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Dissertations / Theses on the topic 'NOISE LANDING GEAR'

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Published: 11 September 2023

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1

Liu, Wen. "Numerical investigation of landing gear noise." Thesis, University of Southampton, 2011. https://eprints.soton.ac.uk/210942/.

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Noise generated by aircraft landing gears is a major contributor to the overall airframe noise of a commercial aircraft during landing approach. Because of the complex geometry of landing gears, the prediction of landing gear noise has been very difficult and currently relies on empirical tools, which have limited reliability and flexibility on the applications of unconventional gear architectures. The aim of this research is to develop an efficient and accurate numerical method to investigate the generation and far field radiation of the landing gear noise. In this thesis a hybrid approach is

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2

Wang, Meng. "High-order numerical investigations into landing gear wheel noise." Thesis, University of Southampton, 2017. https://eprints.soton.ac.uk/416431/.

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Wheels are significant landing gear noise sources. In this project, high-order numerical simulations were conducted to investigate the landing gear wheel noise generation mechanisms and noise reduction treatments. The high-order solver solves the Navier-Stokes equations on multiblock structured grids. In this work, a modified solver was developed based on cell-centred formulation, which can provide more accurate solutions than cell-vertex space. This solver applies a finite-difference scheme at interior control points and at block interfaces with smooth grid metrics. At discontinuous block int

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3

Boorsma, Koen. "Aeroacoustic control of landing gear noise using perforated fairings." Thesis, University of Southampton, 2008. https://eprints.soton.ac.uk/66081/.

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A study was performed to investigate and optimize the application of perforated fairings for landing gear noise control. The sparse knowledge about this new subject has necessitated a more fundamental study involving a basic fairing-strut configuration, followed by wind tunnel tests on a simplified landing gear configuration incorporating perforated fairings. For the basic configuration, various exchangeable perforated half-cylindrical shells shrouding a circular cylinder were the subject of aerodynamic and acoustic tests. A qualitative and quantitative description has been given of the influe

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4

Fattah, Ryu. "The noise generation by a main landing gear door." Thesis, University of Southampton, 2016. https://eprints.soton.ac.uk/390837/.

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Experimental measurements and numerical simulations were conducted on a simplified main landing gear model that consists of a leg-door, and a main strut in a parallel configuration. The effects of varying the leg-door angle of attack, and the gap distance between the two elements, were initially studied by two-dimensional and low-order numerical simulations, using the unsteady Reynolds-Averaged Navier-Stokes equations. The strut diameter was specified to the same diameter as a full-scale main landing gear, and simulated under a free-stream Mach number of 0.2, and a Reynolds number based on the

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5

Lopes, Leonard Vincent Brentner Kenneth S. "A new approach to complete aircraft landing gear noise prediction." [University Park, Pa.] : Pennsylvania State University, 2009. http://etda.libraries.psu.edu/theses/approved/WorldWideIndex/ETD-4401/index.html.

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6

Ravetta, Patricio A. "LORE Approach for Phased Array Measurements and Noise Control of Landing Gears." Diss., Virginia Tech, 2005. http://hdl.handle.net/10919/29975.

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A novel concept in noise control devices for landing gears is presented. These devices consist of elastic membranes creating a fairing around the major noise sources. The purpose of these devices is to reduce wake interactions and to hide components from the flow, thus, reducing the noise emission. The design of these fairings was focused on the major noise sources identified in a 777 main landing gear. To find the major noise sources, an extensive noise source identification process was performed using phased arrays. To this end, phased array technologies were developed and a 26%-scale 777 ma

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7

Remillieux, Marcel Christophe. "Aeroacoustic Study of a Model-Scale Landing Gear in a Semi-Anechoic Wind Tunnel." Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/31674.

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An aeroacoustic study was conducted on a 26%-scale Boeing 777 main landing gear in the Virginia Tech (VT) Anechoic Stability Wind Tunnel. The VT Anechoic Stability Wind Tunnel allowed noise measurements to be carried out using both a 63-elements microphone phased array and a linear array of 15 microphones. The noise sources were identified from the flyover view under various flow speeds and the phased array positioned in both the near and far-field. The directivity pattern of the landing gear was determined using the linear array of microphones. The effectiveness of 4 passive noise control

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8

Van, Mierlo Koen. "Computational analysis of the flow field and noise radiation of a generic main landing gear configuration." Thesis, University of Southampton, 2014. https://eprints.soton.ac.uk/388076/.

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This study investigates the flow field and acoustics of a generic four wheel main landing gear. The landing gear is an important airframe noise source during the approach phase. The characteristics of the flow field around the bogie area of the main landing gear are largely unknown. CFD simulations using the DES turbulence model have been used to calculate the unsteady flow field around a generic landing gear model. The surface pressure data has been sampled and used in a FW-H solver to determine far field noise levels. Two different landing gear models have been used, a simplified geometry an

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9

Bouchouireb, Hamza. "Identification and modelling of noise sources on a realisticnose landing gear using phased array methods applied tocomputational data." Thesis, KTH, MWL Marcus Wallenberg Laboratoriet, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-209186.

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Due to the recent development of quieter turbofan engines, airframe noise has started to emerge asthe most important noise source. This is particularly true during the approach/landing phase, whenthe engines are operated at low-thrust levels. In order to meet future noise level regulations, thecharacterization and subsequent reduction of landing gear induced noise is necessary. Wind-tunnelaeroacoustic tests have always been the favoured method for assessing and studying the noise generatedby landing gears, but their prohibitive cost has steered the attention towards numerical methods.Since dir

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10

Čavojský, Tomáš. "Návrh podvozku malého dvoumístného letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-442821.

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This diploma thesis deals with the landing gear design of the small two-seat aircraft. The introduction focuses on the conceptual gear design and shock absorber computational dynamic characteristic model. The practical part is focused on the landing gear construction according to the selected parameters based on the conceptual and computational model. The diploma thesis ends with strength calculations and production documentation.

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11

Nguyen, Thoai D. "Finite Element Analysis of a Nose Gear During Landing." UNF Digital Commons, 2010. http://digitalcommons.unf.edu/etd/215.

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Nose gear failure is a high concern in the aviation industries. According to the Federal Aviation Administration reports, 55% of aircraft failures occur during takeoff and landing while 45% of failures occur during flight. The objective of this thesis is to determine the stress behavior and the displacement of a nose gear of an aircraft during landing using structural finite element analysis. The nose gear was first modeled using computer-aided design software and then imported into finite element software. The external forces were determined analytically and the interactions between component

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12

Trojánek, Tomáš. "Návrh podvozku malého dvoumístného letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-377755.

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The aim of this master thesis is modification of landing gear for accomplishment CS-23 regula-tion from that purpose, because landing gear in the use can't pass this type of certification. The first part examines the alternatives of landing gear with consideration optimal technical and eco-nomical difficulty. After finding optimal type of landing gear with shock absorber is there part of designing and computing the load. Last part of thesis is about stress analysis of whole con-cept and reconsidering final changes.

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13

Novák, Josef. "Návrh podvozku VUT200 TwinCobra." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232017.

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The goal of following master thesis is to design variety of configuration and retraction options of VUT200 TwinCobra landing gear. For each option are a wheel base and a gauge set up by possibility of main landing gear retraction. Next, CS 23 demands and stress analysis are followed. There is a view of twin engine aircraft landing gear disclosed as well.

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14

Baláš, Martin. "Pevnostní kontrola a topologická optimalizace dílu podvozku letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417462.

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This master thesis is about stress analysis of landing gear for accomplishment CS-23 regulation. The first part examines all alternatives of landing gear regarding for accomplishment of regulation. Next part is stress analysis of main and nose landing gear using FEM analysis in MSC Nastran software. Last part of master thesis describes topology optimization of two parts of landing gear.

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15

Kewley, Sarah Elizabeth. "Parametric study into the shimmy dynamics of a nose landing gear-fuselage model." Thesis, University of Bristol, 2015. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.702149.

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This thesis investigates the influence of different parameters on the shimmy dynamics of a nose landing gear. This is achieved by considering a sequence of increasingly complex models. Due to the nature of landing gear dynamics, numerical continuation is used to analyse the system's shimmy characteristics. A nose landing gear model consisting of a strut, caster and single wheel is presented. It has torsional and lateral bending vibrational modes and is completed with an elastic tyre. The critical forward velocity of the aircraft shimmy onset can be determined as the equilibrium solution loses

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16

Bednář, Peter. "Návrh příďového podvozku pro letouny řady Zlín 40." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-442851.

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This master’ thesis deals with the design of the front landing gear for Zlín 40 aircrafts. The main emphasis in the research part of the work is placed on the selection of a new nose landing gear and the subsequent design of the structure. For the structural design was prepared a new mass analysis and load cases. The load-bearing capacity of the structure is verified using analytical and numerical methods of FEM. An important step of the work is the design concept of structure. The aim of the work is to point out the new possibilities of the nose landing gear structure and verify its feasibili

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17

Vodička, Petr. "Návrh elektro-hydraulické soustavy pro ovládání příďového podvozku malého dopravního letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318402.

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The diploma thesis is focused on design of electrohydraulic system for nose gear control on small civil airliners. First part consists of brief review of small civil airliners, nose gears and CS 23 restrictions relevant for the design. In practical part a typical small civil airliner is defined and kinematic of landing gear mechanisms is designed. Then the electrohydraulic system itself is designed and parameters of some components are suggested. The wheel steering mechanism is simulated and, in conclusion, the whole system is evaluated.

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18

Pauliny, Jozef. "Návrh podvozku čtyřmístného jednomotorového letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231654.

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Cílem této práce je návrh pevného tříkolového podvozku pro jednomotorový čtyřmístný celokompozitní letoun s dodržováním certifikačních specifikací CS-23. To zahrnuje návrh kompozitních pružinových hlavních podvozkových vzpěr v kombinaci s hydropneumatickým tlumičem příďového podvozku. Proces návrhu se dělí do pěti specifických fází; požadavky na konstrukci, předběžný návrh, detailní návrh, příprava výroby a zkoušení prototypu. Zatížení podvozku pro jednotlivé případy a konfigurace letounu je definován v předběžné fázi návrhu. Detailní návrh zahrnuje pevnostní analýzu jednotlivých komponentů. F

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19

SONI, AMIT KUMAR. "FATIGUE LIFE ESTIMATION OF LANDING GEARS OF FIGHTER AIRCRAFT USING FINITE ELEMENT ANALYSIS." Thesis, 2012. http://dspace.dtu.ac.in:8080/jspui/handle/repository/13953.

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M.TECH<br>The Total Technical Life (TTL) of fighter aircraft “Article 29L” is 1800 flying hrs. However the TTL of Main Landing Gear (MLG) and Nose Landing Gear (NLG) is only 2000 landing. Considering average sortie duration of 45 minutes, the life of LGs should have been ideally 2400 landings. So there is need to increase the life of LGs. In older days the stress analysis and life extension study was carried out considering the experimental stress analysis approach and testing, which is time consuming and require huge testing setup. In order to bridge this gap and to reduce the effort,

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20

Shuo-ChenKao and 高碩辰. "On the Mechanism Design of Nose Landing Gears." Thesis, 2019. http://ndltd.ncl.edu.tw/handle/ex3cxd.

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21

Silva, José Miguel Casaca Faria. "Development of a nose landing gear of an unmanned aircraft (RPAS)." Master's thesis, 2017. https://hdl.handle.net/10216/103432.

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22

Silva, José Miguel Casaca Faria. "Development of a nose landing gear of an unmanned aircraft (RPAS)." Dissertação, 2017. https://repositorio-aberto.up.pt/handle/10216/103432.

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