An experimental analysis of the effect of wind load on the stability of a container crane

This study was conducted to analyze the effects of wind loads on the stability of a 50-ton container crane using wind tunnel testing. The experiments were performed in order to furnish designers with data that can be used in the design of a container crane that is wind resistant, assuming an applied wind load of 75 m/s velocity. Data acquisition conditions for this experiment were established in accordance with similarity to a reduced-scale model. The scale of the container crane model, wind speed and time were selected as 1/200, 1/13.3, and 1/15, respectively, and the experiment was conducted using an Eiffel type atmospheric boundary-layer wind tunnel having a 11.52 m² cross-sectional area. All directional drag and overturning moment coefficients were investigated and uplift forces due to wind load at each supporting point were analyzed.     

分离箱梁门式起重机风力系数风洞试验与仿真分析

利用风洞试验和数值仿真方法系统分析分离箱梁的风力系数和形成机理,通过分析得出数值的仿真结果与试验结果能够相互验证;分离箱梁存在气动减阻优势,与单梁相比风力系数较小;针对分离箱梁的总体风力系数,可取C=1.37(相对于分离箱梁迎风面积),由此可知,合理得到分离箱梁门式起重机的风力系数对确定起重机风载荷具有重要作用。     

基于HFFB试验的结构广义荷载与风振响应分析

采用高频测力天平风洞试验技术得到的结构基底弯矩和扭矩进行结构风振响应分析时,只能考虑横向线性振型和扭转向常数型振型,忽略了结构高阶振型对结构响应的贡献。在分析高频测力天平风洞试验测试数据的基础上,以修正线性(常数型)振型广义荷载谱方法为依据,推导得到了结构横向和扭转向各阶振型广义荷载谱。同时,利用此各阶振型广义荷载谱进行了3种典型的格构式高耸结构气弹模型风振响应评估。通过比较气弹模型风洞试验结果和计算结果可知,当考虑振型修正、高阶振型和气动阻尼比后,计算结果与试验结果吻合较好,验证了推导得到的高阶振型广义荷载谱的准确性。     

A parametric study on the influence of boundary conditions on the longitudinal pressure gradient in CFD simulations of an automotive wind tunnel

Computational fluid dynamics (CFD) is an important and extensively used tool for aerodynamic development in the vehicle industry today. Validation of virtual methods by comparison to wind tunnel experiments is a must because manufacturers aim to substitute physical tests on prototype vehicles with virtual simulations. An appropriate validation can be performed only if the wind tunnel geometry with representative boundary conditions is included in the numerical simulation, and if the flow of the empty wind tunnel is accurately predicted. One of the important flow parameters to predict is the longitudinal pressure distribution in the test section, which is dependent on both the wind tunnel geometry and the settings of the boundary layer control systems. This study investigates the effects of flow angularity at the inlet and different boundary layer control systems, namely, basic scoop suction, distributed suction, and moving belts, on the longitudinal pressure distribution in the full-scale aerodynamic wind tunnel of Volvo Cars using CFD and a systematic design of experiments approach. The study shows that the different suction systems used to reduce boundary layer thickness upstream of the vehicle have statistically significant effects on the longitudinal pressure distribution in the test section. However, the estimated drag difference induced on a typical vehicle by the difference in horizontal buoyancy between the tested settings is within the test-to-test uncertainty of the physical wind tunnel, thereby leading to the conclusion that force calculations in simulations are fairly insensitive to the tested parameters on the investigated intervals.

     

风对大型港口机械的脉动效应研究

大型港口机械工作于码头前沿或近岸海域,风的影响不容忽视.传统港口机械的设计过程中风载按静载处理,忽略了风的脉动效应.因此在有限元建模的基础上,结合根据Shinozuka方法模拟的脉动风载荷,预测大型港口机械在工作状态和非工作状态的动态响应,并与传统将风载处理成静载的方法进行对比.研究结果表明:工作状态下,风的脉动效应对结构最大应力的幅值影响不大,其主要影响体现在最大应力点的空间分布,对最大应力数值影响不大,对支座反力的影响亦不明显;非工作状态下,风的脉动效应将引起支反力的大幅波动,此时平均值已不能充分衡量结构的安全性,必须同时关注其标准差与时间历程.     

Application of Computational Fluid Dynamics and Fluid–Structure Interaction Method to the Lubrication Study of a Rotor–Bearing System

Computational methods were used to analyse the elasto-hydrodynamic lubrication of a complex rotor–bearing system. The methodology employed computational fluid dynamics (CFD), based on the Navier–Stokes equation and a fluid–structure interaction (FSI) technique. A series of models representing the system were built using the CFD–FSI methodology to investigate the interaction between the lubrication of the fluid film, and elastic dynamics of the rotor and journal bearing. All models followed an assumption of isothermal behaviour. The FSI methodology was implemented by setting nodal forces and displacements to equilibrium at the fluid–structure interface, therefore allowing the lubrication of the fluid and the elastic deformation of structures to be solved simultaneously. This is significantly different to the more common techniques—such as the Reynolds equation method—that use an iterative solution to balance the imposed load and the force resulting from the pressure of the fluid film to within a set tolerance. Predictions using the CFD–FSI method were compared with the results of an experimental study and the predictions from an ‘in-house’ lubrication code based on the Reynolds equation. The dynamic response of the system was investigated with both rigid and flexible bodies for a range of different bearing materials and dynamic unbalanced loads. Cavitation within the fluid film was represented in the CFD–FSI method using a simplified phase change boundary condition. This allowed the transition between the liquid and vapour phases to be derived from the lubricant’s properties as a function of pressure. The combination of CFD and FSI was shown to be a useful tool for the investigation of the hydrodynamic and elasto-hydrodynamic lubrications of a rotor–bearing system. The elastic deformation of the bearing and dynamic unbalanced loading of the rotor had significant effects on the position of its locus.     

岸边集装箱起重机能耗测试与分析

针对岸边集装箱起重机的能耗问题,选取ZP型65 t岸边集装箱起重机作为测试样机,选用电能质量分析仪作为测试仪器,通过两瓦计法对岸边集装箱起重机的能耗进行系列测试,并基于所得测试数据分析了起重量、升降高度、升降速度、小车移动速度、小车移动距离等主要参数对能耗的影响,可为进一步的节能降耗工作提供参考和依据。     

Design optimization of a wind tunnel force balance using stepwise response surface method

A force balance measures the forces being applied to an object in a wind tunnel test. The force balance needs to be optimized to generate an acceptable gauge reading while guaranteeing no structural failure by the wind tunnel loadings. This paper proposes a stepwise response surface method (RSM) for design optimization of a force balance. Three sampling techniques were tried in the RSM study, and finite element simulation was used for functional evaluation. The first trial was based on broad sampling, followed by a second trial based on narrow sampling. The data from these trials was then utilized in a final regression, in which a quadratic model was generated to identify the final optimum point. The final design of the force balance provides satisfactory gauge readings with decreased stress values even though the roll moment is greatly increased.

     

岸边集装箱起重机大车机构实例库的构建和检索

论述了设计实例的表示与存储技术,针对大车机构提出了一种实例库的构建方案,研究了一种实例检索的算法,通过对实例库进行检索,获得符合设计制造要求的最佳匹配实例。并以大车机构为例,阐述并论证了实例库的构建和实例检索算法的实现过程与方法。     

大型岸边起重机的地震振动台试验研究

设计了集装箱码头岸边装卸起重机（简称岸桥）的1∶50缩比模型及其隔震装置;利用锤击模态试验和地震振动台试验获取了1∶50缩比模型在有无隔震装置下的动态特性和地震响应。试验结果表明：岸桥自身结构具有相对较大的地震抵抗力和整体稳定性,能够满足抗震设计的要求;隔震装置开启后,各测点应变响应的幅值及加速度响应的幅值均有明显的减小,这说明岸桥所采用的隔震装置设计合理有效,且减震效果明显。     

岸边集装箱起重机电缆小车缓冲器的选型

根据岸边集装箱起重机拖令系统运行特点,对比分析了电缆小车橡胶缓冲器的计算冲击力与现场实测冲击力的差异及原因,比较了橡胶缓冲器和聚氨酯缓冲器的优缺点,提出电缆小车缓冲器的设计选型原则。     

岸边集装箱桥式起重机钢结构小车运行方向振动固有频率的简易测试

根据岸边集装箱桥式起重机的结构特点,简化框架模型,采用简单易行的光点投影测试方法,进．行小车运行方向的振动周期及固有频率的测试,以对整机钢结构的动刚度进行检验和评估。     

基于灵敏度分析的集装箱龙门起重机结构的优化设计

运用有限元分析软件ANSYS对集装箱龙门起重机结构系统进行有限元分析。采用灵敏度分析方法,对其结构系统进行优化设计,提出一种重量较轻、静动态性能优良的集装箱龙门起重机结构设计方法。     

大型抗震集装箱起重机模型设计与动力分析

根据在地震载荷作用下大型集装箱起重机出现的损坏形式,以我国第一台带有抗地震装置的岸边集装箱起重机为原型进行地震试验的模型设计以预测起重机在地震作用下的响应。依照相似理论对试验模型进行设计分析,得到试验模型在外形尺寸、结构质量分布、刚度以及加速度的理论相似关系,并通过原型和试验模型的ANSYS有限元计算保证模型设计的正确性。通过地震载荷时程响应分析得出在起重机在不同工况以及抗震装置是否开启等多种状态下的轮压响应,地震台实验数据验证了抗震装置在地震过程中良好的抗震效果。     

某带罩反射面天线刚强度性能试验设计与验证

文中以某带罩反射面天线为研究对象,设计了模拟复杂环境载荷的曲面天线刚强度性能试验,通过风洞试验验证了设计试验的可行性,为电子装备的安全服役提供保障.文中重点讨论了复杂曲面天线模拟风载的近似加载方式和刚强度性能试验分析方法.最后,对比了模拟风载和风洞试验形变测试结果,发现两种试验方法的最大误差在6％以下,证明了实验室模拟...     

基于有限元法的轻型港口起重机结构动态分析

运用有限元分析法,按照港口起重机的结构特点和实际工作条件,建立整机的三维力学模型,并对其分别进行了模态分析、谐响应分析和瞬态分析,得出港口起重机在受外界激励作用时各阶危险频率下的变形情况,为动态设计提供参考．     

岸桥门框连接斜撑布置研究与优化

针对某型号岸边集装箱桥式起重机门框斜撑进行优化设计。首先应用结构拓扑优化技术,建立斜撑拓扑优化设计的模型;通过拓扑优化设计,得到三种斜撑的布置方案。然后基于斜撑的抗风振要求对斜撑进行尺寸优化,得到满足设计条件的质量最轻的优化结果。通过对优化后的斜撑结构在岸桥整机上的刚度和强度校核,验证了提出方法的有效性。     

组合支撑方式下气动多维力多点测量研究

飞行器的设计通常需以其模型在风洞试验中所获取的气动载荷为依据.对于大尺寸、大长径比的飞行器模型,其测试空间受限,常规支撑装置与测量方法难以满足风洞试验的尺寸与动态特性要求.针对上述问题,以压电传感器为核心测试元件,提出了一种结合张线支撑和尾部支撑的组合支撑方式,开发了一种支撑装置与测试元件一体化的气动多维力测试系统.分...     

Investigation of wind tunnel wall effect and wing-fuselage interference regarding the prediction of wing aerodynamics and its influence on the horizontal tail

The calculation of aerodynamic characteristics of a wing is the basic problem for aerodynamic design of aircraft. Wing aerodynamics can be determined experimentally and numerically. The method of fixing the wing in the test chamber of wind tunnel is related to disturbance of flow through the wing. When the wing is entirely fixed in the test chamber, the disturbance is usually caused by the sting connecting the wing to the test chamber. The experiments in this paper fixed the wing by clamping to the wind tunnel wall at the wing symmetry surface (root section). With this wing fixation, it was possible to take advantage of the wingspan twice, but to obtain the 3D wing experiment results, it was necessary to evaluate the impact of the wind tunnel wall effect. As for aircrafts, the aerodynamic force of the aircraft’s wing will have certain difference than that of the wing alone. The intersection region between the wind tunnel wall and wing root (for the experiment), as well as between the fuselage and wing root have complex interactions of boundary layers, in particular separation phenomena in the boundary layers. By solving the differential equation for viscous flows, it was possible to visualize the picture of streamlines and flow separations in this interference region and the aerodynamic characteristics of the wing. The singularity method was also used to compare results within its application range. The aerodynamic coefficients in the two cases with and without interference were analyzed. Complex interactions in the interference region could alter the predicted aerodynamic force calculated for the wing alone, which should be estimated. Very strong separations in the wing-fuselage interference region at large angles of attack turned into vortices at the rear impacting on the horizontal tail aerodynamics that is related to the balance problem of the aircraft.

     

折叠变体飞行器风洞试验模型设计与可靠性分析

特种高速风洞试验模型设计一直是风洞试验领域的难点问题.针对某变体飞行器高速风洞试验任务提出的运动性能指标,设计开发了可控的折叠变体试验模型,对其设计方案及工作原理进行了阐述,并对传动机构进行了优化设计,而后对传动机构进行了可靠性分析与计算.结果表明该试验模型能够对机翼折叠变体角度进行连续、稳定和精确控制,完全达到了设计要求的各项指标.