Orientation and Motion of Water Molecules at Air/Water Interface

Here we report a quantitative study of the orientational structure and motion of water molecule at the air/water interface. Analysis of Sum Frequency Generation （SFG） vibrational peak of the free O-H stretching band at 3700 cm^-1 in four experimental configurations showed that orientational motion of water molecule at air/water interface is libratory within a limited angular range. The free OH bond of the interracial water molecule is tilted around 33°from the interface normal and the orientational distribution or motion width is less than 15°. This picture is significantly different from the previous conclusion that the interracial water molecule orientation varies over a broad range within the ultrafast vibrational relaxation time, the only direct experimental study concluded for ultrafast and broad orient, ational motion of a liquid interface by Wei et al. （Phys. Rev. Lett. 86, 4799, （2001）） using single SFG experimental configuration.

Research on characteristics of water motion and influencing factors for the flexible air chamber jig body

The air bag deformation data were obtained by high-speed dynamic videos experiments. Based on gas–liquid flow VOF model, dynamic mesh technique and deformation data, numerical simulations for different structure models were achieved, and the law of water motion and influencing factors were analyzed.The results show that the flow in the length direction of the jig is smooth, and second pulsation appears in the separation time and forms the secondary separation. The installation position of screen and the number of air bags have a great influence on the uniformity of flow and velocity. The screen height cannot be too low to avoid forming the unstable flow. At the same time, the screen height cannot be too high, otherwise water velocity will be too small and was unable to provide enough power. At the height of 1.4m,velocity unevenness is minimum and the best uniform flow can be obtained. Compared with double air bags, there are the following features of single air bag: water flow is not smooth, the time achieving the maximum velocity is too long, maximum velocity is smaller, and overall effect is worse than double air bags.

A motion correction on direct estimations of air-sea fluxes from a buoy

A flux system deployed on a moored buoy has been described, which is capable of directly estimating the airsea fluxes after removing the contamination in the signal due to buoy motion. A triple loop fitting method has been demonstrated for determining the three angular offsets between measurement axes of the sonic anemometer and motion pack. The data collected in an experiment in the Northern Huanghai Sea is used to correct the three sonic anemometer measurements of turbulent wind for buoy motion. The effective removal of wave-scale motion from the spectra and cospectra are demonstrated. Estimates of along-wind momentum flux, sensible heat flux and latent heat flux calculated by the eddy correlation method based on data obtained by sonic anemometer 81000V are shown to be in the same trend and scale with those determined by the bulk aerodynamic method after motion correction. The motion correction not only greatly improve the estimation of the momentum flux but also has a great impact on the calculated sensible heat flux.

Study of the Motion of a Weighted Cotton Ball in an Air Stream with a Known Impact Trajectory

In the cotton factories ginning process bales of raw cotton in cotton tube transporting through the air has written in the article. As a result, cotton with cotton in the air separated by a separator device with air traffic, has an important theoretical study. First of all, the air flow that affects the dynamic pressure and laws is based on the model established in this study and the results are obtained.

侧面爆破粉尘时空分布模拟分析

从开放性细颗粒物污染治理角度出发,建立建筑物拆除爆破产尘的几何计算模型,运用计算流体力学(CFD)工具,对给定环境风速下的建筑物周围压力场和速度场进行了模拟分析,并对侧面折叠爆破粉尘按R-R(Rosin-Rammler)分布,使用气流-粒子双向耦合的DPM模型研究了爆炸粉尘的时空分布。结果表明,下风侧因建筑物存在导致风速、压力急剧变化而产生涡流,涡流是影响爆破粉尘时空分布的关键因素之一。在时间上,爆破粉尘有气流拖曳运动状态和扩散态;在空间上,因重力作用致下部空间的粉尘浓度较大。

大跨度钢桁架隔震结构隔震性能及影响规律分析

由于大跨空间结构竖向振动问题突出,水平隔震支座难以有效控制结构的竖向地震响应。将摩擦摆水平隔震支座和空气弹簧-摩擦摆三维隔震支座应用于大跨度钢桁架中,分析钢桁架水平隔震结构和三维隔震结构的隔震控制效果。结果表明,水平隔震和三维隔震均延长了结构自振周期,隔震后一阶振型为上部桁架结构沿水平方向的整体平动。时程分析显示,在普通地震动、近断层脉冲型地震动和远场长周期地震动作用下,水平隔震支座对桁架水平和竖向节点峰值加速度的平均隔震率分别为43.4%和9.2%,三维隔震支座对桁架水平和竖向节点峰值加速度的平均隔震率分别为43.8%和24.4%,水平隔震支座和三维隔震支座对桁架峰值等效应力的平均隔震率分别为4.2%和17.7%。水平隔震支座和三维隔震支座对桁架水平地震响应控制效果基本相同,三维隔震支座对结构的竖向地震响应控制效果更好。

考虑轴颈倾斜与空泡运动的径向滑动轴承油气润滑分析

由于重载作用及制造误差而导致的轴颈倾斜现象会改变轴承不同截面处的偏心率及油膜厚度,滑动轴承高速运转时,油膜间隙中会不可避免地混入微小气泡,因此探究轴颈发生倾斜时油气两相流对径向滑动轴承润滑特性的影响很有必要。将考虑空泡运动的、修正后的Rayleigh-Plesset(mRPS)方程与雷诺方程共同联立,通过编写相应算法求解耦合后的方程,分析含气率、气泡参数以及轴颈倾斜程度对滑动轴承静特性参数的影响。结果表明:在不同转速下,随着含气率的增加,最大油膜压力、承载力、端泄流量、摩擦力等静特性参数呈下降趋势;气泡参数对润滑性能的影响与偏心率有关,增大气泡的表面膨胀黏度与减小初始气泡半径对轴承润滑会产生相同的效果;轴颈倾斜会改变油膜压力分布及数值大小,同时使空化区域发生倾斜;随着轴颈倾斜程度的增加,滑动轴承静特性参数逐渐增大,且在大偏心率大倾斜度时更为显著;适当改变气泡参数与油液含气率会在一定程度上削弱由轴颈倾斜带来的影响。

蝴蝶飞行机理及仿蝴蝶扑翼飞行器研究进展综述

仿生扑翼飞行器具有高机动性、高隐蔽性以及高效率等突出优势,在军事侦查、探险搜救等领域具有较好的应用前景,而其应用的基础是对生物飞行机理的深入探究.随着先进运动观测和实验技术的引入,对昆虫飞行行为的记录和分析更为便捷和准确.研究表明常见的昆虫拍打频率较高,在25~400 Hz之间,而蝴蝶较为特殊,其扑打频率较低,大约为10 Hz,对于蝴蝶的许多独特的飞行技能尚缺少足够的认识.蝴蝶前翼和后翼的翼面积都较大,身体同侧的前后翼几乎为同步拍打,且扑打幅度较大,甚至接近180°.蝴蝶飞行中身体有较大幅度的上下和俯仰震荡,翼和身体运动高度耦合.即便如此,蝴蝶仍具有敏捷的飞行能力,可以达到点对点的飞行目标,甚至上千公里的长途迁徙,是优秀的仿生学研究对象.因此,蝴蝶启发的仿生扑翼飞行器也得到了全世界研究人员的关注.蝴蝶的飞行机制相对于其他昆虫更加特殊,飞行行为和气动特性更为复杂,这使得仿蝴蝶扑翼飞行器的研制更加困难.目前对于仿蝴蝶飞行器的研制大多数对蝴蝶翼–身耦合的机理进行了简化,很少能实现受控的稳定飞行.最后,本文梳理了真实蝴蝶的飞行行为特点和飞行机理,指出了仿蝴蝶扑翼飞行器研制的关键技术,总结了该类飞行器未来的发展方向和应用前景.

基于实时数据采集的摆动力学综合实验

在单摆实验基础上,利用转动传感器设计了摆运动的综合实验。准确测量摆动过程中摆角、摆动角速度随时间变化状态,研究了小角度摆动情况下摆球的实时运动状态,验证了单摆小角度摆动的简谐运动,并通过数据拟合准确测定本地重力加速度为9.77 m/s^(2),百分误差仅为0.22%;同时,研究了大角度摆动时摆球的欠阻尼运动,并测定了摆动过程的空气阻尼系数为0.00224 s^(-1)。该方案通过瞬时量的测量实现了多个动力学知识点的探究,能够有效促进学生对相关知识的理解,激发学生探究运动过程中物理量变化规律的热情。

IMotion变速运动控制在空调中的应用

本文概要介绍了IR公司最新开发的iMotion变速运动控制芯片IRMCF312的结构和特性,并结合空调系统的具体应用需求,提出了一套完整的以此芯片为主控制芯片的空调系统从硬件到软件的设计,进而体现了iMotion运动控制芯片的优势所在。

气浮垫的误差均化能力研究

为探究小孔节流气浮轴承的误差均化能力的主要影响因素,建立单个气浮垫的误差运动模型,并利用所定义的均化系数研究气浮垫误差运动、导轨条形状误差和气浮垫结构参数三者之间的定量关系。研究表明:对于长波长的导轨条形状误差(波数为0~1),当波数逐渐增加时,均化系数从1逐渐降低到接近0;对于短波长的导轨条形状误差(波数为1~10),当波数靠近或者等于正整数时,均化系数取接近于0的最小值;当波数靠近或者等于正整数加0.5时,均化系数取小于0.25的局部最大值;结构参数中,封气边宽度对误差均化能力有很大影响,气垫间隙和小孔节流器孔径对误差均化能力基本无影响;当移动速度小于10 000 mm/s时,移动速度对误差均化能力的影响微弱。

机制砂风选中砂粒运动轨迹简化计算模型

随着我国建筑行业对机制砂的需求正在不断增长,以及机制砂行业的持续发展,对于提高砂石粒径级配的要求也在随之提高。机制砂在风选中的运动规律的研究,是机制砂风选设备结构设计与风速设计的基础,对提高风选分级效果具有重要的意义。该文以机制砂风选中砂石骨料运动规律为研究对象,通过理论分析对机制砂颗粒在风选中的运动轨迹进行研究,建立砂石颗粒风选运动数学模型,使用Matlab软件对该模型进行计算。结果表明,砂石颗粒粒径、气流速度、风口高度等因素明显影响最终的风选分级效果。

储气库压缩机宽工况气阀优选及运动规律仿真

以某储气库压缩机为研究对象,分析气阀结构及阀片材料性能,根据工况参数开展气阀的运动状态模拟,设计出阀片运动规律仿真可视化图形用户输入界面,实时显示计算结果及阀片运动模拟曲线,降低研究开发的成本,为储气库气阀可靠性设计提供参考。

20℃的静止空气中直径5 mm的雨滴的自由下落运动研究

文章采用球形雨滴模型,利用空气阻力系数C_(D)的较严格的表达式即Wallis公式,计算出直径5 mm的雨滴在20℃的静止空气中自静止开始自由下落时的v~t图像.文章又在C_(D)统一取作0.44的近似下,解出解析的、普适的v(t)函数,并作出相应的v~t图像.结果显示这两条v~t曲线几乎完全重合,这就意味着近似处理是完全合适的.文章解释了其中的原因,并指出实测极限速率比球形雨滴模型下的理论值小2.00 m/s的原因在于实际雨滴的形状呈现汉堡状,其实际的空气阻力系数经计算约为0.52.文章认为球形雨滴模型从总体上看是比较实用的.

客车舱门气弹簧选型设计与运动仿真

为了提高客车舱门气弹簧选型的设计质量、效率及可视性,文章采用三维软件进行客车舱门气弹簧的选型设计,通过作图法得到气弹簧的安装位置,然后理论计算确认该安装位置的舱门支撑力和关闭力满足设计要求。通过CATIA中的数字样机(DMU)模块的运用,实现气弹簧运动仿真,直观观测舱门开启角度、干涉情况等,从设计源头校核确认,保证气弹簧自锁有效。气弹簧三维选型设计与运动仿真分析的使用,提高了客车舱门气弹簧选型设计的效率与设计水平,在设计源头避免气弹簧选型不当导致舱门开启角度不对、舱门开启力度偏大或偏小、气弹簧寿命短等问题。

An Analysis on the Motion Characteristics of Fuel and Shell in Launching

The relative characteristics of motion of the fuel and shell upon launching is analyzed. By means of mechanical analysis and calculation, it is proposed that relative motion exists not only in the ranges between the fuel and shell of the warhead, but also in the fuel in different positions. The result of study indicates that the position of the fuel in the warhead has a marked influence on the relative motion, while the frictional coefficient between the fuel and shell has less influence upon it.

空天双基地雷达海杂波建模与分析

空天双基地雷达作为一种新兴的天基雷达体制,发射机置于卫星上,接收机采用飞行器,极大地克服了传统单基地天基雷达空间传输损耗过大的问题,但其杂波特性更加复杂。对空天双基地雷达海杂波特性进行了分析,首先分析了空天双基地雷达的几何构型,然后基于海杂波双基散射系数和运动特性因素构建了海杂波空时数学模型,最后结合理论与仿真结果阐释了空天双基海杂波特性,为空天双基地雷达杂波抑制技术研究提供了参考。

Some Characteristics of the Surface Boundary Layer of a Strong Cold Air Process over Southern China

In southern China, cold air is a common weather process during the winter season; it can cause strong wind, sharp temperature decreases, and even the snow or freezing rain events. However, the features of the atmospheric boundary layer during cold air passage are not clearly understood due to the lack of comprehensive observation data, especially regarding turbulence. In this study, four-layer gradient meteorological observation data and one-layer, 10-Hz ultrasonic anemometer-thermometer monitoring data from the northern side of Poyang Lake were employed to study the main features of the surface boundary layer during a strong cold-air passage over southern China. The results show that, with the passage of a cold air front, the wind speed exhibits low-frequency variations and that the wind systematically descends. During the strong wind period, the wind speed increases with height in the surface layer. Regular gust packets are superimposed on the basic strong wind flow. Before the passage of cold air, the wind gusts exhibit a coherent structure. The wind and turbulent momentum fluxes are small, although the gusty wind momentum flux is slightly larger than the turbulent momentum flux. However, during the invasion of cold air, both the gusty wind and turbulent momentum fluxes increase rapidly with wind speed, and the turbulent momentum flux is larger than the gusty wind momentum flux during the strong wind period. After the cold air invasion, this structure almost disappears.

Design, Development and Testing of an Air Damper to Control the Resonant Response of a SDOF Quarter-Car Suspension System

An air damper possesses the advantages that there are no long term changes in the damping properties, there is no dependence on working temperature and additionally, it has less manufacturing and maintenance costs. As such, an air damper has been designed and developed based on the Maxwell type model concept in the approach of Nishihara and Asami [1]. The cylinder-piston and air-tank type damper characteristics such as air damping ratio and air spring rate have been studied by changing the length and diameter of the capillary pipe between the air cylinder and the air tank, operating air pressure and the air tank volume. A SDOF quarter-car vehicle suspension system using the developed air enclosed cylinder-piston and air-tank type damper has been analyzed for its motion transmissibility characteristics. Optimal values of the air damping ratio at various values of air spring rate have been determined for minimum motion transmissibility of the sprung mass. An experimental setup has been developed for SDOF quarter-car suspension system model using the developed air enclosed cylinder-piston and air-tank type damper to determine the motion transmissibility characteristics of the sprung mass. An attendant air pressure control system has been designed to vary air damping in the developed air damper. The results of the theoretical analysis have been compared with the experimental analysis.

The Effect of Mass Ratio and Air Damper Characteristics on the Resonant Response of an Air Damped Dynamic Vibration Absorber

In this paper, it is shown that, a road vehicle 2DOF air damped quartercar suspension system can conveniently be transformed into a 2DOF air damped vibrating system representing an air damped dynamic vibration absorber (DVA) with an appropriate change in the ratio μ of the main mass and the absorber mass i.e. when mass ratio μ >> 1. Also the effect of variation of the mass ratio, air damping ratio and air spring rate ratio, on the motion transmissibility at the resonant frequency of the main mass of the DVA has been dis- cussed. It is shown that, as the air damping ratio in the absorber system increases, there is a substantial decrease in the motion transmissibility of the main mass system where the air damper has been modeled as a Maxwell type. Optimal value of the air damping ratio for the minimum motion transmissibility of the main mass of the system has been determined. An experimental setup has been designed and developed with a control system to vary air pressure in the damper in the absorber system. The motion transmissibility characteristics of the main mass system have been obtained, and the optimal value of the air damping ratio has been determined for minimum motion transmissibility of the main mass of the