二维传声器阵列测量技术及其对飞机进场着陆过程噪声的实验研究

发展了一种由１１１个传声器组成的Ｍ维平面传声器阵列测量技术,１１１个传声器在平面阵列中的位置应用随机优化的方法确定,从而保证平面传声器阵列在感兴趣的测量频率范围内具有理想的性能,并应用数值模拟的方法检验了平面传声器阵列的频谱特性．应用此平面传声器阵列对当前流行的民用客机进场着陆过程中飞机噪声源进行了测量分析,实验结果表明应用此项技术可以辨别出在飞机表面上所有重要的噪声源,并可获得全尺寸飞机机体重要噪声源的详细的频谱特性、指向特性和声级变化．     

ARJ21客机降落阶段起落架噪声试验研究

为了测量ARJ21客机的起落架噪声,在飞行现场分别采用改进的频域波束形成和解卷积算法对降落阶段的起落架噪声进行了测量。通过比较两种算法发现,解卷积算法比改进的频域波束形成算法具有更好的声源识别能力。为了提高传声器的利用率,设计了多臂螺旋阵,并且利用线性插值消除了多普勒效应。根据主起落架和前起落架的分布位置不同,将声源识别区域划分为两部分,在140—800Hz范围内对不同频段的1/3倍频程的起落架噪声进行了测量。结果发现:在250 Hz以上频段,主起落架为主要噪声源,且在中心频率500 Hz的1/3倍频程内为唯一强声源;前起落架在中心频率630 Hz的1/3倍频程内为主要噪声源。通过试验得到了主起落架和前起落架噪声在不同频段的分布特点,为起落架降噪设计提供了支持。     

间歇性排气噪声源的特性及消声器结构的研究

排气噪声可分为稳定排气噪声，周期性排气噪声和间歇性排气噪声，通过对锻压机离合器与制动器的排气噪声源的特性研究，指出间歇性气噪声是由管道噪声，阀门噪声和喷口噪声所组成，首次指出了间歇性排气噪声存在单极子噪声及爆炸声。通过理论计算及试验建立了一种有效的滤波了噪消声器结构。     

频谱测量中的边带噪声误差估测

将频谱测量中的误差分为两大类，即被测信号的误差和频谱仪本身的误差。图1为仪器输入信号Vin中包含的噪声Vn和信号Vs的频谱，则瞬时噪声Vn=Vin-Vs,在频域上关于信号工对称。笋析证明边带噪声是由幅度噪声和相位噪声组成，并用小信号调制理论来描述，     

舰船多辐射声源近距离通过特性的仿真

由于舰船三个特定部位(尾部、中后部、中部)的辐射噪声具有明显不同的功率谱特征,利用这些特征具有实际的意义。我们采用简化的近距离舰船辐射噪声三亮点模型来逼近舰船这三个特定部位的辐射噪声中的连续谱结构,采用时间滑动的卷积算法来重构舰船某一辐射噪声源的噪声序列,重构的噪声序列同时具有要求的幅度概率分布和功率谱形状。在重构不同辐射声源时域信号的基础上,对舰船辐射噪声的通过特性以及三个辐射噪声源在不同的接收位置的影响进行了仿真。仿真结果与实测的某型舰船的通过频谱结果相比较,表明其频域特征是大体一致的。     

贯流风扇气动声场数值模拟及分析

针对贯流风扇气动噪声传播特性,采用基于非结构网格的CE/SE算法对其气动流场进行数值模拟,并模拟了气动噪声的传播.湍流模拟采用大涡模型,搭接式滑移网格模型处理动静干涉.噪声传播采用完全欧拉方程作为控制方程,远场采用无反射边界条件.将使用该方法得到的远场噪声频谱与实验数据进行对比分析,结果表明与实验测量得到宽带频谱不同,采用大涡模拟湍流模型进行声源模拟时,会加强部分离散频率上的声级,从而产生误差.     

南海北部海洋环境噪声谱级空间差异性分析

为研究中国近海海洋环境噪声的空间差异性,揭示其形成原因,以同一海域同一季节两个测量站位的长期观测数据为研究对象,对比两个站位噪声谱级的差异.结合海洋信道和噪声源特性的影响,分析港口强噪声源到噪声采集站位的传播损失,发现在50~500 Hz频段传播损失差值和噪声谱级差值呈现较强相关性;对港口航船噪声源级的分析发现,该频段内源级相差20 dB左右,与休渔期前后航船密度差异相对应。试验分析和研究结果表明,南海北部海域50~500 Hz频段内海洋环境噪声与航船噪声源密切相关,两站位噪声空间差异由海区传播条件差异与航船噪声源级差异共同引起。      

某型歼击机进气道噪声测量

为了估算某型歼击机进气道结构的声疲劳特性,在试飞状态对此型飞机进行了实际声载荷测量.测量传声器采用压电晶体传声器.飞行状态包括起飞、着陆及中空和高空各种特技飞行.测量结果表明,受载状况及噪声频谱与飞行状态密切相关,它对研究歼击机进气道内的声场特性及评估进气道结构的声疲劳特性都有较高的实用价值.     

起降客机噪声源识别的平面阵设计

针对起降客机的噪声源识别,给出了平面多臂对数螺旋阵的设计过程。多臂对数螺旋阵可以在较宽的分析频带内保持较小的主瓣宽度,同时平均旁瓣水平较低,从而具有良好的宽带噪声源识别性能,但其阵型设计中需要考虑的参数较多。本文以ARJ21客机起降过程中的主起落架噪声源识别为例,研究了多臂对数螺旋阵各参数对其噪声源识别性能的影响。所给出的阵列设计流程可以为飞行客机的噪声源识别,尤其是多子阵嵌套的平面阵设计提供参考。     

近场声全息技术及其应用

<正>陈心昭毕传兴北京:科学出版社,2013,243页,定价:65元准确识别噪声源是噪声研究、控制、声质量设计的前提。早期识别噪声源的方法,如近场声压法和表面振速法,采用声级计和加速度传感器等进行简单的噪声振动测量并加以判断,简单但精度不高,可归为经典声学方法。电子技术、计算机技术和信号处理技术的迅速发展,为我们提供了现代声学意义上的噪声源识别方法,如频谱分析、相关分析、相干分析等,进一步又出现了声强测量、小波分析、声全息、声聚焦、波束成形等新方法和新技术。     

渐开线斜齿轮短齿廓修形降噪分析*

为了降低特定工况下减速箱的噪声特性,找到相对最佳的渐开线斜齿轮修形方式,该文基于专业的齿轮修形软件Kisssoft和多学科一体化软件LMS Virtual Lab,根据短齿廓修形可以改变渐开线斜齿轮的端面、轴向重合度的原理,比较了未修形和经过不同短齿廓修形方式达到特定重合度后的渐开线斜齿轮减速箱声功率级的大小。分析了经过短齿廓修形后的减速箱声功率级在转速500~2000 r/min之间显著下降的原因,并对经过短齿廓修形后的减速箱声功率级在2500 r/min和3000 r/min时并未明显下降的原因做了解释。最后根据减速箱声功率级在转速500~2000 r/min之间的平均降幅,认为通过齿形鼓形修形使得渐开线斜齿轮的端面、轴向重合度分别为1.516、0.864时,减速箱声功率级降幅最大,降噪效果最好。     

飞机机体表面声压及舱内降噪优化设计

本文以某型客机为研究对象，从飞行试验数据分析和声学建模两方面研究机体表面声压分布及其对舱内壁板近场辐射声压的影响。首先根据试飞数据分析了机体表面声压分布，然后利用统计能量法建立飞机客舱中后段的声学模型，以试飞数据作为声源输入，研究机体表面声压分布对客舱内部壁板附近声压分布的影响，并在此基础上提出优化设计方案，通过模型验证优化方案的有效性。试飞数据表明：机体表面声压在后应急门前方、靠近地板处最大；巡航速度升高，声压级较大区域的面积随之增加；巡航高度和发动机N1N2频率变化对机体表面声压级分布无明显影响。仿真数据表明：仅蒙皮结构无法有效降低客舱噪声；对声学降噪包进行优化能增加壁板隔声量，降低舱内声压。     

Noise Reduction in Spur Gear Systems

This article lists some tips for reducing gear case noise. With this aim, a static analysis was carried out in order to describe how stresses resulting from meshing gears affect the acoustic emissions. Different parameters were taken into account, such as the friction, material, and lubrication, in order to validate ideas from the literature and to make several comparisons. Furthermore, a coupled Eulerian–Lagrangian (CEL) analysis was performed, which was an innovative way of evaluating the sound pressure level of the aforementioned gears. Different parameters were considered again, such as the friction, lubrication, material, and rotational speed, in order to make different research comparisons. The analytical results agreed with those in the literature, both for the static analysis and CEL analysis—for example, it was shown that changing the material from steel to ductile iron improved the gear noise, while increasing the rotational speed or the friction increased the acoustic emissions. Regarding the CEL analysis, air was considered a perfect gas, but its viscosity or another state equation could have also been taken into account. Therefore, the above allowed us to state that research into these scientific fields will bring about reliable results.     

Study on the effect of sound duration on the annoyance of helicopter noise by applying a technique of time compression and expansion of sound signals

The number of helicopter operations has rapidly increased during the last 20 years in Japan. Helicopter noise sounds different from other aircraft; the waveform of the sound pressure is impulsive and the signal duration is relatively long. The Environmental Agency of Japan implemented new guidelines for evaluating noise exposure around small airports, including heliports, in 1990. This study was executed in connection with the development of provisional guidelines. Psychoacoustic experiments were carried out to identify an evaluation index for helicopter noise. In order to examine the effect of duration independently, we not only used original sound recordings, but also synthesized sound signals. The durations of these sound signals were time compressed or expanded without degrading the quality of the original sound recording. The test results show that the effect of duration is significant, and that the A-weighted sound exposure level is a better index than the maximum A-weighted sound pressure level for the evaluation of helicopter noise.     

Impact of aircraft sound quality combined with the repetition of aircraft flyovers on annoyance as perceived activity disturbance in a laboratory context

This study focuses on perceived activity disturbance evaluated by participants who are subjected to the repetition noise of current aircraft and modified aircraft in regard to tonal quality. A previous study devoted to the sound quality of aircraft noise revealed that one of the most important perceptive features is the emergence of Doppler shifted tones. Six 20-min sound sequences were created combining two variables: number of aircraft (N₁ with six aircraft and N₂ with 10 aircraft plus one sequence without aircraft N₀) and tonality (sequences with current aircraft, sequences with +5 dB-amplified tonality and sequences with −5 dB-attenuated tonality). For all sequences, the equivalent sound level and the peak level of the loudest event are constant, except for the sequence without aircraft. Sixty-three subjects, attending two different sequences in one session, rated on a category scale the level of activity disturbance due to the noise environment when carrying out memory and concentration tasks. The order of presentation was controlled as an additional variable in the variance analyses. The perceived activity disturbance is significantly influenced by the equivalent sound level. The influence of the number of aircraft flyovers is statistically significant at the 5% level. High tonal components have no effect on perceived disturbance. Memory and concentration performances, measured by number of incorrect or correct answers, are influenced only by the order of presentation, revealing the importance of the learning effect. Reaction time, which is influenced by the equivalent sound level, seems better adapted for measuring the effect of noise on task achievement. These results are discussed in regard to related research.     

The effect of proximity of the landing gear lights on its turbulent wake

A simplified model of a landing gear is tested in a wind tunnel to investigate the effect of the landing light location on the resulting noise generation. Examination of the near-field pressure fluctuations, combined with phase-locked stereoscopic particle imaging velocimetry of the unsteady wake identified two distinct sources of pressure fluctuations. The higher frequency source has a wide frequency band and is situated in the outer regions of the wake near the lights. On the other hand, the lower frequency source is found to be stronger, has a narrower frequency band and is developed further downstream in the wake, closer to the wake centreline. The lower frequency source is observed to be rather robust as it is hardly affected by the location of the landing lights, whereas the higher frequency source becomes weaker as the spacing between the lights is reduced. The effect of a splitter plate positioned downstream of the landing gear strut is also investigated as a means of reducing the lower frequency pressure fluctuations. Although the lower frequency source is considerably weakened by the splitter plate, substantial enhancement of the higher frequency source is observed.     

Interactive simulation of aircraft noise in aural and visual virtual environments

This paper describes a novel aircraft noise simulation technique developed at RWTH Aachen University, which makes use of aircraft noise auralization and 3D visualization to make aircraft noise both heard and seen in immersive Virtual Reality (VR) environments. This technique is intended to be used to increase the residents’ acceptance of aircraft noise by presenting noise changes in a more directly relatable form, and also aid in understanding what contributes to the residents’ subjective annoyance via psychoacoustic surveys. This paper describes the technique as well as some of its initial applications. The reasoning behind the development of such a technique is that the issue of aircraft noise experienced by residents in airport vicinities is one of subjective annoyance. Any efforts at noise abatement have been conventionally presented to residents in terms of noise level reductions in conventional metrics such as A-weighted level or equivalent sound level L_eq. This conventional approach however proves insufficient in increasing aircraft noise acceptance due to two main reasons – firstly, the residents have only a rudimentary understanding of changes in decibel and secondly, the conventional metrics do not fully capture what the residents actually find annoying i.e. characteristics of aircraft noise they find least acceptable. In order to allow least resistance to air-traffic expansion, the acceptance of aircraft noise has to be increased, for which such a new approach to noise assessment is required.     

Estimation of directivity and sound power levels emitted by aircrafts during taxiing, for outdoor noise prediction purpose

Integrated noise model (INM) is the most internationally used software to calculate noise levels near airports. Take off, landing or pass by operations can be modeled by INM, but it does not consider aircrafts taxiing, which, in some cases, can be important to accurately evaluate and reduce airports’ noise assessment.Aircraft taxiing noise emission can be predicted using other prediction tools based on standards that describe sound attenuation during propagation outdoors. But these tools require data inputs that are not known: directivity and sound power levels emitted by aircraft during taxiing.This paper describes methods used to calculate directivity indexes and sound power levels, based on field measurements made in Madrid-Barajas Airport (Spain). Obtained results can be used as inputs for general purpose outdoor sound prediction software, which will be able to evaluate noise at airports vicinity as industrial noise.Directivity and sound power levels have been estimated in octave and third octave band terms, for several aircraft families.     

An experimental study of sound generated by flows around cylinders of different cross-section

The sound radiated by rigid cylinders placed transversely in a uniform stream has been measured in an anechoic wind tunnel over a range of Mach numbers (M=0.09-0.2). The cylinders have different cross-sections, e.g., circular, square, rectangular, elliptic, and circular with lateral ribs or knurled surfaces. Different length to diameter ratios of the cylinders are also investigated. Results are presented as narrow band spectra, measured in the far field (acoustic as well as geometric). All spectra are presented with dimensionless (scaled) axes, as well as the original dimensional scales. It is shown that elliptic cross-sections are less noisy, compared to all other cylinders, but noise abatement techniques such as lateral ribs and knurled surfaces can also reduce tonal radiated noise. Two practical applications of these experiments are the reduction of radiated noise from pantographs of high-speed railway trains, and from the landing gear of modern passenger aircraft.