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Articles de revues sur le sujet « NOISE LANDING GEAR »

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Auteur : Grafiati

Publié le 11 septembre 2023

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1

Mu, Yongfei, Jie Li, Wutao Lei et Daxiong Liao. « The effect of doors and cavity on the aerodynamic noise of fuselage nose landing gear ». International Journal of Aeroacoustics 20, n^o 3-4 (15 mars 2021) : 345–60. http://dx.doi.org/10.1177/1475472x211003297.

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The aerodynamic noise of landing gears have been widely studied as an important component of the airframe noise. During take-off and landing, there are doors, cavity and fuselage around the landing gear. The noise caused by these aircraft components will interfere with aerodynamic noise generated by the landing gear itself. Hence, paper proposes an Improved Delayed Detached Eddy Simulation (IDDES) method for the investigation of the flow field around a single fuselage nose landing gear (NLG) model and a fuselage nose landing gear model with doors, cavity and fuselage nose (NLG-DCN) respectively. The difference between the two flow fields were analyzed in detail to better understand the influence of these components around the aircraft’s landing gear, and it was found that there is a serious mixing phenomenon among the separated flow from the front doors, the unstable shear layer falling off the leading edge of the cavity and the wake of the main strut which directly leads to the enhancement of the noise levels. Furthermore, after the noise sound waves are reflected by the doors several times, an interference phenomenon is generated between the doors. This interference may be a reason why the tone excited in the cavity is suppressed.

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2

Kopiev, Victor, Ivan Belyaev, Mikhail Zaytsev et Kun Zhao. « An Aeroacoustic Study of Full-Scale and Small-Scale Generic Landing Gear Models with Identical Geometry ». Applied Sciences 13, n^o 4 (10 février 2023) : 2295. http://dx.doi.org/10.3390/app13042295.

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The paper reports on the results of acoustic measurements of full-scale and small-scale generic landing gear models, which have identical geometry and differ only by their scales. The large-scale landing gear models were simplified and lack small geometric details, which for the first time allows their results to be directly compared with those for the small-scale models of the same geometry. It is shown that after application of the scaling procedure to their noise spectra, the normalized results for broadband noise of the landing gear models of different scales are in good agreement with each other. This result seems to support the feasibility of developing technologies for low-frequency noise reduction of landing gears based on small-scale tests and allowing refinement of semi-empirical models of noise prediction for different landing gear elements.

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3

Yang, Guang Jun, Jian Jun Liu et Jing Sun. « Computational Aeroacoustic Simulation of Landing Gear ». Applied Mechanics and Materials 421 (septembre 2013) : 110–15. http://dx.doi.org/10.4028/www.scientific.net/amm.421.110.

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RANS / NLAS numerical simulation method is adopted in this paper to carry out study on the aerodynamic noise analysis of basic landing gear configuration. Reynolds average N-S equation is solved with nonlinear turbulence model to establish the landing gear initial flow field, based on which, the NLAS (nonlinear acoustic solver) processed the turbulence fluctuation reconstruction to obtain the near-field acoustic characteristics of landing gear. Combined with the flow characteristics and the associated noise spectrum analysis, aerodynamic noise characteristics of landing gear are achieved. The work in this paper can provide useful research foundation on the following noise reduction design of landing gear.

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4

TIAN, Siyuan, Peixun YU, Junqiang BAI, Xiaofeng REN, Anyu BAO et Xiao HAN. « Analysis of aerodynamic and aeroacoustics of full scale landing gear ». Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 40, n^o 5 (octobre 2022) : 953–61. http://dx.doi.org/10.1051/jnwpu/20224050953.

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The aerodynamic noise of a landing gear is an important source of airframe noise. The analysis of its noise characteristics plays an important role in the design of a low-noise landing gear. Based on the FL-52 acoustic wind tunnel test technology, the coupled scale adaptive model and the acoustic disturbance equation, the results on aerodynamic noise of a full-scale landing gear model are analyzed. The high-fidelity model includes transverse strut, torsion arm, piston rod, wheel and other parts. The characteristics of static pressure distribution, power spectrum density of pulsating pressure, aerodynamic noise source distribution and directivity of overall sound pressure level are analyzed. The noise characteristics of the far-field microphone are compared with the local microphone installed in the wheel cavity. In this way, we characterize the directivity of pure tone in the wheel cavity and understand its contribution to the far-field noise. The results show that the aerodynamic noise of the landing gear can be quantified accurately by the hybrid numerical method. The pure tone has two frequencies inside and outside the wheel of the landing gear: 560 Hz and 960 Hz. The peak of the loudest sound pressure level reaches 136 dB, and the pure tone radiates to the surface of the non-separation area of the wheel of the landing gear. However, the wall pressure spectrum of the points located in the turbulence region shows a wide-frequency characteristic, and there is no obvious pure tone. From the point of view of the far-field noise directivity, the forward noise of the landing gear is larger than the rear noise, and there is a small overall sound pressure level area at the points of 65 and 110 degrees respectively. When the monitoring points are far away, the far-field noise of the landing gear shows the characteristics of wide frequency, and no obvious pure tone appears. The method can provide the technical support for predicting the aeroacoustics of a landing gear and designing a low-noise land gear.

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5

Hu, Ning, Xuan Hao, Cheng Su, Wei Min Zhang et Han Dong Ma. « Near-Field Noise Prediction for Landing Gear Based on Detached Eddy Simulations ». Applied Mechanics and Materials 472 (janvier 2014) : 105–10. http://dx.doi.org/10.4028/www.scientific.net/amm.472.105.

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A four-wheel rudimentary landing gear is studied numerically by detached eddy simulation (DES) based on the Spalart-Allmaras turbulence model. The surface sound pressure level and sound pressure spectra are calculated using the obtained unsteady flow field. The investigation shows that DES can describe the steady and unsteady properties in the flow around rudimentary landing gear. It can give reasonable results since the flow around the landing gear is a massive separated flow. The results prove the feasibility of DES type methods in massive separated unsteady flow field and aerodynamic noise prediction for landing gear, and can be used in the study of landing gear noise reduction.

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6

Merino-Martínez, Roberto, Eleonora Neri, Mirjam Snellen, John Kennedy, Dick G. Simons et Gareth J. Bennett. « Multi-Approach Study of Nose Landing Gear Noise ». Journal of Aircraft 57, n^o 3 (mai 2020) : 517–33. http://dx.doi.org/10.2514/1.c035655.

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7

Liang, Yong, Kun Zhao, Yingchun Chen, Longjun Zhang et Gareth J. Bennett. « An Experimental Characterization on the Acoustic Performance of Forward/Rearward Retraction of a Nose Landing Gear ». International Journal of Aerospace Engineering 2019 (4 juillet 2019) : 1–11. http://dx.doi.org/10.1155/2019/4135094.

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The modern undercarriage system of a large aircraft normally requires the landing gear to be retractable. The nose landing gear, installed in the front of the fuselage, is retracted either forward or rearward. In the forward/rearward retraction system, the landing gear is normally installed to the trailing/leading side of the bay. When the incoming flow passes the landing gear as well as the bay, the installation that corresponds to the forward/rearward retraction system has a significant impact on the coupling flow and the associated noise of the landing gear and the bay. In this paper, acoustic performance of the forward/rearward retraction of the nose landing gear was discussed based on experiment. The landing gear bay was simplified as a rectangular cavity, and tests were conducted in an aeroacoustics wind tunnel. The cavity oscillation was first analyzed with different incoming speeds. Then, the landing gear model was installed close to the trailing and the leading side of the cavity, respectively. It was observed that installation close to the leading side can help disturb the shear layer so as to suppress the oscillation, while the trailing one can make the landing gear itself produce lower noise. Accordingly, conclusions on the acoustic performance of the forward/rearward retraction of the nose landing gear are made.

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8

Long, Shuang Li, Hong Nie et Xin Xu. « Aeroacoustic Study on a Simplified Nose Landing Gear ». Applied Mechanics and Materials 184-185 (juin 2012) : 18–23. http://dx.doi.org/10.4028/www.scientific.net/amm.184-185.18.

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Simulation analysis and experiment research are performed on the aeroacoustic noise of a landing gear component in this paper. Detached Eddy Simulation (DES) is used to produce the flow field of the model. The Ffowcs-Williams/Hawkings (FW-H) equation is used to calculate the acoustic field. The sound field radiated from the model is measured in the acoustic wind tunnel. A comparison shows that the simulation results agree well with the experiment results under the acoustic far field condition. The results show that the noise radiated from the model is broadband noise. The directivity of the noise source is like a type of dipole. The wheel is the largest contributor and the strut is the least contributor to the landing gear noise. The results can provide some reference for low noise landing gear design.

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9

Bennett, Gareth J., Eleonora Neri et John Kennedy. « Noise Characterization of a Full-Scale Nose Landing Gear ». Journal of Aircraft 55, n^o 6 (novembre 2018) : 2476–90. http://dx.doi.org/10.2514/1.c034750.

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10

Huang, Longlong, Kun Zhao, Junbiao Liang, Victor Kopiev, Ivan Belyaev et Tian Zhang. « A Numerical Study of the Wind Speed Effect on the Flow and Acoustic Characteristics of the Minor Cavity Structures in a Two-Wheel Landing Gear ; ». Applied Sciences 11, n^o 23 (26 novembre 2021) : 11235. http://dx.doi.org/10.3390/app112311235.

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The landing gear is widely concerned as the main noise source of airframe noise. The flow characteristics and aerodynamic noise characteristics of the landing gear were numerically simulated based on Large Eddy Simulation and Linearized Euler Equation, and the feasibility of the simulation model was verified by experiments. Then the wind speed effect on the flow and acoustic characteristics of the minor cavity structures in a two-wheel landing gear were analyzed. The results show that the interaction of vortices increases with the increase of velocity at the brake disc, resulting in a slight increase in the amplitude of pressure fluctuation at 55 m·s−1~75 m·s−1. With the increase of speed, the obstruction at the lower hole of torque link decreases, and many vortical structures flow out of the lower hole and are dissipated, so that the pressure fluctuation amplitude of 75 m·s−1 almost does not increase relative to 55 m·s−1. The contribution of each part in the landing gear to the overall noise is as follows: shock strut > tire > torque link > brake disc. At the speed of 34 m·s−1~55 m·s−1, the contribution of each component to the total noise increases with the increase of speed, and the small components such as torque link and brake disc contribute more to the total noise. At the speed of 55 m·s−1~75 m·s−1, the increase of overall noise mainly comes from the main components such as shock strut and tire, and the brake disc and torque link contribute very little to the overall noise. It provides a reference for the further noise reduction optimization design of the landing gear.

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11

Souliez, F. J., L. N. Long, P. J. Morris et A. Sharma. « Landing Gear Aerodynamic Noise Prediction Using Unstructured Grids ». International Journal of Aeroacoustics 1, n^o 2 (août 2002) : 115–35. http://dx.doi.org/10.1260/147547202760236932.

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Aerodynamic noise from a landing gear in a uniform flow is computed using the Ffowcs Williams-Hawkings (FW-H) equation. The time accurate flow data on the integration surface is obtained using a finite volume low-order flow solver on an unstructured grid. The Ffowcs Williams-Hawkings equation is solved using surface integrals over the landing gear surface and over a permeable surface away from the landing gear. Two geometric configurations are tested in order to assess the impact of two lateral struts on the sound level and directivity in the far-field. Predictions from the Ffowcs Williams-Hawkings code are compared with direct calculations by the flow solver at several observer locations inside the computational domain. The permeable Ffowcs Williams-Hawkings surface predictions match those of the flow solver in the near-field. Far-field noise calculations coincide for both integration surfaces. The increase in drag observed between the two landing gear configurations is reflected in the sound pressure level and directivity mainly in the streamwise direction.

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12

Guo, Zhifei, Peiqing Liu, Jin Zhang et Hao Guo. « Numerical simulation of aeroacoustic noise from landing gear and rectangular cavity ». Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering 234, n^o 7 (17 janvier 2020) : 1259–71. http://dx.doi.org/10.1177/0954410019900722.

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This paper is aimed at researching the interaction between aeroacoustic noise radiated from a rectangular cavity (gear bay) and from landing gear. It is a complicated flow-induced noise problem, involving the nonlinear, unsteady evolution of the turbulent structure inside the airflow bypassing the landing gear and the cavity. The generation and radiation mechanism of aeroacoustic noise are also concerned. In fact, it is a problem about the nonlinear interaction between the vortices shedding from the boundary layer of bluff bodies and the cavity-limited shear layer. To simplify this issue, a two-wheel landing gear named LAGOON is chosen as the landing gear model. The unsteady flow field and aerodynamic noise from it is simulated by applying the commercial software ANSYS Fluent. Good agreement is achieved between the numerical simulation and wind tunnel measurements in terms of the aerodynamic and aeroacoustic results. According to the size of LAGOON, a simple rectangular cavity is designed as the landing gear bay. Both the cavity combined with LAGOON and the cavity alone are simulated and compared. The results show that under the blocking effect of a strut, most small pieces of vortices at the trailing edge of the cavity bottom would dissipate rather than move forward along with the backflow, leading to the correlation of cavity resonance being more contrasting and increasing its amplitude. The blockage effect induced by rear wall could also enhance the turbulence kinetic energy at the wake of the strut, thus increasing the low-frequency noise radiated from the strut and cavity.

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13

Guo, Y. P., K. J. Yamamoto et R. W. Stoker. « Experimental Study on Aircraft Landing Gear Noise ». Journal of Aircraft 43, n^o 2 (mars 2006) : 306–17. http://dx.doi.org/10.2514/1.11085.

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14

Molin, Nicolas. « Landing gear noise assessment on Airbus aircraft ». Journal of the Acoustical Society of America 123, n^o 5 (mai 2008) : 3393. http://dx.doi.org/10.1121/1.2934068.

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15

Spalart, Philippe R., Mikhail L. Shur, Mikhail K. Strelets et Andrey K. Travin. « Towards noise prediction for rudimentary landing gear ». Procedia Engineering 6 (2010) : 283–92. http://dx.doi.org/10.1016/j.proeng.2010.09.030.

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16

Spalart, Philippe R., Mikhail L. Shur, Mikhail Kh Strelets et Andrey K. Travin. « Initial noise predictions for rudimentary landing gear ». Journal of Sound and Vibration 330, n^o 17 (août 2011) : 4180–95. http://dx.doi.org/10.1016/j.jsv.2011.03.012.

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17

Chow, Leung Choi, et Jon Higgins. « Reduction of airframe noise from landing gear ». Air & ; Space Europe 2, n^o 6 (novembre 2000) : 53–56. http://dx.doi.org/10.1016/s1290-0958(01)80038-1.

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18

Boorsma, K., X. Zhang et N. Molin. « Landing gear noise control using perforated fairings ». Acta Mechanica Sinica 26, n^o 2 (16 octobre 2009) : 159–74. http://dx.doi.org/10.1007/s10409-009-0304-0.

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19

Zhao, Kun, Yong Liang, Tingrui Yue, Zhengwu Chen et Gareth J. Bennett. « Characterization of the aircraft bay/landing gear coupling noise at low subsonic speeds and its suppression using leading-edge chevron spoiler ». Advances in Mechanical Engineering 11, n^o 8 (août 2019) : 168781401987143. http://dx.doi.org/10.1177/1687814019871431.

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When the aircraft opens the bay door to let the landing gear either drop or retract, the incoming flow will result in a significant amount of coupling noise from the bay and the landing gear. Here, an experimental study was reported to characterise the acoustic performance and flow field at low subsonic speeds. Also, we examined a passive control method leading-edge chevron spoiler to suppress the noise. The experiment was performed in a low-speed aeroacoustic wind, the bay was simplified as a rectangular cavity and the spoiler was mounted to the leading edge. Both acoustic and aerodynamic measurements were performed through two microphone arrays, pressure transducers and particle image velocimetry. It was found that installation of the landing gear model can attenuate cavity oscillation noise to some extent by disturbing the shear layer of the cavity leading edge. Moreover, acoustic measurement confirmed the noise control when the spoiler was used. In addition, a parametric study on the effects of chevron topology was performed, and an optimised value was found for each parameter. From the aerodynamic measurement, the noise reduction was explained from the perspective of fluid dynamics. It was observed that installation of the chevron can raise the leading-edge shear layer and break up the large-scale vortices, thereby controlling the Rossiter mode noise and the landing gear model noise at certain frequencies.

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20

Li, Long Shuang, Hong Nie et Xin Xu. « Simulation and Experiment on Landing Gear Component Noise ». Applied Mechanics and Materials 170-173 (mai 2012) : 3454–59. http://dx.doi.org/10.4028/www.scientific.net/amm.170-173.3454.

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Simulation analysis and experiment research are performed on the aeroacoustic noise of a landing gear component in this paper. Detached Eddy Simulation (DES) is used to produce the flow field of the model. The Ffowcs-Williams/Hawkings (FW-H) equation is used to calculate the acoustic field. The sound field radiated from the model is measured in the acoustic wind tunnel. A comparison shows that the simulation results agree well with the experiment results under the acoustic far field condition. The results show that the noise radiated from the model is broadband noise. The directivity of the noise source is like a type of dipole. The location between shock absorber and strut, shock absorber and bogie can induce the interaction noise which is presented by two energy peaks in the spectra. The shock absorber and the bogie is the main contributor while the strut is the least contributor to the total noise.

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Sasaki, Daisuke, Deguchi Akihito, Hiroshi Onda et Kazuhiro Nakahashi. « Landing Gear Aerodynamic Noise Prediction Using Building-Cube Method ». Modelling and Simulation in Engineering 2012 (2012) : 1–16. http://dx.doi.org/10.1155/2012/632387.

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Landing gear noise prediction method is developed using Building-Cube Method (BCM). The BCM is a multiblock-structured Cartesian mesh flow solver, which aims to enable practical large-scale computation. The computational domain is composed of assemblage of various sizes of building blocks where small blocks are used to capture flow features in detail. Because of Cartesian-based mesh, easy and fast mesh generation for complicated geometries is achieved. The airframe noise is predicted through the coupling of incompressible Navier-Stokes flow solver and the aeroacoustic analogy-based Curle’s equation. In this paper, Curle’s equation in noncompact form is introduced to predict the acoustic sound from an object in flow. This approach is applied to JAXA Landing gear Evaluation Geometry model to investigate the influence of the detail components to flows and aerodynamic noises. The position of torque link and the wheel cap geometry are changed to discuss the influence. The present method showed good agreement with the preceding experimental result and proved that difference of the complicated components to far field noise was estimated. The result also shows that the torque link position highly affects the flow acceleration at the axle region between two wheels, which causes the change in SPL at observation point.

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Isotani, Kazuhide, Kenji Hayama, Akio Ochi et Toshiyuki Kumada. « 1002 Aerodynamic noise reduction for aircraft landing gear ». Proceedings of the Fluids engineering conference 2009 (2009) : 321–22. http://dx.doi.org/10.1299/jsmefed.2009.321.

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23

Guo, Yueping. « A statistical model for landing gear noise prediction ». Journal of Sound and Vibration 282, n^o 1-2 (avril 2005) : 61–87. http://dx.doi.org/10.1016/j.jsv.2004.02.021.

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Chen, Tao, Hong Hou, Zhi Fei Chen et Cheng Kun Jiang. « Measurement of ARJ21 Aircraft Landing Gear Noise Using Array Signal Processing Technology ». Advanced Materials Research 588-589 (novembre 2012) : 747–50. http://dx.doi.org/10.4028/www.scientific.net/amr.588-589.747.

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Flyover noise measurements were conducted on an aircraft ARJ21 aiming at landing gear noise prediction schemes. The analysis is based on acoustic dedopplerized spectra and localization maps was calculated with the pressure signals of a acoustic phased array with 30 microphones. The acoustic phased array is a spatially distributed set of microphones which simultaneously sample the acoustic field. The doppler shifts was removed using linear interpolation.By appropriately time delaying the output of individual microphones, the origin and level of noise source(the landing gear) can potentially be determined. The success of this approach depends largely on the phased array design, and the array data processing method. This paper focuses on the two areas.

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Moberg, Bengt, Anders Johansson, Johan Rignér et Per Näsman. « Operational noise optimization of aircraft approaches - Initial findings ». INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, n^o 6 (1 août 2021) : 499–507. http://dx.doi.org/10.3397/in-2021-1494.

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As the pilots slow the aircraft down and extend flaps and landing gear in preparation for landing the characteristics of the aircraft as a noise source changes. In the OPNOP project, the possibility to use this variation in noise generation to minimize noise at a specified location is examined. Such analysis requires an increased understanding about aircraft noise generation as the aircraft changes configuration and speed during the approach, where theoretical models available can be overly simplistic and of little use for this purpose. Using flight data from 113 actual Airbus A321 flights, and corresponding noise measurements on the ground, this study reports on the initial findings forming the foundation on which further analysis will be conducted. Intermediary findings relate to: a comparison between models and actual measurements, the distance variability to the runway for various flap selections and extension of the landing gear as well as a comparison between flight data and on-ground noise measurements. Captured data suggest that it should be possible to use speed and configuration recommendations to reduce noise over selected approach areas. Future research will include scenario generation and incorporate flight data from an earlier study to increase validity.

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NING, Fangli. « Numerical Computational Method for Predicting Aircraft Landing Gear Noise ». Journal of Mechanical Engineering 49, n^o 08 (2013) : 171. http://dx.doi.org/10.3901/jme.2013.08.171.

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Dobrzynski, Werner, Leung Choi Chow, Malcolm Smith, Antoine Boillot, Olivier Dereure et Nicolas Molin. « Experimental Assessment of Low Noise Landing Gear Component Design ». International Journal of Aeroacoustics 9, n^o 6 (juillet 2010) : 763–86. http://dx.doi.org/10.1260/1475-472x.9.6.763.

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Morris, Philip J., Kenneth S. Brentner et Leonard V. Lopes. « A design‐oriented approach to landing gear noise prediction ». Journal of the Acoustical Society of America 123, n^o 5 (mai 2008) : 3394. http://dx.doi.org/10.1121/1.2934069.

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Spalart, Philippe R., Mikhail L. Shur, Mikhail K. Strelets et Andrey K. Travin. « Reprint of : Towards Noise Prediction for Rudimentary Landing Gear ». Procedia IUTAM 1 (2010) : 283–92. http://dx.doi.org/10.1016/j.piutam.2010.10.030.

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Li, Yong, Malcolm Smith et Xin Zhang. « Measurement and control of aircraft landing gear broadband noise ». Aerospace Science and Technology 23, n^o 1 (décembre 2012) : 213–23. http://dx.doi.org/10.1016/j.ast.2011.07.009.

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Hedges, L. S., A. K. Travin et P. R. Spalart. « Detached-Eddy Simulations Over a Simplified Landing Gear ». Journal of Fluids Engineering 124, n^o 2 (28 mai 2002) : 413–23. http://dx.doi.org/10.1115/1.1471532.

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The flow around a generic airliner landing-gear truck is calculated using the methods of Detached-Eddy Simulation, and of Unsteady Reynolds-Averaged Navier-Stokes Equations, with the Spalart-Allmaras one-equation model. The two simulations have identical numerics, using a multi-block structured grid with about 2.5 million points. The Reynolds number is 6×105. Comparison to the experiment of Lazos shows that the simulations predict the pressure on the wheels accurately for such a massively separated flow with strong interference. DES performs somewhat better than URANS. Drag and lift are not predicted as well. The time-averaged and instantaneous flow fields are studied, particularly to determine their suitability for the physics-based prediction of noise. The two time-averaged flow fields are similar, though the DES shows more turbulence intensity overall. The instantaneous flow fields are very dissimilar. DES develops a much wider range of unsteady scales of motion and appears promising for noise prediction, up to some frequency limit.

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Takaishi, Takehisa, Hiroki Ura, Kenichiro Nagai, Yuzuru Yokokawa, Mitsuhiro Murayama, Yasushi Ito, Ryotaro Sakai, Hirokazu Shoji et Kazuomi Yamamoto. « Airframe noise measurements on JAXA Jet Flying Test Bed “Hisho” using a phased microphone array ». International Journal of Aeroacoustics 16, n^o 4-5 (juillet 2017) : 255–73. http://dx.doi.org/10.1177/1475472x17718725.

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In 2015, the Japan Aerospace Exploration Agency launched the Flight demonstration of QUiet technology to Reduce nOise from High-lift configurations project to verify by flight demonstration the feasibility of practical noise-reducing aircraft modification concepts. In order to serve as a baseline for comparison before modification, airframe noise sources of the JAXA Jet Flying Test Bed “Hisho” were measured with a 30 m diameter array of 195 microphones mounted on a wooden platform built temporary beside the runway of Noto Satoyama Airport in Japan. A classical Delay and Sum in the time domain beamforming algorithm was adapted for the present study, with weight factors introduced to improve the low-frequency resolution and autocorrelations eliminated to suppress wind noise at high frequencies. In the landing configuration at idle thrust, the main landing gear, nose landing gear, and side edges of the six extended flap panels were found to be the dominant “Hisho” airframe noise sources. Deconvolution by the DAMAS and CLEAN-SC algorithms provided clearer positions of these sound sources at low frequencies. Integration of acoustical maps agreed well with the sound pressure level measured by a microphone placed at the center of the microphone array and gave detailed information about the contribution of each noise source.

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Belyaev, I. V., M. Yu Zaytsev, V. F. Kopiev et I. V. Pankratov. « Experimental Research on Noise Reduction for Realistic Landing Gear Geometries ». Acoustical Physics 65, n^o 3 (mai 2019) : 297–306. http://dx.doi.org/10.1134/s1063771019030011.

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Humphreys, William M., et Thomas F. Brooks. « Noise Spectra and Directivity for a Scale-Model Landing Gear ». International Journal of Aeroacoustics 8, n^o 5 (juillet 2009) : 409–43. http://dx.doi.org/10.1260/147547209788549316.

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Liu, Wen, Jae Wook Kim, Xin Zhang, David Angland et Bastien Caruelle. « Landing-gear noise prediction using high-order finite difference schemes ». Journal of Sound and Vibration 332, n^o 14 (juillet 2013) : 3517–34. http://dx.doi.org/10.1016/j.jsv.2013.01.035.

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Zhao, Kun, Patrick Okolo, Eleonora Neri, Peng Chen, John Kennedy et Gareth J. Bennett. « Noise reduction technologies for aircraft landing gear-A bibliographic review ». Progress in Aerospace Sciences 112 (janvier 2020) : 100589. http://dx.doi.org/10.1016/j.paerosci.2019.100589.

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Pullin, Rhys, Mark J. Eaton, James J. Hensman, Karen M. Holford, Keith Worden et S. L. Evans. « A Principal Component Analysis of Acoustic Emission Signals from a Landing Gear Component ». Applied Mechanics and Materials 13-14 (juillet 2008) : 41–47. http://dx.doi.org/10.4028/www.scientific.net/amm.13-14.41.

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This work forms part of a larger investigation into fracture detection using acoustic emission (AE) during landing gear airworthiness testing. It focuses on the use of principal component analysis (PCA) to differentiate between fracture signals and high levels of background noise. An artificial acoustic emission (AE) fracture source was developed and additionally five sources were used to generate differing AE signals. Signals were recorded from all six artificial sources in a real landing gear component subject to no load. Further to this, artificial fracture signals were recorded in the same component under airworthiness test load conditions. Principal component analysis (PCA) was used to automatically differentiate between AE signals from different source types. Furthermore, successful separation of artificial fracture signals from a very high level of background noise was achieved. The presence of a load was observed to affect the ultrasonic propagation of AE signals.

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Ricciardi, Tulio R., William R. Wolf, Nicholas J. Moffitt, Jordan R. Kreitzman et Paul Bent. « Numerical noise prediction and source identification of a realistic landing gear ». Journal of Sound and Vibration 496 (mars 2021) : 115933. http://dx.doi.org/10.1016/j.jsv.2021.115933.

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Ricciardi, Tulio R., William R. Wolf et Rachelle Speth. « Acoustic Prediction of LAGOON Landing Gear : Cavity Noise and Coherent Structures ». AIAA Journal 56, n^o 11 (novembre 2018) : 4379–99. http://dx.doi.org/10.2514/1.j056957.

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Burley, Casey L., Thomas F. Brooks, William M. Humphreys et John W. Rawls. « ANOPP Landing-Gear Noise Prediction with Comparison to Model-Scale Data ». International Journal of Aeroacoustics 8, n^o 5 (juillet 2009) : 445–75. http://dx.doi.org/10.1260/147547209788549299.

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Hajczak, Antoine, Laurent Sanders et Philippe Druault. « Landing gear interwheel tonal noise characterization with the Boundary Element Method ». Journal of Sound and Vibration 458 (octobre 2019) : 44–61. http://dx.doi.org/10.1016/j.jsv.2019.06.010.

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Guo, Yueping. « RETRACTED : A component-based model for aircraft landing gear noise prediction ». Journal of Sound and Vibration 312, n^o 4-5 (mai 2008) : 801–20. http://dx.doi.org/10.1016/j.jsv.2007.11.013.

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Alqash, Sultan, Sharvari Dhote et Kamran Behdinan. « Predicting Far-Field Noise Generated by a Landing Gear Using Multiple Two-Dimensional Simulations ». Applied Sciences 9, n^o 21 (23 octobre 2019) : 4485. http://dx.doi.org/10.3390/app9214485.

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In this paper, a new approach is proposed to predict the far-field noise of a landing gear (LG) based on near-field flow data obtained from multiple two-dimensional (2D) simulations. The LG consists of many bluff bodies with various shapes and sizes. The analysis begins with dividing the LG structure into multiple 2D cross-sections (C-Ss) representing different configurations. The C-Ss locations are selected based on the number of components, sizes, and geometric complexities. The 2D Computational Fluid Dynamics (CFD) analysis for each C-S is carried out first to obtain the acoustic source data. The Ffowcs Williams and Hawkings acoustic analogy (FW-H) is then used to predict the far-field noise. To compensate for the third dimension, a source correlation length (SCL) is assumed based on a perfectly correlated flow. The overall noise of the LG is calculated as the incoherent sum of the predicted noise from all C-Ss. Flow over a circular cylinder is then studied to examine the effect of the 2D CFD results on the predicted noise. The results are in good agreement with reported experimental and numerical data. However, the Strouhal number (St) is over-predicted. The proposed approach provides a reasonable estimation of the LG far-field noise at a low computational cost. Thus, it has the potential to be used as a quick tool to predict the far-field noise from an LG during the design stage.

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Johansson, Anders. « Aircraft Approach Noise Trials ». INTER-NOISE and NOISE-CON Congress and Conference Proceedings 265, n^o 2 (1 février 2023) : 5893–99. http://dx.doi.org/10.3397/in_2022_0875.

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This article presents the results from a series of aircraft approach trials that were conducted with the aim to investigate noise reduction procedures within the boundaries of a normal ILS approach. The significant decline in air traffic at Stockholm Arlanda, that occurred during the pandemic meant that the empty airspace and the availability of grounded aircrafts could be utilized to perform controlled flights - something that would have been difficult to achieve during normal traffic conditions. The approach trials were performed by two Airbus A321, which alternately carried out interrupted landing procedures starting 17 nautical miles (nm) from the runway threshold. During the trials, the aircraft speed and configuration (high lift devises and landing gear) were varied according to a predetermined schedule. To capture these variations, flight data (FDR) were recorded while the noise on ground was measured at positions approximately once every nautical mile along the flight track. Results suggest that speed and configuration recommendations can be effective to reduce noise, especially for the final 7 nautical miles of the flight track. However, whether a low speed is to be advocated during the entire approach is currently unclear.

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OCHI, Akio, Kazuhide ISOTANI et Kenji HAYAMA. « Development of Landing Gear Noise Reduction Device Based on Unsteady CFD Analysis ». JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 59, n^o 687 (2011) : 102–8. http://dx.doi.org/10.2322/jjsass.59.102.

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Guo, Yueping. « Effects of Local Flow Variations on Landing Gear Noise Prediction and Analysis ». Journal of Aircraft 47, n^o 2 (mars 2010) : 383–91. http://dx.doi.org/10.2514/1.43615.

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IMAMURA, Taro, Tohru HIRAI, Yuzuru YOKOKAWA, Mitsuhiro MURAYAMA et Kazuomi YAMAMOTO. « Numerical Analysis of Steady Flow around a Landing Gear Noise Measurement Model ». JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 57, n^o 671 (2009) : 493–98. http://dx.doi.org/10.2322/jjsass.57.493.

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Bulté, Jean, et Stéphane Redonnet. « Landing Gear Noise Identification Using Phased Array with Experimental and Computational Data ». AIAA Journal 55, n^o 11 (novembre 2017) : 3839–50. http://dx.doi.org/10.2514/1.j055643.

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Spalart, Philippe R., et ew A. Wetzel. « Rudimentary Landing Gear Results at the 2012 BANC-II Airframe Noise Workshop ». International Journal of Aeroacoustics 14, n^o 1-2 (février 2015) : 193–216. http://dx.doi.org/10.1260/1475-472x.14.1-2.193.

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Merino-Martínez, Roberto, John Kennedy et Gareth J. Bennett. « Experimental study of realistic low–noise technologies applied to a full–scale nose landing gear ». Aerospace Science and Technology 113 (juin 2021) : 106705. http://dx.doi.org/10.1016/j.ast.2021.106705.

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