微凸体油膜弹性支承效应的刨切试验验证研究

论述了切削过程切屑卷曲的主要机理,利用该理论通过试验手段,验证并分析了边界润滑状态下,被切削工件表面微凸体油膜弹性支承问题,进一步论证了"微凸体油膜弹性支承效应"的客观存在.     

微凸体油膜弹性支承效应的刨切试验验证研究

论述了切削过程切屑卷曲的主要机理,利用该理论通过试验手段,验证并分析了边界润滑状态下,被切削工件表面微凸体油膜弹性支承问题,进一步论证了“微凸体油膜弹性支承效应”的客观存在。     

边界效应对导弹头罩流场热环境数值仿真影响

针对边界效应对超声速导弹头罩热力环境数值仿真准确度产生影响的问题，采用流-热-固多场耦合分区求解方法，建立了导弹头罩数值仿真模型，对其流场与结构温度场进行数值模拟，实现导弹头罩流场热环境精确仿真计算和边界效应对导弹头罩热力环境数值仿真影响分析。结果表明：随着边界远离头罩驻点，温度场的边界效应逐渐减弱；边界距离头罩驻点的远近对压力场无影响；热环境分析时需要考虑边界效应，流场分析时可以忽略此效应；此研究对导弹头罩热力环境预示数值仿真计算具有指导意义。     

半空间内圆形反平面震源的地面响应研究

地下震源对地面是存在动力效应的,研究这种响应对于地震减灾、防震、震源反演等都是非常重要的。对地下存在圆形反平面谐和震源的动力学问题进行研究,首先利用虚源法写出满足半空间边界应力自由条件的位移波函数,再利用圆形震源边界上的应力边界条件推出含有未知系数的非线性方程,借助于格拉夫(Graf)加法公式和傅立叶级数展开得到未知系数的无穷线性方程组,通过有限项截断得到有限线性方程组,最终确定了介质内的位移场和应力场。利用一个算例具体讨论了地面位移响应和圆形震源边界处的环向应力的变化规律,说明了方法的有效性。     

采用镜像延拓和RBF神经网络处理EMD中端点效应

在分析经验模态分解端点效应出现原因的基础上,采用镜像延拓法和径向基函数神经网络预测法对端点效应进行了研究,并对一组数值仿真信号和12层钢筋混凝土框架模型振动台试验实测得到的加速度信号进行了边界处理和经验模态分解。算例结果表明,这两种方法基于边界两端预测数据,都可以有效抑制端点效应对分析信号的影响,提高经验模态分解的效果。另外,对于复杂信号仅采用径向基函数神经网络延拓原始信号,对抑制端点效应的效果不很明显,而对复杂信号经滤波后先利用径向基函数神经网络预测、再利用镜像延拓进行处理,则可以明显抑制端点效应的影响。     

基于边界效应和非牛顿效应的活塞杆密封润滑分析

针对活塞杆密封平行间隙建立了适用于活塞杆密封的热流体润滑模型。以活塞杆内行程为例,研究了液压润滑剂的边界效应和非牛顿效应对密封件流体润滑模型油膜压力分布的影响,并与不考虑边界效应的牛顿流体润滑模型的油膜压力分布进行了比较。结果表明:对于活塞杆往复密封,在研究的工况范围内,边界效应和非牛顿效应对油膜压力分布都有一定的影响。相对滑动速度较高、油膜厚度较薄时边界效应对油膜压力分布的影响较大;特征剪应力较小时非牛顿效应较明显。     

双正交提升小波在非对称表面形貌分析中的应用

由平顶珩磨获得的表面形貌是非对称的、多尺度的,而传统滤波函数处理这类表面形貌时存在畸变效应.利用双正交小波的优点,使用提升方案,采用边界对称延拓策略,解决了传统滤波函数在突变处和边界处的畸变效应,并以缸套内表面为例,选用bior4.4双正交小波,证明了提升双正交小波在表面形貌分析中的改善作用.     

HHT端点效应的最大Lyapunov指数边界延拓方法

针对HHT(Hilbert-Huangtransfrom)的端点效应问题,提出基于最大Lyapunov指数预测模型的HHT边界延拓方法.该方法通过相空间重构,并利用时间序列相似点的演化行为,采用最大Lyapunov指数预测模型来对时间序列的端点进行预测,有效避免了不同边界条件的三次样条插值和Hilbert变换频谱泄露对...     

光纤闭环液位控制系统

研制一种利用光纤的闭环液位控制系统,光纤探针是由两根多模光纤焊接在一起形成的,光纤探针边界处的光线对周围介质的折射率敏感,系统使用两个光纤探针将液位控制在相应的范围内,设计的液位控制系统很好地解决了液滴效应带来的延迟问题。     

基于沉浸边界法的鱼体自主游动数值仿真

沉浸边界法是一种通过在流场中加入一个虚拟边界的方法实现壁面的无滑移效应的有限差分法,而虚拟边界是通过计算反馈力的方法得到。陈述了基于沉浸边界法的一种数值计算方法,并且利用这种数值方法对固定及简谐振动圆柱绕流进行了数值仿真,并将计算所得到的压力、涡量云图、流线以及阻力系数与文献进行对比,结果较为符合,验证了数值算法的可靠性;对于雷诺数Re=2500下摆动频率为2Hz的鱼体进行了自主游动数值仿真,得到稳定平均速度在1.35倍体长左右,推进效率η=76.4%。     

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.

     

On the influence of the characteristics of flow on pressure distribution around building models with a view to simulating the minimum height of the atmospheric boundary layer

Results of an investigation of the influence of the characteristics of flow on pressure distribution around building models are reported. The influence of the mean velocity profile, turbulence intensity, percentage boundary layer immersion ratio and the building model's aspect ratio on the pressure distribution was studied with the view of simulating the minimum height of the atmospheric boundary layer in a wind tunnel for building aerodynamics investigations. It is cautiously suggested that atmospheric boundary layer height of at least three times the building height should be simulated in the wind tunnel. Turbulence characteristics exercise primary influence on the flow around models and shear exercises secondary influence on the flow. Finally, it is imperative to simulate the correct turbulence intensity and scale in the simulated turbulent boundary layer. However, further tests should be carried out to study these problems in closer detail.     

典型窄基输电塔风致响应气弹模型风洞试验

首先,采用离散刚度法,设计制作了典型窄基输电塔气动弹性模型;然后,通过大气边界层风洞试验,对窄基输电塔不同高度及风向下的位移、加速度响应特性进行了测试分析;最后,基于风洞试验结果计算了窄基输电塔风振系数并与规范结果进行了比较。结果表明,窄基输电塔位移均值响应主要为顺风向;顺、横风向脉动位移、加速度响应值都较大,随风向变化不明显,呈上下波动趋势;高度变化对脉动位移和加速度的响应影响略有不同。此外,根据中国荷载规范给出的输电塔横担处的风振系数值大于本次试验结果。     

On characteristics of flow around building models with a view to simulating the minimum fraction of the natural boundary layer

The results of an investigation of the characteristics of the flow around building models in terms of the various stagnation points are reported. The influence of the mean velocity profile, turbulence intensity, percentage boundary layer immersion ratio and the building model's aspect ratio on the location of the various stagnation points was studied from the point of view of simulating the minimum fraction of the atmospheric boundary layer in a wind tunnel for building aerodynamics investigations. It is suggested that the atmospheric boundary layer height of at least two to three times the building height should be simulated in a wind tunnel for studying the effects of strong and gusty winds on buildings and structures.     

Modal parameter identification in atmospheric turbulence excitation flutter test based on Hilbert-Huang transform

In flutter tests, particularly in wind tunnel experiments, the aircraft model is generally excited by atmospheric turbulence, which increases the difficulty in precisely identifying the modal parameters. To estimate the modal parameters under turbulence excitation for flutter boundary prediction, a technique was developed and evaluated depending on the Hilbert-Huang transform in this paper. The results of simulated flutter cases show that the developed technique can identify modal frequencies more precisely than the modal damping ratio, while the estimation of the modal damping ratio is quite good. Finally, in a wind tunnel flutter test, good flutter boundaries were predicted in advance by using the modal parameters identified from the turbulence response at low airspeeds.

     

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。     

The difference in the uplift force at each support point of a container crane between FSI analysis and a wind tunnel test

We analyzed the difference between FSI (fluid-structure interaction) analysis and a wind tunnel test regarding the uplift force at each support point of a container crane and also design stowing devices — a tie-down rod and a stowage pin — and an alarm system to prevent overturning of a container crane under wind loads. We know that FSI analysis agrees more with wind tunnel tests than with structural analysis, but the results of FSI analysis are different from those of the tests. To evaluate the effect of the wind load on the stability of the crane, two container cranes that are widely used in container terminals-50 ton-class and 61 ton-class container cranes-are adopted for the analytic model and 19 values are considered for the wind direction as the design parameter. First, a wind tunnel test for the reduced-scale container crane model is performed according to the wind direction using an Eiffel-type atmospheric boundary-layer wind tunnel. Next, FSI analysis for a full-scale container crane is conducted using ANSYS and CFX. Then, the uplift force obtained from FSI analysis is compared with that yielded by the wind tunnel test. Finally, a formula is suggested to compensate the difference between FSI analysis and the wind tunnel test.     

激光片光浓度场测量系统及其在风洞模拟中的应用

为在大型环境风洞中模拟大气污染物迁移扩散状况,开发出污染物浓度激光片光测量系统和污染物发放系统。基于激光片光浓度场测量系统,风洞模拟得到城市环境下点、线和面源污染物的扩散分布图案。基于风洞试验工况的边界条件,计算流体动力学(CFD)仿真得到污染物扩散分布,CFD仿真结果和激光片光浓度测量结果,两者定性一致,达到了相互印证的效果。将研究开发的激光片光浓度场测量系统和定量采样方法相结合,有望实现风洞试验中污染物浓度场的定量测试。     

超长斜拉索风阻系数及风雨激振的试验研究

结合主跨为1088m的世界最大跨度斜拉桥苏通大桥,对拉索的抗风问题进行了系统的研究。通过横桥向、顺桥向拉索风阻系数的风洞测量试验,得到了光索、螺旋线及压痕凹坑3种表面情况拉索的风阻系数;并模拟人工降雨,在风洞中重现了拉索的风雨激振现象,研究了风速、降雨量、拉索表面情况以及机械阻尼对风雨激振的影响。结果表明,拉索的阻力系数与表面情况、倾角、Re数密切相关,螺旋线、压痕凹坑及机械阻尼均可有效抑制拉索风雨激振现象。本文的试验方法及结果为超长斜拉索抗风研究提供了有益的参考。     

风洞喉道可调中心体机构分析与设计

第二喉道在跨超声速风洞中具有重要作用,中心体式第二喉道作为其中一种重要的结构形式近年来国外已开展了大量研究。本文以跨声速风洞第二喉道中心体机构的设计为背景,从偏置曲柄滑块机构原理入手,结合0.3 m风洞第二喉道可调中心体机构的结构特点,创新性地运用了对称偏置双曲柄滑块机构,并对其进行了运动学和动力学分析。风洞运行结果表明:该机构具有良好的气动性能,结构形式合理可靠。