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Applied Sciences
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Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems
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Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Acoustics and Vibrations".

Deadline for manuscript submissions: closed (30 April 2019) | Viewed by 34921

Printed Edition Available!
A printed edition of this Special Issue is available here.

Special Issue Editors

Prof. Dr. Roberto Citarella

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Guest Editor
Department of Industrial Engineering, University of Salerno, 84084 Fisciano, Italy
Interests: fracture mechanics; fatigue; bioengineering; vibroacoustics; boundary element method; finite element method; statistical energy analysis; dynamics
Special Issues, Collections and Topics in MDPI journals
Dr. Luigi Federico

E-Mail Website
Guest Editor
Head of Environmental Impact of Air Transport System Dept., Italian Aerospace Research Center (CIRA), Via Maiorise, 81043 Capua, CE, Italy
Interests: vibroacoustics; aeroacoustics; aerospace systems; air traffic management (ATM)
Special Issues, Collections and Topics in MDPI journals
Dr. Mattia Barbarino

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Guest Editor
Head of Computational Acoustics Laboratory, Italian Aerospace Research Center (CIRA), 81043 Capua (CE), Italy
Interests: aero-vibro-acoustics; CFD; machine learning; multidisciplinary optimization
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The journal, Applied Sciences, is a forum for the communication of ideas and methods presently in use at the forefront of technology in the field of applied engineering. The purpose of this Special Issue is to highlight the latest enhancements in the abatement of noise and vibrations of aerospace and automotive systems. The reduction of acoustic emissions and the improvement of cabin interior comfort are on the path of all major industries of the transport system, having a direct impact on customer satisfaction and, consequently, the commercial success of new products. Topics to be covered in this Special Issue deal with computational, instrumentation and data analysis of noise and vibration of fixed wing aircrafts, rotating wing aircrafts, space launchers and automotive vehicles and cover, but are not limited to, aerodynamically generated noise, engine noise, sound absorption, cabin acoustic treatments, duct acoustics, active noise control and vibroacoustic properties of materials. The Special Issue provides an opportunity for scientists and engineers to publish their studies of current interest, both in the computational and experimental fields of research, and also articles introducing new approaches and methodologies.

Dr. Roberto Citarella
Dr. Luigi Federico
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Applied Sciences is an international peer-reviewed open access semimonthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • Vibroacoustics
  • Aeroacoustics
  • Acoustics, Noise, Vibration, Aeronautics, Automotive

Published Papers (10 papers)

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Editorial

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3 pages, 159 KiB  
Editorial
Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems
by Roberto Citarella, Luigi Federico and Mattia Barbarino
Appl. Sci. 2020, 10(11), 3853; https://doi.org/10.3390/app10113853 - 01 Jun 2020
Cited by 7 | Viewed by 1730
Abstract
This Special Issue highlights the latest enhancements in the abatement of noise and vibrations of aerospace and automotive systems. The reduction of acoustic emissions and the improvement of cabin interior comfort are on the path of all major transportation industries, having a direct [...] Read more.
This Special Issue highlights the latest enhancements in the abatement of noise and vibrations of aerospace and automotive systems. The reduction of acoustic emissions and the improvement of cabin interior comfort are on the path of all major transportation industries, having a direct impact on customer satisfaction and, consequently, the commercial success of new products. Topics covered in this Special Issue deal with computational, instrumentation and data analysis of noise and vibrations of fixed wing aircrafts, satellites, spacecrafts, automotives and trains, ranging from aerodynamically generated noise to engine noise, sound absorption, cabin acoustic treatments, duct acoustics and vibroacoustic properties of materials. The focus of this Special Issue is also related to industrial aspects, e.g.,: numerical and experimental studies have been performed for an existing and commercialized engine to enable design improvements aimed at reducing noise and vibrations; moreover, an optimization is provided for the design of low vibroacoustic volute centrifugal compressors and fans whose fluids should be strictly kept in the system without any leakage. Existing procedures and algorithms useful to reach the abovementioned objectives in the most efficient way are illustrated in the collected papers. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)

Research

Jump to: Editorial

16 pages, 6748 KiB  
Article
A Novel Optimization Framework to Replicate the Vibro-Acoustics Response of an Aircraft Fuselage
by Venanzio Giannella, Riccardo Lombardi, Matteo Maria Pisani, Luigi Federico, Mattia Barbarino and Roberto Citarella
Appl. Sci. 2020, 10(7), 2473; https://doi.org/10.3390/app10072473 - 03 Apr 2020
Cited by 11 | Viewed by 2066
Abstract
In this work, a novel optimization framework, based on a Multi-Disciplinary Optimization (MDO) procedure, applied to the vibro-acoustic Finite Element Method (FEM) model of an aircraft fuselage mock-up, is proposed. The MDO procedure, based on an Efficient Global Optimization (EGO)-like approach, is implemented [...] Read more.
In this work, a novel optimization framework, based on a Multi-Disciplinary Optimization (MDO) procedure, applied to the vibro-acoustic Finite Element Method (FEM) model of an aircraft fuselage mock-up, is proposed. The MDO procedure, based on an Efficient Global Optimization (EGO)-like approach, is implemented to characterize acoustic sources that replicate the sound pressure field generated by the engines on the fuselage. A realistic sound pressure field, evaluated by aeroacoustic simulations, was considered as the reference acoustic load, whereas two equivalent sound fields, displayed by two different arrays of microphones and generated by the same configuration of monopoles, were calculated by the proposed vibro-acoustic FEM-MDO procedure. The proposed FEM-MDO framework enables to set up ground experimental tests on aircraft components, useful to replicate their vibro-acoustic performances as if tested in flight. More in general, such a procedure can also be used as a reference tool to design simplified tests starting from more complex ones. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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15 pages, 4546 KiB  
Article
Research on Leakage Location of Spacecraft in Orbit Based on Frequency Weighting Matrix Beamforming Algorithm by Lamb Waves
by Lei Qi, Zhoumo Zeng, Yu Zhang, Lichen Sun, Xiaobo Rui, Xin Li, Lina Wang, Tao Liu and Guixuan Yue
Appl. Sci. 2020, 10(4), 1201; https://doi.org/10.3390/app10041201 - 11 Feb 2020
Cited by 7 | Viewed by 1919
Abstract
Clashes between space debris and spacecraft in orbit may cause air leakages, which pose a substantial danger to the crew and the spacecraft. Lamb wave dispersion in spacecraft structures and the randomness of leak holes are the difficulties in leak location. To solve [...] Read more.
Clashes between space debris and spacecraft in orbit may cause air leakages, which pose a substantial danger to the crew and the spacecraft. Lamb wave dispersion in spacecraft structures and the randomness of leak holes are the difficulties in leak location. To solve these problems, a frequency weighting matrix beamforming algorithm is proposed in this paper. The elastic Lamb waves that are caused by leakages are acquired by an ‘L’ shaped sensor array consisting of eight acoustic emission sensors. The angle of a leak can be obtained through the superposition of different time delays, and the intersection of two angles can be used to find the location of the leak. Traditional beamforming is improved by matching the wave speeds in different frequency bands and weightings according to the energy distribution. Narrowband filtering is used to delay overlay different signal speeds with different frequency bands via a dispersion curve. The weighting method is used to compensate the frequency band response of different leak holes. The detailed location algorithm process is introduced and verified by experiments. For 1.5 and 2 mm leak holes, location direction accuracies of 1.33° and 1.93° for one sensor array were obtained, respectively. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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16 pages, 8288 KiB  
Article
Substructuring of a Petrol Engine: Dynamic Characterization and Experimental Validation
by Enrico Armentani, Venanzio Giannella, Roberto Citarella, Antonio Parente and Mauro Pirelli
Appl. Sci. 2019, 9(22), 4969; https://doi.org/10.3390/app9224969 - 19 Nov 2019
Cited by 9 | Viewed by 3158
Abstract
In this work, the vibration behavior of a 4-cylinder, 4-stroke, petrol engine was simulated by leveraging on the Finite Element Method (FEM). A reduced modelling strategy based on the component mode synthesis (CMS) was adopted to reduce the size of the full FEM [...] Read more.
In this work, the vibration behavior of a 4-cylinder, 4-stroke, petrol engine was simulated by leveraging on the Finite Element Method (FEM). A reduced modelling strategy based on the component mode synthesis (CMS) was adopted to reduce the size of the full FEM model of the engine. Frequency response function (FRF) analyses were used to identify the resonant frequencies and corresponding modes of the different FEM models, and the obtained results were compared with experimental data to get the model validation. Subsequently, modal-based frequency forced response analyses were performed to consider the loads acting during the real operating conditions of the engine. Finally, the impact on vibrations at the mounts, produced by an additional bracket connecting the engine block and gearbox, was also investigated. Both the full and reduced FEM model demonstrated and reproduced with high accuracy the vibration response at the engine mounts, providing a satisfactory agreement with the vibrations measured experimentally. The reduced modelling strategy required significantly shorter runtimes, which decreased from 24 h for the full FEM model to nearly 2 h for the reduced model. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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20 pages, 11446 KiB  
Article
Postponing the Onset and Alleviating the Load of Transonic Buffet by Using Steady and Periodic Tangential Slot Blowing
by Huixue Dang, Junhai Zhao, Zhichun Yang and Huibo Dang
Appl. Sci. 2019, 9(19), 4132; https://doi.org/10.3390/app9194132 - 02 Oct 2019
Cited by 2 | Viewed by 2746
Abstract
Transonic buffet not only influences the structural integrity, handling quality and ride comfort, but also limits the flight envelope of transporters and airliners. To delay buffet onset and alleviate the buffet load, the effects of both steady and periodic tangential slot blowing are [...] Read more.
Transonic buffet not only influences the structural integrity, handling quality and ride comfort, but also limits the flight envelope of transporters and airliners. To delay buffet onset and alleviate the buffet load, the effects of both steady and periodic tangential slot blowing are investigated. The results show that steady tangential blowing on the airfoil upper surface can postpone the buffet onset margin and evidently increase the lift coefficient at incidence angles near and above the buffet onset case of the clean airfoil. Under buffeting conditions of the clean airfoil, unsteady aerodynamic loads can be greatly suppressed by both steady and periodic blowing. The control effort is depicted as reduced wedge effect and weakened dynamic effect. The buffet mechanism includes (a) the feedback loop between the Kutta wave and the separation bubble under the shock foot, and (b) the interaction between the shear layer shed by the shockwave and Kutta waves. Under blowing conditions, the upstream creeping Kutta waves are prevented, and the intensity of the shear layer shed by the shockwave into separated flows is evidently reduced. Parametric studies show that the control effect is reduced as the blowing slot moves downstream, and steady blowing at 41% x/c is the most favorable control case. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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21 pages, 10233 KiB  
Article
Analysis of Aerodynamic Noise Characteristics of High-Speed Train Pantograph with Different Installation Bases
by Yongfang Yao, Zhenxu Sun, Guowei Yang, Wen Liu and Prasert Prapamonthon
Appl. Sci. 2019, 9(11), 2332; https://doi.org/10.3390/app9112332 - 06 Jun 2019
Cited by 17 | Viewed by 5302
Abstract
The high-speed-train pantograph is a complex structure that consists of different rod-shaped and rectangular surfaces. Flow phenomena around the pantograph are complicated and can cause a large proportion of aerodynamic noise, which is one of the main aerodynamic noise sources of a high-speed [...] Read more.
The high-speed-train pantograph is a complex structure that consists of different rod-shaped and rectangular surfaces. Flow phenomena around the pantograph are complicated and can cause a large proportion of aerodynamic noise, which is one of the main aerodynamic noise sources of a high-speed train. Therefore, better understanding of aerodynamic noise characteristics is needed. In this study, the large eddy simulation (LES) coupled with the acoustic finite element method (FEM) is applied to analyze aerodynamic noise characteristics of a high-speed train with a pantograph installed on different configurations of the roof base, i.e. flush and sunken surfaces. Numerical results are presented in terms of acoustic pressure spectra and distributions of aerodynamic noise in near-field and far-field regions under up- and down-pantograph as well as flushed and sunken pantograph base conditions. The results show that the pantograph with the sunken base configuration provides better aerodynamic noise performances when compared to that with the flush base configuration. The noise induced by the down-pantograph is higher than that by the up-pantograph under the same condition under the pantograph shape and opening direction selected in this paper. The results also indicate that, in general, the directivity of the noise induced by the down-pantograph with sunken base configuration is slighter than that with the flush configuration. However, for the up-pantograph, the directivity is close to each other in Y-Z or X-Z plane whether it is under flush or sunken roof base condition. However, the sunken installation is still conducive to the noise environment on both sides of the track. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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33 pages, 12274 KiB  
Article
Vibroacoustic Optimization Study for the Volute Casing of a Centrifugal Fan
by Jianhua Zhang, Wuli Chu, Jinghui Zhang and Yi Lv
Appl. Sci. 2019, 9(5), 859; https://doi.org/10.3390/app9050859 - 27 Feb 2019
Cited by 12 | Viewed by 6180
Abstract
A numerical optimization is presented to reduce the vibrational noise of a centrifugal fan volute. Minimal vibrational radiated sound power was considered as the aim of the optimization. Three separate parts of volute panel thickness (ST: the side panel thickness; BT: the back [...] Read more.
A numerical optimization is presented to reduce the vibrational noise of a centrifugal fan volute. Minimal vibrational radiated sound power was considered as the aim of the optimization. Three separate parts of volute panel thickness (ST: the side panel thickness; BT: the back panel thickness; FT: the front panel thickness) were taken as the design variables. Then, a vibrational noise optimization control method for the volute casing was proposed that considered the influence of vibroacoustic coupling. The optimization method was mainly divided into three main parts. The first was based on the simulation of unsteady flow to the fan to obtain the vibrational noise source. The second used the design of experiments (DoE) method and a weighted-average surrogate model (radial basis function, or RBF) with three design variables related to the geometries of the three-part volute panel thickness, which was used to provide the basic mathematical model for the optimization of the next part. The third part, implementing the low vibrational noise optimization for the fan volute, applied single-objective (taking volute radiated acoustical power as the objective function) and multi-objective (taking the volute radiated acoustical power and volute total mass as the objective function) methods. In addition, the fan aerodynamic performance, volute casing surface fluctuations, and vibration response were validated by experiments, showing good agreement. The optimization results showed that the vibrational noise optimization method proposed in this study can effectively reduce the vibration noise of the fan, obtaining a maximum value of noise reduction of 7.3 dB. The optimization in this study provides an important technical reference for the design of low vibroacoustic volute centrifugal compressors and fans whose fluids should be strictly kept in the system without any leakage. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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16 pages, 7841 KiB  
Article
Analytic Model and the Influence of Actuator Number on the Performance of Plasma Synthetic Jet Actuator Array
by Shengfang Huang, Zhibo Zhang, Huimin Song, Yun Wu, Zhengzhong Sun and Yinghong Li
Appl. Sci. 2018, 8(9), 1534; https://doi.org/10.3390/app8091534 - 01 Sep 2018
Cited by 4 | Viewed by 2778
Abstract
Coupled with the multichannel discharge model and plasma synthetic jet actuator (PSJA) aerodynamic model, an analytical model to predict the performance of the PSJA array is put forward. The multichannel discharge model takes these factors into consideration, the delay time in the breakdown [...] Read more.
Coupled with the multichannel discharge model and plasma synthetic jet actuator (PSJA) aerodynamic model, an analytical model to predict the performance of the PSJA array is put forward. The multichannel discharge model takes these factors into consideration, the delay time in the breakdown process, the electrical transformation of the discharge channel from a capacitor to a resistor induced by the air breakdown, and the varying plasma resistance in the discharge process. The PSJA aerodynamic model is developed based on the conservation equations of mass, momentum, energy, and the lumped capacitance method. The multichannel discharge model can simulate the multichannel discharge process and give the discharge energy in the plasma channel. With a constant heating efficiency, the time-independent heating energy deposition power in a discharge channel is obtained. Importing the heating energy, the PSJA aerodynamic model presents the evolution process of the jet. Simulation results show that the jet strength induced by a single actuator decreases with the number of actuators in the PSJA array. When the actuator number increases from 1 to 20, the weakening extent of mass ejected, peak jet velocity, and jet duration time is 62%, 54%, and 33%, respectively. The discharge efficiency increases with the actuator number, while the thermodynamic efficiency decreases with the actuator number. As a result, the total energy efficiency doesn’t always increase with an increase in the number of actuators. When the discharge efficiency of a conventional one channel discharge has been a relatively large value, the total energy efficiency actually decreases with the growth of actuator number. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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21 pages, 12646 KiB  
Article
Multibody Simulation for the Vibration Analysis of a Turbocharged Diesel Engine
by Enrico Armentani, Francesco Caputo, Luca Esposito, Venanzio Giannella and Roberto Citarella
Appl. Sci. 2018, 8(7), 1192; https://doi.org/10.3390/app8071192 - 20 Jul 2018
Cited by 26 | Viewed by 5274
Abstract
In this paper, a multibody calculation methodology has been applied to the vibration analysis of a 4-cylinder, 4-stroke, turbocharged diesel engine, with a simulation driven study of the angular speed variation of a crankshaft under consideration of different modeling assumptions. Moreover, time dependent [...] Read more.
In this paper, a multibody calculation methodology has been applied to the vibration analysis of a 4-cylinder, 4-stroke, turbocharged diesel engine, with a simulation driven study of the angular speed variation of a crankshaft under consideration of different modeling assumptions. Moreover, time dependent simulation results, evaluated at the engine supports, are condensed to a vibration index and compared with experimental results, obtaining satisfactory outcomes. The modal analysis also considers the damping aspects and has been conducted using a multibody model created with the software AVL/EXCITE. The influence of crankshaft torsional frequencies on the rotational speed behavior has been evaluated in order to reduce the vibration phenomena. The focus of this work is related to industrial aspects since, for an existing and commercialized engine, a numerical and experimental complex study has been performed to enable design improvements aimed at reducing noise and vibrations. Existing procedures and algorithms are combined here to reach the abovementioned objectives in the most efficient way. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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17 pages, 6660 KiB  
Article
A Study on Optimal Compensation Design for Meteorological Satellites in the Presence of Periodic Disturbance
by Shijie Xu, Naigang Cui, Youhua Fan and Yingzi Guan
Appl. Sci. 2018, 8(7), 1190; https://doi.org/10.3390/app8071190 - 20 Jul 2018
Cited by 3 | Viewed by 2763
Abstract
Periodic disturbance may cause serious effects on the attitude of meteorological satellites, and the attenuation of periodic disturbance is required. In this paper, a fundamental study on the optimal design of constant compensations against known-law periodic disturbance for meteorological satellites is investigated. An [...] Read more.
Periodic disturbance may cause serious effects on the attitude of meteorological satellites, and the attenuation of periodic disturbance is required. In this paper, a fundamental study on the optimal design of constant compensations against known-law periodic disturbance for meteorological satellites is investigated. An analytical solution for the relationship between the frequency and amplitude ratios and the response of a typical second-order vibration system is firstly derived. The compensation and disturbance torques are determined according to practical engineering. The criteria for designing the optimal compensations are based on the analytical and simulation results. Then, the criteria are applied to a flexible spacecraft actuated by constant control torque in the presence of sustained periodic disturbance. The optimal compensation torque parameters for spacecraft are acquired based on former criteria. The compensate effectiveness of the optimal compensation torque is provided and compared with results of other selections in the frequency and amplitude ratio domain. Numerical simulation results and experimental results clearly demonstrate the good performance of proposed criteria. This work provides a significant reference for the vibration attenuation of meteorological satellites in the present of periodic disturbance. Full article
(This article belongs to the Special Issue Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems)
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