基于多岛遗传算法的汽车车身气动优化

为研究不同长细比汽车车身的最优气动性能,基于英国汽车工业研究协会(Motor Industry Research Association, MIRA)阶背模型,利用多岛遗传算法开展不同长细比的汽车车身气动优化.优化结果表明优化模型的气动阻力因数随着长细比的增大而降低.通过改变车身的长细比得到的5种优化模型具有发动机罩倾角、后风窗倾角和尾部上翘角较大,前风窗倾角较小的特点.对8个优化参数进行分析可知：尾部上翘距离和前悬距离对气动特性的影响最大.     

底部导流板形式对高速列车气动阻力的影响

为减小高速列车运行时的气动阻力,设计直式、斜式、内圆弧式和外圆弧式等4种转向架前后底部导流板的高速列车模型.通过风洞试验验证数值模拟方法的有效性,采用数值计算分析底部导流板对列车气动阻力和底部流场的影响.结果表明：不同形式底部导流板的列车总阻力相差可达20%,其中头车气动阻力因数极差值最大为0.062.导流板影响列车底部气流速度和转向架区域压力分布,其导流作用使得转向架区域气动阻力和转向架的阻力同时改变.转向架前后导流板的导流效果越好,转向架区域的气动阻力越小;同时,气流冲击使得转向架上的滞止压力增大;在二者的共同作用下高速列车的总阻力存在一个较小值.底部采用直式导流板对降低全车气动阻力的效果最好.     

不同造型风格的车身低阻基本形体

针对低阻车身造型风格多元化的需求,结合数值模拟和遗传算法,考虑不同的约束条件,求解4种造型风格不同且气动阻力因数在0.087~0.100内的车身低阻基本形体,并用缩比模型的风洞试验验证该方法的可靠性.高尾车型低阻基本形体的气动阻力因数值比低尾车型的偏高约0.010;不同长高比车身的气动阻力因数变化趋势不同,应独立进行优化.凹形头部与凸形头部的低阻基本形体都有低且长的尾部,头部正压区总面积相近.     

Aerodynamic drag reduction on a realistic vehicle using continuous blowing

The aerodynamic drag reduction of a realistic vehicle model through continuous blowing was numerically analyzed based on the open-source computational fluid dynamics (CFD) program, OpenFOAM. Simulations were performed on a realistic passenger vehicle model with available wind tunnel test data, DrivAer, at four different Reynolds numbers (Re). The aerodynamic drag coefficient decreased with increasing Re. The CFD technique was validated by comparing the aerodynamic drag coefficients at Re = 4.87 × 10⁶. Predicted drag coefficients of the DrivAer estate model show less than 3% difference from wind tunnel test data, whereas those of fastback and notchback vehicles showed less than 1% difference. Sectional pressure distributions agreed well with wind tunnel test data. The effect of continuous blowing was investigated using the DrivAer estate model with a blowing position at the end of the roof for vertical blowing and at the C-pillar for lateral blowing. Simulations were performed at Re = 4.87 × 10⁶ and 9.75 × 10⁶ and blowing speeds of 20%, 40%, 60%, and 100% of the vehicle driving speed. The effect of continuous blowing increased with Re. The drag reduction was more than 6% for roof blowing due to increasing rear pressure when the blowing speed equaled the vehicle driving speed. The maximum drag reduction was approximately 7.5% for simultaneous roof and lateral blowing. The results indicate that continuous blowing can efficiently reduce vehicle aerodynamic drag and consequently greenhouse gas emissions.

     

静止和旋转孤立车轮局部流场的评价

为研究车轮周围流场特征,分别对某孤立车轮静止和旋转工况下周围流场进行数值研究,并给予试验验证.计算采用定常雷诺时均纳维斯托克斯方程.在1∶15的模型风洞中进行试验.数值模拟结果与试验数据吻合.针对数值模拟结果,详细分析静止和旋转孤立车轮周围流场的流动情况、表面压力因数、气动阻力因数和气动升力因数等,得到孤立车轮旋转对车轮附近局部流场的影响以及形成机理.车轮的转动使总体压差减小,降低气动阻力和升力,改善气动性能。     

A review of: “Computers,Work and Health”. By TREVOR A. WILLIAMS,Taylor & Francis, 4 John St,London WC1N 2ET (1988), pp. x + 142, £25·00. ISBN 0-85066-453-5

The effects of cabin noise on subjective comfort assessments were systematically investigated in order to reveal optimisation potentials for an improved passenger noise acceptance. Two aircraft simulation studies were conducted. An acoustic laboratory test facility provided with loudspeaker systems for realistic sound presentations and an aircraft cabin simulator (Dornier Do 728) with a high degree of ecological validity were used. Subjects were exposed to nine different noise patterns (three noise levels ranging from 66 to 78 dB(A) combined with three different frequency spectra). Regression analysis demonstrated a significant increase of passengers' acceptance with lower noise levels and significant effects of different frequency spectra determined by seat position in the aircraft cabin (front, middle, rear). Acoustic cabin design should therefore consider measures beyond noise level reduction altering noise characteristics to improve passengers' comfort and well-being in the aircraft cabin.

Practitioner Summary: To improve passenger comfort in the aircraft with respect to cabin noise, passengers' reactions to specific noise conditions were systematically investigated. Two laboratory studies showed significant dose-response relationships between sound pressure level and subjective comfort ratings which differed due to the noise at specific seat positions in the aircraft.     

动车组司机室空调蒸发器气动噪声数值仿真

为研究动车组司机室空调蒸发器的噪声响应，建立某型司机室分体式空调蒸发器的计算流体动力学模型，采用FLUENT中的大涡模拟（large eddy simulation, LES）计算瞬态气动流场。对瞬态流场数据进行傅里叶变换，得到空气流场的频域数据。基于流场频域数据，采用Virtual.Lab的边界元法计算蒸发器的气动噪声，采用声压法计算蒸发器的辐射声功率，并与测试结果进行对比分析。结果表明：蒸发器出口位置气动噪声最高，最大声压级高于56 dB；最大声功率级出现在125~400 Hz的低频段；声功率级随着频率的增加逐渐降低，但在5 000 Hz的高频辐射中声功率级仍然超过55 dB，这表明空调蒸发器气动噪声属于宽频噪声；计算结果与测试结果吻合良好，验证声压法计算空调蒸发器气动声功率可行。     

轿车乘员舱内气流对气动阻力影响的数值模拟

为揭示轿车侧窗开启程度和乘员舱内布置对气动阻力的影响规律,建立1∶1阶背式英国汽车研究协会(Motor Industry Research Association,MIRA)标准模型;基于FLUENT,在30 m/s风速下采用可实现k-ε湍流模型对不同侧窗开度的模型进行三维稳态数值模拟,得到气动阻力因数随侧窗开启程度的增大而增大的变化趋势.在侧窗全开时,改变舱内布置,得到气动阻力因数随假人个数的变化规律;对比不同情况下模型的流场分布发现,当考虑乘员舱内气流时,气动阻力的大小不仅与进气量有关,而且受舱内流场分布的影响.     

Investigation of flow structures involved in sound generation by two- and three-dimensional cavity flows

Proper Orthogonal Decomposition and Stochastic Estimation are combined to shed some light on the link between organized flow structures and noise generation by turbulent flows. Proper Orthogonal Decomposition (POD) is firstly used to extract selected flow events. Based on the knowledge of these structures, the Quadratic Stochastic Estimation of the acoustic pressure field is secondly performed. Both procedures are successively applied to two- and three-dimensional numerical databases of a flow over a cavity. It is demonstrated that POD can extract selected aerodynamic events which can be associated with selected frequencies in the acoustic spectra. Reconstructed acoustic fields also indicate the aerodynamic events which are responsible of the main energy of the noise emission. Such mathematical tools offer new perspectives in analysing flow structures involved in sound generation by turbulent flows and in the experimental design of a flow control strategy.     

基于偏最小二乘法的翼型稳健设计替代模型

翼型的稳健设计就是要实现翼型对外界噪声因素不敏感,使翼型实现性能高且稳定的目标。翼型设计经过了几十年的研究发展,目前常用的翼型稳健设计主要是采用风洞和数值模拟两种方式,但它们也分别有成本高和计算量大的不足。通过对建模方法进行研究,提出了一种基于偏最小二乘法（PLS)的翼型稳健设计方法,采用该方法对基准翼型RAE2822选取11个设计变量（10个外形设计变量和马赫数）进行稳健设计后将其与基准翼型的阻力系数进行对比。结果表明使用偏最小二乘法替代模型所获得的稳健翼型,其阻力系数的均值和方差较基准翼型分别减小了44%和82%,其气动性能更好且性能更加稳定。使用偏最小二乘法替代模型进行翼型稳健设计具有成本低,计算速度快的特点,且能满足基本的结果精度要求,具有实际的应用价值。     

基于扩展卡尔曼滤波的气动参数在线修正方法

提出了在风洞试验获取的气动参数的基础上对由各种误差和扰动引起的气动偏差进行修正的方法。采用扩展卡尔曼滤波算法,利用雷达获取在线飞行弹丸的一段飞行数据(位置和速度),使用已知的气动参数对飞行数据进行过滤得到气动参数的修正系数,对已知气动参数中的阻力系数和升力系数进行修正,为后段弹道计算提供更加精确的气动参数。通过仿真计算,验证了上述方法的有效性,并利用弹道外推计算,通过对比落点误差证明了上述方法的精确性,为气动参数辨识和弹道修正提出了新的途径。     

The implementation of a knowledge-based framework for the aerodynamic optimization of a morphing wing device

In the field of aerospace engineering currently a lot of research effort is directed towards the reduction of cruise drag of civil transport aircraft in order to reduce fuel burn, and hence environmental impact and costs. In order to reduce cruise drag, a promising method is under consideration by adjusting, or rather morphing the rear part of the aircraft’s wing during cruise flight. Given the premature state of knowledge of such a design implementation, a knowledge-based computational framework is developed. The purpose of this framework is to allow for an aerodynamic optimization of a section of the wing. The framework is set up in such a way that all relevant design knowledge generated in the process can be captured and used in a subsequent mechanical design process. In this fashion, the complex design process of a novel morphing wing device can be automated to a certain degree. This automation can be used to construct a large number of different feasible and optimized designs with varying boundary conditions of a complex experimental device.This article describes the initial 2-dimensional aerodynamic design step of the morphing device under consideration and how it is implemented in a knowledge-based optimization framework. It describes the initial stage of the development of this tool, as it will be expanded by a number of design steps that each adds more detail to the design in all relevant aspect fields (aerodynamic, structural, actuation, etc.). Ultimately, this tool will be used to obtain a thorough evaluation of a number of different proposed structural solutions and allow for a comparison between them.     

Helmholtz共振腔气动噪声数值仿真

为探究出一套完整、准确的气动噪声仿真方法,用FLUENT和Actran仿真Helmholtz共振腔旁接管道系统模型.针对流场仿真,采用六面体网格建模,分析选择合适的网格密度,明确网格及边界条件的影响,以获得准确的声源信息;运用Lighthill声类比方法对声场进行仿真,采用数值计算、传声损失仿真和气动噪声仿真计算等3种方法提取管道内部场点声压级频谱曲线,分析曲线峰值频率特征,包括共振频率分析和声模态分析等.采用CFD软件与声学仿真软件相结合的方法,可以有效进行流场和声场的仿真.     

考虑气动特性的汽车前照灯造型参数化方法

为研究汽车前照灯造型对汽车气动阻力的影响并指导车灯造型设计,提出一种车灯造型参数化方法.结合美学、考虑汽车空气动力学,在分析汽车前部和车灯造型的基础上,总结出车灯造型的3类设计参数;建立了由"考虑美学与气动阻力的车灯造型汽车外流场数值分析简化模型"和正交实验优化算法组成的车灯造型参数设计平台.实例的数值计算和风洞实验验证了文中方法的有效性及参数优化组合的效果.该方法对丰富汽车造型设计和车灯设计、促进其工程化很有意义.     

导弹异形卷弧翼安装选型

为在空中发射武器外形设计中引入异形卷弧翼,将其作为导弹主升力面,研究其相对于弹身的安装选型问题．模型设计采用1对异形卷弧翼,并将其沿弹体纵向平面对称布置．定义异形卷弧翼相对于弹身的安装位置角和安装偏角参数,选取2组计算模型,基于计算流体力学（Computational Fluid Dynamics,CFD）仿真计算评估这2个角度的变化对异形卷弧翼-弹身组合体纵向超音速气动参数的影响,得到组合体升力因数、阻力因数以及升阻比随2个角度参数变化而变化的规律．结果表明,在设计任务中,当安装位置角等于120°,安装偏角等于-10°时,组合体的升力因数和升阻比达到最大值．该方法可以改善导弹的升力特性,提高导弹的升阻比,使导弹获得更好的飞行性能．     

总线化车身控制及诊断系统的设计

低成本和低功耗、高可靠性和智能化是制约网络化技术在车身控制中应用的重要因素。兼顾实时性和成本,设计开发了基于CAN／LIN总线的车身电子电器网络化控制系统,该系统由左、右前车灯模块,左、右后车灯模块,左、右后视镜模块,车项灯光控制模块,组合开关模块等组成。在介绍了车身控制网络的拓扑结构、各CAN／LIN控制模块的软硬件设计的基础上,着重讨论了模块的智能驱动、冗余设计、抗干扰措施、异常保护、故障诊断和报警的软硬件实现方法,以及控制模块的低功耗设计等内容。完成的控制网络已在桑塔纳2000上进行了装车,实验结果验证了方案的可行性和正确性。     

Reduction of aero-acoustic noise originating from a high-speed polygon mirror scanner motor in a laser beam printer utilizing air-flow analysis

This research investigates the aero-acoustic noise originating from a high-speed polygon mirror of a laser beam printer by identifying its source and propagation numerically and experimentally. It calculates the air flow around the polygon mirror scanner motor of a laser printer operating at high speed. Simulated velocity of air flow around the polygon mirror is compared with the experimental velocity measured using a hot-wire anemometer. The frequency spectrum of the air flow around the polygon mirror matches that of the aero-acoustic noise. A significant number of discrete peaks and a broadband of aero-acoustic noise originate from the turbulent air flow around the polygon mirror. We propose the use of a cylindrical block to reduce turbulent air flow around the polygon mirror. The proposed design reduces not only the turbulent air flow but also the discrete peaks and the broadband of aero-acoustic noise.     

Computational simulation of model and full scale Class 8 trucks with drag reduction devices

Numerical solutions of the unsteady Reynolds-averaged Navier–Stokes equations using a parallel implicit flow solver are given to investigate unsteady aerodynamic flows affecting the fuel economy of Class 8 trucks. Both compressible and incompressible forms of the equations are solved using a finite-volume discretization for unstructured grids and using Riemann-based interfacial fluxes and characteristic-variable numerical boundary conditions. A preconditioned primitive-variable formulation is used for compressible solutions, and the incompressible solutions employ artificial compressibility. Detached eddy simulation (DES) versions of the one-equation Menter SAS and the two-equation k − ?/k − ω hybrid turbulence models are used. A fully nonlinear implicit backward-time approximation is solved using a parallel Newton-iterative algorithm with numerically computed flux Jacobians. Unsteady three-dimensional aerodynamic simulations with grids of 18–20 million points and 50,000 time steps are given for the Generic Conventional Model (GCM), a 1:8 scale tractor–trailer model that was tested in the NASA Ames 7 × 10 tunnel. Computed pressure coefficients and drag force are in good agreement with measurements for a zero-incidence case. Similar computations for a case with 10° yaw gave reasonable agreement for drag force, while the pressure distributions suggested the need for tighter grid resolution or possibly improved turbulence models. Unsteady incompressible flow simulations were performed for a modified full scale version of the GCM geometry to evaluate drag reduction devices. All of these simulations were performed with a moving ground plane and rotating rear wheels. A simulation with trailer base flaps is compared with drag reduction data from wind tunnels and track and road tests. A front spoiler and three mud-flap designs with modest drag reduction potential are also evaluated.     

汽车水平外形参数对气动阻力影响的仿真分析

针对现有的汽车气动性能优化研究大多集中于纵向外形参数上,缺乏对水平外形参数研究的问题,选取水平外形参数中车尾收缩角和后风窗收缩角作为气动优化研究对象.利用数值仿真软件建立车体模型并进行仿真,求解获得水平外形参数的变化对气动阻力的影响规律.将水平参数的变化与对应的纵向外形参数的减阻效果进行对比分析.结果表明：水平外形参数的变化引起尾流结构显著变化,且与对应的纵向外形参数相比其减阻效果更好.因此,水平外形参数对汽车气动性能优化具有积极影响.     

基于ZigBee无线传感器的空调PMV控制方法研究

为了达到使室内环境满足人体对舒适度的要求,设计了一种基于ZigBee的PMV实时控制系统.该系统通过无线传感器对室内环境因素进行实时测量,经过计算对空调送风温度和风量进行实时控制.通过仿真和数据测量证明该控制系统相比定温度的传统控制系统更具有合理性,且具有低功耗、低成本、自组织等特点,拥有广泛的应用前景.