法可有效实现兼顾静动性能的拓扑优化。     

Influence mechanism on flow and heat transfer characteristics for air-cooled steam condenser cells

Air-cooled steam condensers (ACSCs) have been extensively utilized to reject waste heat in power industry to save water resources. However, ACSC performance is so sensitive to ambient wind that almost all the air-cooled power plants in China are less efficient compared to design conditions. It is shown from previous research that the influence of ambient wind on the cell performance differs from its location in the condenser. As a result, a numerical model including two identical ACSC cells are established, and the different influence on the performance of the cells is demonstrated and analyzed through the computational fluid dynamics method. Despite the great influence from the wind speeds, similar cell performance is obtained for the two cells under both windless and wind speed conditions when the wind parallels to the steam duct. Fan volumetric effectiveness which characterizes the fan performance, as well as the exchanger heat transfer rate, drops obviously with the increasing wind speed, and performance difference between the exchanger pair in the same A-frame also rises continuously. Furthermore, different flow and heat transfer characteristics of the windward and leeward cell are obtained at different wind angles, and ambient wind enhances the performance of the leeward cell, while that of the windward one changes little.     

EXPERIMENTAL INVESTIGATION ON THE EVOLUTION OF INTERNAL SOLITARY WAVE OVER A RIDGE AND ITS ACTING FORCES ON A SUBMERGED SLENDER BODY

内孤立波沿山脊地形传播过程中的结构变化使得影响海洋结构物及水下航行器安全的不确定因素增加,用大型重力式分层流试验水槽系统研究内孤立波过山脊地形及其对细长潜体作用力特性,可有效提高对其危害性机理的认识.为此,利用电导率探头阵列,结合染色标识方法,测量内孤立波演变特性,同时利用三分量传感器测量水下细长体模型受力特性.研究结果表明：山脊地形显著改变下凹型内孤立波结构,表现为坡前波幅增大,坡顶背风波面抬升,坡后波长变长;内波结构变化直接影响细长体受力特性,表现为坡前向下作用力明显增强,坡顶向上作用力突显,坡后作用力持续时间变长;细长体受力特性变化影响其运动趋势,坡前下沉运动增强、朝山脊方向纵荡运动显著.     

An experimental and three dimensional numerical study on the wind-related heat transfer from a rectangular flat plate model collector flush mounted on the roof of a model house

Experimental and three dimensional numerical work was performed to evaluate the average heat transfer coefficients for forced convection heat transfer from the surface of a rectangular flat plate model collector flush mounted on the roof of a model residential house. Examined parameters are the roof tilt angle, windward and leeward orientations. Experiments were carried out for mass transfer using the naphthalene sublimation technique. The final results were presented in terms of heat transfer parameters using the analogy between heat and mass transfer. Numerical study was performed using Ansys Fluent 6.3. Results of experimental study are in good agreement with that of numerical study. It is observed that heat transfer coefficient decreases very slowly with increasing angle of attack and it can be stated that angle of attack does not have a strong effect on heat transfer coefficients in the range investigated. It is also observed that heat transfer coefficients on the leeward orientation are lower than those of the windward orientation. Flow separation was observed on collector surface in leeward orientation.     

Conical gas flows with shock waves and turbulent boundary layer separation

The results of a theoretical and experimental investigation of nonsymmetric flow around a V-wing with supersonic leading edges are presented. The range of the angles of attack and yaw, on which additional singular lines are formed on the windward cantilever of the wing, are experimentally determined using different techniques of flow diagnostics. These are one convergence line and two divergence lines in the transverse flow which were not previously observable in the calculations of ideal-gas flow around wings. It is established that the appearance of the three new alternating singular lines located between the central chord of the wing and a convergence line, exterior to them and occurring within the framework of the ideal gas model, is associated with the relation between the intensities of two contact discontinuities. One of these proceeds from the branching point of the bow shock above the leeward cantilever, while the second issues out of the triple point of a λ-shaped shock configuration accompanying developed turbulent-boundary-layer separation generated by an internal shock incident on the leeward cantilever surface. If the intensity of the contact discontinuity proceeding from the branching point of the bow shock is large as compared with that of the contact discontinuity of the λ-configuration, then the flow pattern realized on the windward cantilever is analogous to that obtained within the framework of the ideal gas model, that is, it includes one convergence line on the wing surface. Under these conditions, the results of the calculations within the framework of the ideal gas model are applicable for understanding the phenomena occurring in the wing shock layer in a considerable part of the control parameter range, including the regimes with intense internal shocks generating turbulent boundary layer separation from the leeward cantilever. Corrections should be made only for a carachteristic pressure distribution in the separation zone and, as a consequence of separation, for an elevated pressure level in the vicinity of the central chord which is the stagnation line of the transverse flow that has passed across the oblique and terminating shocks of the λ-configuration and possesses a higher stagnation pressure than the flow that has passed in an ideal gas across the internal shock incident normally on the leeward cantilever. This is possible only when the divergence line, at which the stream surface enclosing the turbulent boundary layer separation zone enters, does not go over from the leeward onto the windward cantilever.     

An Energy Method Applied to Large Elastic Deflection of a Thin Plate of Bimodulus Material

Abstract

Some composite materials and high-polymers are known to behave differently in simple tension and compression under static loads. The present paper is concerned with a method of analysis of the bending of bimodulus elastic plates employing Ambartsumyan-Khachatryan's model for isotropic bimodulus materials. This problem may be reduced to the conventional problem of minimizing the potential energy of the plate as a whole. A simply supported thin square plate subjected to lateral load is analyzed numerically by a simplex method. Results of the calculation show that the effect of the difference between the tensile and compressive elastic moduli on the deformation of the plate may be substantial