高超声速飞行器气体辐射噪声计算方法

高超声速飞行器周围的激波层内高温气体会发生剧烈的物理化学变化,伴随强烈的光辐射过程,直接影响红外导引头的光学成像效果。采用流体力学Navier-Stokes方程和热化学非平衡模型模拟高温非平衡流动,考虑电子跃迁和振转跃迁以窄带法求解气体辐射特性参数,基于有限体积法离散辐射传输方程,在分别验证流场解算、辐射参数求解和辐射传输计算的基础上,进行了飞行器高速飞行的流动和辐射模拟。数值求解得到了飞行器流场特征和粒子数空间分布。计算的选定波长范围内的气体辐射发射系数空间分布显示其与激波形状和波后气体温度分布相似。通过传输得到的飞行器光学窗口视线路径上的气体辐射噪声成轴对称分布,发现辐射噪声和飞行速度、气体成分等密切相关,马赫数增加时气体辐射噪声显著增强。     

高超声速飞行器气体辐射噪声计算方法

高超声速飞行器周围的激波层内高温气体会发生剧烈的物理化学变化,伴随强烈的光辐射过程,直接影响红外导引头的光学成像效果。采用流体力学Navier-Stokes方程和热化学非平衡模型模拟高温非平衡流动,考虑电子跃迁和振转跃迁以窄带法求解气体辐射特性参数,基于有限体积法离散辐射传输方程,在分别验证流场解算、辐射参数求解和辐射传输计算的基础上,进行了飞行器高速飞行的流动和辐射模拟。数值求解得到了飞行器流场特征和粒子数空间分布。计算的选定波长范围内的气体辐射发射系数空间分布显示其与激波形状和波后气体温度分布相似。通过传输得到的飞行器光学窗口视线路径上的气体辐射噪声成轴对称分布,发现辐射噪声和飞行速度、气体成分等密切相关,马赫数增加时气体辐射噪声显著增强。     

轴流通风机气动噪声的实验与预测

１引言轴流风机的气动噪声基本可分为紊流噪声及离散噪声。在中、低压头范围,尤其是单转子风机情况下,离散噪声经过管道声阻抗的衰减作用,在远离风机声场中可降到很低水平,此时紊流噪声成为主要成分。紊流噪声可有多种声源［１］,包括来流攻角引起升力变动相应的紊流噪声,叶片表面紊流边界层直接幅射的素流噪声,边界层分离的噪声,及叶片尾涡引起升力变化诱发的噪声。这些噪声都具有宽频带的特性。在来流无冲击进口,无边界层分离的正常运行条件下,从边界层中小尺寸旋涡直接幅射的声能是不大的。对有限叶片弦长,因叶片两表面大尺寸…     

亚音主旋翼的噪声预测和声隐身分析

本文介绍了基于FW-H方程的亚音主旋翼噪声预测方法,并在螺桨噪声预测程序基础上发展了主旋翼噪声预测程序。本文采用商用CFD软件FINE／TURBO模拟直升机旋翼流场,为噪声预测程序提供所需要的桨叶表面载荷,并用算例验证了载荷数据的准确性和噪声预测程序的有效性。本文计算和讨论了亚音悬停条件下的辐射噪声,并重点分析了不同形状桨叶对辐射噪声的影响,结果表明采用合理的薄翼型叶尖、尖削叶尖及线性扭转桨叶都可以降低辐射噪声,为通过改变桨叶形状降低旋翼辐射噪声提供了合理途径。     

车辆天窗气动噪声的数值分析与实验研究

本文从汽车天窗气动噪声的机理入手,利用与实车几何尺寸为1:5的简化模型进行了空腔绕流的数值计算,分析了其流场结构及气动噪声产生的原因.在低速静音风洞中进行了不同流速下的流场和声场实验研究,研究了天窗不同位置的速度剪切层变化,以及不同流速下的声压级变化,发现了除了特征频率下的风振噪声,还存在较大频率范围的气动噪声,其随着...     

水下目标噪声测量中的同步钟测距

本测距系统采用两只型号相同的ＷＺＧ－５ＭＨｚ石英晶体振荡器，在同一个时基标准下进行同步测距，５ＭＨｚ石英晶体振荡器具有准确度高，稳定性好的特点，从而成功的解决了在舰船辐射噪声测量中，目标船与测量水听器间测距误差大的问题。本文较详细的介绍了同步钟测距原理，并对在舰船辐射噪声测量中噪声级与距离关系，目标船相对测量水听器的位置，测距误差等进行了描述。     

激光测距在测量船舶近场辐射噪声中的应用

本文主要阐述在海上测量船舶的近场辐射噪声中，利用激光测距，快速，准确得到了被测船舶与测量水听器之间的正横距离。     

支持向量机对舰船噪声DEMON谱的分类识别

本文采用径向基核函数的支持向量机的分类算法,实现了对舰船目标的分类识别。对两类不同类型的舰船的辐射噪声的DENOM谱建立了支持向量机模型,并进行了分类识别试验。试验结果表明,在结构风险最小的准则下,采用网格搜索法确定,径向基核函数的参数σ取值0.23、惩罚系数C值取13为最优的分类识别参数。并通过留一法验证,该模型具备良好的推广能力,总体正确识别率为91.2%。     

前置导叶对横流风机性能及气动噪声的影响

在横流风机叶轮前加前置导叶(IGV)可以改善横流风机的进口流场,减少叶片上的流动分离,进而降低横流风机的功率。采用非结构化网格RNGκ-ε两方程模型,分别对不加IGV、加IGV1,以及IGV2的横流风机内部流场进行数值模拟,并对三种情况进行气动性能及噪声试验。数值模拟和试验结果表明在加不同IGV以后,横流风机的噪声增大,但是功率在加IGV2后出现了一定的降低。     

Effect of cutter geometric configuration on aerodynamic noise generation in face milling cutters

Aerodynamic noise spectrum of rotary face milling cutters consists of a broad range of high frequencies and discrete tones. This paper aims to develop a method to calculate the aerodynamic noise generation and propagation by rotary face milling cutters. The effects of milling cutter geometry on the generation of aerodynamic noise are analyzed. Based on the computational fluid dynamics (CFD) method, the Ffowcs Williams–Hawkings (FW–H) equation is used to predict the sound pressure level (SPL) of aerodynamic noise in face milling cutters. The accurate calculation of time-varying flow variables along with the rotation of cutter is very important for the prediction of aerodynamic noise. In this case, the Navier–Stokes (N–S) equation is employed to evaluate the pressure and velocity fields around the milling cutters, first in a steady mode with the Multiple Reference Frames (MRF) model, and then in an unsteady mode with sliding mesh technique (SMT) by introducing the steady flow variables as its initial fields. It is found that both the overall aerodynamic noise due to the entire cutter and the aerodynamic noise only due to the cutter gullet regions are significantly affected by the number of cutter teeth/gullet regions. Moreover, six representative milling cutters with different tooth numbers and geometries of gullet regions are chosen to study the effects of gullet configuration on aerodynamic noise generation, and the characteristics of noise spectra generated by the cutters are analyzed. The aerodynamic noise generated only by the cutter gullet regions is found to be strongly dependent on the gullet design-volume and shape. The results also reveal that the gullet design advantage of Cutter C in reducing noise generation among the eight-tooth designs, and the gullet design advantage of Cutter A in reducing noise generation among the five and seven-tooth designs in this investigation.     

Computational bluff body aerodynamic noise prediction using a statistical approach

A new method for calculating the aerodynamic noise generated by bluff bodies is presented in this paper. The methodology uses two-dimensional, unsteady Reynolds averaged Navier Stokes turbulent flow simulations to calculate the acoustic source terms. To account for turbulent flow effects that are not resolved by the flow simulation, a statistical approach has been developed and applied to introduce narrow band random noise. Spanwise de-correlation of flow information is accounted for using a correction method based on a de-correlation length scale. Curle’s compact acoustic analogy is used to calculate the far-field noise. To illustrate the effectiveness of the method, the turbulent flow and noise about two test cases are calculated and compared with experimental results from the literature.     

高速动车组气动噪声试验与仿真分析

通过风洞试验对某高速动车组整车、受电弓及转向架远场气动噪声特性进行分析.试验结果表明,高速动车组远场气动噪声是一宽频噪声,总声能随速度的6.6次方增加;由受电弓引起的远场气动噪声主要集中在中高频,噪声峰值频率随速度变化线性增加;由转向架引起的远场气动噪声主要集中在中低频,噪声峰值频率与速度无关.在此基础上,通过大涡模拟...     

电动水上飞机低噪声螺旋桨翼型优化

为降低翼型的气动噪声,以某型电动水上飞机螺旋桨所使用的RAF-6翼型为研究对象,首先通过CFD/FW-H方法计算得到翼型的升、阻力系数以及气动噪声;其次使用型函数线性叠加描述翼型的几何形状;进而,为使翼型获得设计状态下较好的声学与气动性能,由翼型的气动噪声与升阻比构成优化目标,以型函数系数为变量,以保证翼型升、阻力系数变化不超过10%为约束,使用引入响应面模型的遗传算法对翼型进行降噪优化。通过优化翼型与基准翼型的对比可知,设计状态的优化翼型气动噪声声压级降低了2.17 dB,升阻比提高1.12%,且优化翼型在小攻角状态下具有较为优异的声学与气动性能。优化结果表明,该优化方法具有一定应用价值,可为螺旋桨噪声控制研究提供参考。     

LES-FEM coupled analysis and experimental research on aerodynamic noise of the vehicle intake system

To thoroughly explore the aerodynamic noise in order to achieve a more efficient engineering application for a vehicle intake system, the large eddy simulation and the finite element method were employed in numerical simulations, and the aeroacoustic characteristics were validated through the experimental data. In this research, the k-ε model was adopted to simulate the steady state fluid dynamic, and the static pressure loss was consistent with the bench test data, indicating the computational fluid dynamics model was valid. After acquiring the data from the steady state simulation, the fluctuating pressure of the inner wall was calculated based on the transient state calculation results from the large eddy simulation. Thereafter, the finite element method was used to determine the acoustic performance of the intake system. By comparing the experiment data, the noise reduction indicated that the intake system performed well at various frequencies, e.g. 320 Hz, 520 Hz and 770 Hz, but poorly at 140 Hz, 210 Hz, 420 Hz and 600 Hz. Finally, the far-field aerodynamic noise was calculated based on FW-H equation, and the output showed that the noise of each measuring point agreed well with the test results in trend. In particular, the inlet sound pressure spectrum almost fit the test data with the airflow of 300 m³/h, and several amplitude peaks appeared at 210 Hz, 420 Hz and 600 Hz, corresponding to the low-attenuation region of the noise reduction curve. Moreover, the specific frequencies were not shifted with the airflow changing. In conclusion, the numerical simulation method proves to be effective in calculating the aerodynamic noise accurately.     

低压载人试验舱复压系统的气动特性计算和声学设计

随着我国高山医学和航空航天生物学研究的发展，低压舱的设计与建造已提到了议事日程。低压载人试验舱要为科学家提供合适的低压条件，同时又要为乘员创造必要的工作生活环境包括声学环境，本文介绍低压舱舱内气动状态的计算方法和复压系统的声学设计，并给出计算实例。     

Some aerodynamic and acoustic characteristicsof acute laryngitis

The purpose of the present study was to describe the effects ofacute laryngitis on some aerodynamic, acoustic, and perceptual measures. Eleven subjects with diagnosed acute laryngitis due to upper respiratory infection were recorded during a laryngitic episode and 1 week to 10 days after amelioration of the laryngitic condition. Fundamental frequency values, collapsed across the five vowels, were significantly reduced in the laryngitic compared with the normal speaking condition. The decrease in fundamental frequency associated with acute laryngitis suggests an increase in the mass of the vocal folds. In addition, aerodynamic values differed significantly for the laryngitic condition compared with the normal speaking condition, suggesting the presence of laryngeal hypofunction. Perceptual data indicated that speakers in the laryngitic condition were judged to have a hoarse voice when compared with the normal speaking condition.     

Theory of aerodynamic heating from molecular collision analysis

An aerodynamic heating model is derived from molecular collision analysis, in which the rising temperature of a hypersonic flying object as a function of the flying speed in a classical dense monoatomic gas environment is set up. The model predicts that the rising temperature of the hypersonic flying object is independent of the gas density but depends linearly on the gas atomic mass. A nonequilibrium molecular dynamics simulation is carried out to verify the theoretical model. Also, through analyzing the vibrational density of states in the flying objects, it is found that the excited phonon frequency is near the collision frequency, uncovering that the phonons are mainly excited by the face colliding gas atoms. Our study provides a new insight into understanding the intrinsic mechanism of aerodynamic heating and helps to develop the temperature-controllable hypersonic flying vehicle.     

多路噪声测量系统的研制

本描述了多路噪声测量系统的建立,该系统是一以微机为中心的数字化系统,可实现对４路稳态宽带噪声的测量,测量参数是线性声压级和倍频带声压级。系统由微机、ＴＭＳ３２０Ｃ３０板、多路ＡＤ板、传感器、放大器等设备构成硬件系统,并通过编制Ｃ３０板嵌入式软件和微机主控程序实现系统功能。在软件编制中结合数字信号处理技术,并结合硬件特性优化程序设计,本系统测量方法简易,快捷和精度高,在噪声测量领域具有较高实用价值