冰雪运动雪上摩擦学与雪蜡研究现状

冬奥冰雪运动摩擦阻力影响运动健儿成绩,减少滑雪板与雪面之间摩擦阻力,有助于提升滑雪时的行进速度,提高运动员成绩排名. 研究冰雪表面摩擦学,有助于认识冰雪表面水润滑机理,为设计高性能滑雪板和雪蜡材料提供相关的研究基础. 因此,本文作者从冰雪表面摩擦学开始,简要介绍冰雪表面水润滑机理及影响冰雪表面摩擦学性能的影响因素,如环境参数(运动环境的温度/湿度)、雪基参数(雪面硬度、密度,雪面温度/湿度、冰晶大小、雪面污染物)、滑雪板基底参数及雪蜡的使用等;着重介绍了滑雪运动必备的材料-滑雪板减阻蜡的作用和分类,含氟雪蜡对人员环境的危害,雪蜡的选择与打蜡方式对雪板减阻性能的影响以及国内外现有的冰雪摩擦测试装置. 最后,对我国现有冰雪摩擦学基础研究,冰雪运动摩擦学及雪蜡材料的应用开发研究提出了几点建议和期望.      

固定鸭舵双旋弹全弹道动态稳定性及其影响因素

为研究固定鸭舵双旋弹全弹道飞行时的动态稳定性问题,在小攻角条件下建立复攻角运动的状态空间模型,并应用霍尔维茨方法导出其特征根实部皆负的一般性条件.针对起控前/后前体滚转角的运动特点,利用常规旋转弹的稳定性分析方法,建立固定鸭舵双旋弹在不同飞行状态下的动态稳定性判据,其与常规旋转弹的形式相似,无控飞行时在升力和静力矩项中对应增加了舵面控制力和力矩项;有控飞行时进一步增加了有关项相对增量的影响.据此在后体参数确定的条件下推导舵面参数约束条件,并分析操纵舵控制力系数导数、安装位置和舵偏角对动态稳定性的影响,揭示了该类炮弹动不稳定形成的原因.对复攻角运动在不同条件下的仿真分析结果表明,当舵面引起的有关项相对增量同时位于无控和有控飞行的边界曲线内时,固定鸭舵双旋弹全弹道飞行动态稳定,验证了本文推导的动态稳定性判据和舵面参数约束条件合理,为该类炮弹的研制提供了理论依据与设计参考.     

非旋转钝锥高超声速双平面拍摄风洞自由飞试验

在高超声速下(6 马赫) 开展了双平面拍摄风洞自由飞试验,对非旋转钝锥在小攻角下的运动特性和圆锥摆动问题进行了研究. 试验结果表明,虽然只预置了攻角而无侧滑角,模型仍然全部出现了圆锥摆动,且在观察窗范围内侧滑角幅值均大于攻角幅值. 模型角运动虽均处于小于10° 的小攻角和小侧滑角状态,但阻尼力矩项呈现较为明显的非线性,而静力矩项的非线性较弱,近似为线性. 5 组实验中,有1 组模型的角运动可能趋于极限平面运动或者是攻角幅值较小的极限圆锥运动,另外4 组试验模型角运动显示出了趋于极限圆锥运动的趋势. 尾端盖对模型的角运动影响不明显,而尾部对称布置的片条状凸起物对整个角运动幅值变化的稳定性存在明显影响,有凸起物的两组模型角运动幅值波动明显较小.      

微液滴在PDMS软基体表面的动态摩擦行为研究

通过固液界面摩擦力测试装置研究了微液滴在PDMS软基体表面运动时的动态摩擦学行为,并对微液滴体积、滑动速度及软基体力学性能对固液界面动态摩擦行为的影响进行了分析. 结果表明:微液滴在软基体表面运动时表现出最大静摩擦力和动态摩擦力. 最大静摩擦力与微液滴黏度和速度梯度呈正比,动态摩擦力与微液滴体积、滑动速度和基体力学性能有关. 随着微液滴体积的增加,三相接触线长度增加,动态摩擦力增加;随着相对滑动速度增加,三相接触线长度及接触角滞后增加,动态摩擦力增加;随着软基体弹性模量降低,固液界面黏附力增加,固液界面运动能量耗散增加,动态摩擦力增加. 研究结果可为PDMS软基体表面微液滴的精确驱动和运动参数优化提供理论指导,也可进一步丰富固液界面摩擦理论.      

考虑系留点垂向运动的飞艇系缆响应特性分析

为研究考虑系留点垂向运动的飞艇系缆的面内运动响应特性,将运动的飞艇作为系缆的边界条件处理,对系缆下端的系留点受到垂向激励时的系留飞艇系缆的运动状态进行了数值模拟,研究了系缆的动张力、运动情况。分析了飞艇攻角、系缆线密度等参数对系统的影响。研究结果表明:当系留点竖向简谐运动时,系缆上各点都做近似的简谐运动,在不同的线密度和攻角参数下,系缆各点的法向振幅分布不同,系缆可能处于二阶的振动状态;且随着系缆密度和攻角的增大,切向振幅增大,法向振幅减小;系留点激励还引起整个系统偏离平衡位置,这会引起飞艇动态高度的降低,在系留飞艇的高度控制中会有一定的影响。以上研究结果可为系留在舰船等运动中平台上的飞行器控制和系缆设计提供参考。     

一种基于坐标系级联的攻角探测方法

攻角作为描述弹体飞行状态的重要参数,是外弹道测试的重要内容之一。针对制导炮弹空中飞行时直接探测弹丸攻角相对较为困难的问题,提出了一种基于坐标系级联的弹丸攻角探测方法。该方法以弹用MINS/GNSS组合导航参数的输出为基础,建立了弹丸攻角的探测模型,采用坐标系级联的方式实现了弹丸攻角的最优估计。某型精确制导炮弹的数值仿真结果表明:采用本文提出的攻角探测方法得到的攻角估计误差分布在0.7°,并且MINS/GNSS组合导航系统姿态输出精度以及各个传感器测量精度的提高均有助于弹丸攻角的最优估计。该方法是一种在不需要增加额外探测设备的基础上实现弹丸攻角最优估计的有效方法,可以为弹丸攻角探测的实际工程应用提供新思路。     

高超声速自适应激波针数值研究

针对传统的与钝体轴线共线安装的固定式激波针方法在有攻角状态所存在的问题, 在前人工作基础上得到一种新型高超声速飞行器减阻/降热方法------自适应激波针方法. 将该方法应用于三维高超声速轴对称钝锥外形以及扁平楔外形, 并采用数值模拟的方法对其进行了概念验证. 在0○~120○攻角范围内, 对不同L/D参数的激波针外形流场以及前缘壁面的压力、热流分布等进行了对比分析. 结果表明, 这种新型自适应激波针方法无论在无攻角还是有攻角状态, 均可有效降低高超声速飞行器头部壁面的压力和热流, 可以有效解决传统激波针方法在较大攻角情况状态下失效的问题.      

基于格子Boltzmann方法的粘弹性流体圆柱绕流分析

将光滑界面法引入到格子Boltzmann方法中分析粘弹性流体绕流问题,分别采用单松弛模型和对流扩散模型求解运动方程和Oldroyd-B本构方程,针对圆形和椭圆内部边界条件,给出连续界面插值函数,在此基础上,运用光滑界面法将内部边界转换为作用力项施加到演化方程中。首先分析圆柱绕流问题,给出不同材料参数情况下的流场分布和阻力系数计算结果,比较发现与宏观数值模拟结果相吻合。将模型拓展到绕椭圆流动中,分析椭圆形状和材料参数对粘弹性流体绕柱流的影响,发现随着椭圆长轴与短轴比值的增加和维森伯格数的增加,阻力系数逐渐下降,并且长短轴比对迭代收敛有较大影响。     

多场耦合求解非线性气动弹性的研究综述

非线性气动弹性分析中,涉及到非线性流体动力学和非线性结构动力学的耦合问题.阐述了国内外应用计算流体动力学(computational fluid dynamics,CFD)/计算结构动力学(computational structural dynamics,CSD)耦合求解技术来处理非线性气动弹性问题的研究现状,全面分析了流体域和结构域的非线性特征模拟技术、高效网格运动策略、耦合界面相容性条件、耦合计算效率及降阶技术、气动弹性实验及算法验证、多学科耦合求解等关键技术,总结了相关最新研究的方法和成果, 对比分析了其优缺点并提出了展望.      

两栖UAV滑跳动力学特性仿真研究

基于空气动力学、势流理论和二元平面滑行理论,建立了两栖UAV入水滑跳动力学模型,重点对两栖UAV入水滑跳动力学特性进行了分析,并研究了多种入水条件对滑跳状态的影响.结果显示:(1)两栖UAV触水瞬间,姿态出现明显变化,UAV出现瞬时剧烈抬头趋势;(2)两栖UAV入水攻角增大,会造成UAV较大的沾湿深度和较短的滑水时间;...     

SKI VIBRATIONS AND DAMPING

Skis and runners sliding on snow like to vibrate. Soft snows tend to dampen ski vibrations but icy surfaces often set up severe oscillations. A feedback situation, such as driving on a gravel road, may also exist since vibrating skis create washboard conditions. Skis are subject to a range of forcing functions from low frequencies in big moguls (bumps) to 200–300 Hz frequencies at high speeds on icy surfaces. Analysis is complicated by random inputs, nonprismatic and anisotropic structures, and varying suspension systems.     

基于POD和代理模型的静气动弹性分析方法

静气动弹性问题考虑弹性结构与定常气动力间的相互耦合作用,对飞行器的性能和安全具有显著的影响.在现代飞行器设计阶段,计算流体力学(CFD)/计算结构力学(CSD)直接耦合方法是精确考察静气动弹性影响的重要手段.然而,基于CFD技术的气动力仿真手段在耦合过程中计算量大且耗时长,难以满足设计阶段的需求.因此,为了兼顾计算精度与效率,文章采用本征正交分解(POD)和Kriging代理模型相结合的模型降阶方法,替代CFD求解过程并耦合有限元分析(FEA)方法,建立了高效、准确的静气动弹性分析框架.相较于传统的以模态法为主的静气动弹性分析方法,该方法能够解决更为复杂的静气动弹性问题以及提供静气动弹性变形过程中的气动分布载荷.针对典型三维跨声速HIRENASD机翼模型开展的马赫数、迎角变化的算例验证表明:由建立的静气动弹性分析方法与CFD/CSD直接耦合方法计算得到机翼翼梢处的静变形量间的相对误差在5%以内;同时该方法预测静平衡位置处的气动分布载荷的误差在5%以内,静气动弹性分析的计算效率至少提升了6倍.     

Finite element modeling of interfacial forces and contact stresses of pneumatic tire on fresh snow for combined longitudinal and lateral slips

Significant challenges exist in the prediction of interaction forces generated from the interface between pneumatic tires and snow-covered terrains due to the highly non-linear nature of the properties of flexible tires, deformable snow cover and the contact mechanics at the interface of tire and snow. Operational conditions of tire-snow interaction are affected by many factors, especially interfacial slips, including longitudinal slip during braking or driving, lateral slip (slip angle) due to turning, and combined slip (longitudinal and lateral slips) due to brake-and-turn and drive-and-turn maneuvers, normal load applied on the wheel, friction coefficient at the interface and snow depth. This paper presents comprehensive three-dimensional finite element simulations of tire-snow interaction for low-strength snow under the full-range of controlled longitudinal and lateral slips for three vertical loads to gain significant mechanistic insight. The pneumatic tire was modeled using elastic, viscoelastic and hyperelastic material models; the snow was modeled using the modified Drucker-Prager Cap material model (MDPC). The traction, motion resistance, drawbar pull, tire sinkage, tire deflection, snow density, contact pressure and contact shear stresses were obtained as a function of longitudinal slip and lateral slip. Wheel states - braked, towed, driven, self-propelled, and driving - have been identified and serve as key classifiers of discernable patterns in tire-snow interaction such as zones of contact shear stresses. The predicted results can be applied to analytical deterministic and stochastic modeling of tire-snow interaction.     

Aerodynamics of ski jumping: experiments and CFD simulations

The aerodynamic behaviour of a model ski jumper is investigated experimentally at full-scale Reynolds numbers and computationally applying a standard RANS code. In particular we focus on the influence of different postures on aerodynamic forces in a wide range of angles of attack. The experimental results proved to be in good agreement with full-scale measurements with athletes in much larger wind tunnels, and form a reliable basis for further predictions of the effects of position changes on the performance. The comparison of CFD results with the experiments shows poor agreement, but enables a clear outline of simulation potentials and limits when accurate predictions of effects from small variations are required.     

Validation of CFD‐CSD coupling interface methodology using commercial codes

Coupling interface between computational fluid dynamics (CFD) and computational structural dynamics (CSD) is required to provide exchange of information for the simulation of fluid–structure interaction (FSI) phenomena. Accuracy and consistency of information exchanged through coupling interface between the independent CFD and CSD solvers plays a central role in the simulation and prediction of FSI phenomenon, like flutter. In this paper validation of an implemented coupling interface methodology is presented for subsonic, transonic and near supersonic mach regime. The test case chosen for this purpose is the flutter of AGARD445.6 standard I‐wing weakened model configuration for subsonic to near transonic flow regime. Gambit^® and Fluent^® are used for CFD grid generation and solution of fluid dynamic equations, respectively. CSD modeling and simulation are provided by numerical time integration of modal dynamic equations derived through the finite element modeling in ANSYS^® environment. Copyright © 2009 John Wiley & Sons, Ltd.     

基于误差马尾图量化爆轰数值模拟结果的置信度

针对爆轰流体力学数值模拟过程中输入参数的不确定性, 通过抽样技术, 形成确定性爆轰流体力学程序的各种输入和数值求解, 建立输入参数与输出响应量的样本, 再通过概率框架下的误差累积分布函数与马尾图, 给出了爆轰数值模拟过程中输入参数不确定度对模拟结果影响的置信度量化方法。通过一维黎曼问题、平面爆轰问题计算了误差马尾图, 给出了二维爆轰拉氏自适应流体动力学LAD2D程序计算网格与模拟结果置信度的关系, 对多物理爆轰过程发展高置信度数值模拟软件有很好的借鉴作用。     

Direct numerical simulation of a freely decaying turbulent interfacial flow

Whereas Large Eddy Simulation (LES) of single-phase flows is already widely used in the CFD world, even for industrial applications, LES of two-phase interfacial flows, i.e. two-phase flows where an interface separates liquid and gas phases, still remains a challenging task. The main issue is the development of subgrid scale models well suited for two-phase interfacial flows. The aim of this work is to generate a detailed data base from direct numerical simulation (DNS) of two-phase interfacial flows in order to clearly understand interactions between small turbulent scales and the interface separating the two phases. This work is a first contribution in the study of the interface/turbulence interaction in the configuration where the interface is widely deformed and where both phases are resolved by DNS. To do this, the interaction between an initially plane interface and a freely decaying homogeneous isotropic turbulence (HIT) is studied. The densities and viscosities are the same for both phases in order to focus on the effect of the surface tension coefficient. Comparisons with existing theories built on wall-bounded or free-surface turbulence are carried out. To understand energy transfers between the interfacial energy and the turbulent one, PDFs of the droplet sizes distribution are calculated. An energy budget is carried out and turbulent statistics are performed including the distance to the interface as a parameter. A spectral analysis is achieved to highlight the energy transfer between turbulent scales of different sizes. The originality of this work is the study of the interface/turbulence interactions in the case of a widely deformed interface evolving in a turbulent flow.     

薄膜结构流固耦合的CFD数值模拟研究

基于弱耦合分区求解策略,在CompaqVisualFortran6．5环境下搭建了薄膜结构三维流固耦合效应的CFD数值模拟平台。程序采用模块化编程思想,主要包含几何建模、流体分析、结构分析和数据交换四个模块。其中几何建模模块采用自行编制的膜结构找形分析程序,流体分析模块采用经过二次开发的计算流体力学软件FLUENT6．0,结构分析模块采用自行编制的膜结构动力分析程序MDLFX;在数据交换模块中,编制了基于薄板样条法的插值计算程序,以实现流固交界面上不同区域网格间的数据传递问题,编制了基于代数法和迭代法的动网格变形程序,以实现流固耦合运算中的动网格更新。基于该软件平台,对单向柔性屋盖和鞍形膜结构屋盖进行了流固耦合数值模拟,验证了方法的有效性。     

Study of airflow in a cold-region tunnel using a standard k − ε turbulence model and air-rock heat transfer characteristics: validation of the CFD results

An efficient computational fluid dynamics (CFD) method for simulating the flow and convective heat transfer process of airflow in a tunnel is required to analyze the freezing and thawing of surrounding rock and to apply the results to the design of the insulation layer for a tunnel located in a cold region. Comparisons of experimental data and CFD results using a standard k ? ε turbulence model, a wall function, a thermal function and an adaptive finite element method are presented. Comparison of the results indicated that the proposed model and simulation method are efficient at determining the solid–air interface heat coefficient in a thin and infinitely wide horizontal plate and the hydrodynamic and thermal fields in a 3-D cavity. After demonstrating that the necessary validations are satisfied, this paper presents an analysis of the characteristics of airflow and air–rock heat transfer in a cold-region tunnel.