Relevant bibliographies by topics / Nose landing gear

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Nose landing gear'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "Nose landing gear"

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Mu, Yongfei, Jie Li, Wutao Lei, and Daxiong Liao. "The effect of doors and cavity on the aerodynamic noise of fuselage nose landing gear." International Journal of Aeroacoustics 20, no. 3-4 (March 15, 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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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "Research on the nose landing gear of a military training aircraft." INCAS BULLETIN 12, no. 4 (December 4, 2020): 249–59. http://dx.doi.org/10.13111/2066-8201.2020.12.4.23.

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This paper presents the analysis of the landing gear configurations and the proposal of a solution for a military training aircraft. The paper presents both landing gears: nose and main because they are inextricably linked. The nose landing gear of military aircraft is a complex system composed of structural elements, electric and hydraulic components, energy absorption components, aircraft tire wheels etc., which is dimensioned according to the weight of the aircraft. Additional components attached to the nose landing gear include a landing gear extension and retraction mechanism and a steering system. The landing gear must withstand the weight of the aircraft in all phases of take-off (maximum weight: fuel, armament, ammunition, other equipment, flight crew etc.) and landing (impact from landing and a lower weight after completing the mission due to fuel consumption and ammunition use).
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Liang, Yong, Kun Zhao, Yingchun Chen, Longjun Zhang, and 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 (July 4, 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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Zhang, Lin Hai, Xiao Ye Qi, Jun Gong Ma, and Rong Rong Yang. "The Load Simulation Research of Nose Landing Gear Steering." Applied Mechanics and Materials 687-691 (November 2014): 701–5. http://dx.doi.org/10.4028/www.scientific.net/amm.687-691.701.

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The nose landing gear is a vital component of an aircraft,which has an important impact on the safety of the aircraft.This paper studies the system of nose landing gear steering on the basis of the gear and rack mechanism durability test of a certain type of civil aircraft landing gear steering. Furthermore,it puts forward a method of passive loading,which can simulate the friction when the nose landing gear reciprocating turning,and establishes the mathematical model. The simulation results show that the simulator can meet the requirements of load,and laid a theoretical foundation for the subsequent actual work.
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Merino-Martínez, Roberto, Eleonora Neri, Mirjam Snellen, John Kennedy, Dick G. Simons, and Gareth J. Bennett. "Multi-Approach Study of Nose Landing Gear Noise." Journal of Aircraft 57, no. 3 (May 2020): 517–33. http://dx.doi.org/10.2514/1.c035655.

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Shams, Taimur Ali, Syed Irtiza Ali Shah, Muhammad Ayaz Ahmad, Kashif Mehmood, Waseem Ahmad, and Syed Tauqeer ul Islam Rizvi. "Selection Methodology of an Electric Actuator for Nose Landing Gear of a Light Weight Aircraft." Applied Sciences 10, no. 23 (December 6, 2020): 8730. http://dx.doi.org/10.3390/app10238730.

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Landing gear system of an aircraft enables it to take off and land with safety and comfort. Because of the horizontal and vertical velocity of aircraft, upon landing, the complete aircraft undergoes different forcing functions in the form of the impact force that is absorbed by landing gears, shock absorbers, and actuators. In this research, a selection methodology has been proposed for an electrical actuator to be installed in the retraction mechanism of nose landing gear of an aircraft having 1600 kg gross takeoff weight. Nose landing gear and its associated components, like strut and shock absorbers, were modeled in CAD software. Analytical expressions were then developed in order to calculate the actuator stroke, translational velocity, force, and power for complete cycle of retraction, and some were subsequently compared with the computational results that were obtained using MSC ADAMS®. Air in the oleo-pneumatic shock absorber of nose landing gear was modeled as a nonlinear spring with equivalent spring constant, whereas hydraulic oil was modeled as a nonlinear damper with equivalent damping constant. The nose landing gear system was modeled as a mass-spring-damper system for which a solution for sinusoidal forcing functions is proposed. Finally, an electrical actuator has been selected, which can retract and extend nose landing gear, meeting all of the constraints of aircraft, like fuselage space, aircraft ground clearance, locking loads, power consumption, retraction and extension time, and dynamic response of aircraft. It was found that the selection of an electrical actuator is based upon the quantification of forces transmitted to electrical actuator during one point load at gross takeoff weight. The ability of retraction and extension time, as dictated by Federal Aviation Regulation, has also been given due consideration in the proposed methodology as significant criteria. The proposed system is now in the process of ground testing, followed by flight testing in the near future.
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Bennett, Gareth J., Eleonora Neri, and John Kennedy. "Noise Characterization of a Full-Scale Nose Landing Gear." Journal of Aircraft 55, no. 6 (November 2018): 2476–90. http://dx.doi.org/10.2514/1.c034750.

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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "Preliminary calculation of the landing gear of a military training aircraft." INCAS BULLETIN 12, no. 4 (December 4, 2020): 241–47. http://dx.doi.org/10.13111/2066-8201.2020.12.4.22.

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The paper presents a preliminary calculation method, which is easy to apply for pre-dimensioning the landing gear. Preliminary calculation of the landing gear includes estimating the loads on landing and determining the position of the nose landing gear and the main landing gear of a military training aircraft. Another purpose of the preliminary calculation is to ensure the stability of a military training aircraft on landing and take-off, as well as to ensure the lateral stability of the aircraft during ground operations such as taxiing, landing or take-off.
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Lee, Hong-Chul, Young-Ha Hwang, and Tae-Gu Kim. "Failure analysis of nose landing gear assembly." Engineering Failure Analysis 10, no. 1 (February 2003): 77–84. http://dx.doi.org/10.1016/s1350-6307(02)00031-6.

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Chen, Yi, Rongyao Cui, Rongbo Ju, and Qingbo Dou. "Simulation of Nose Landing Gear Shimmy with Flexible Airframe Considered." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 2 (April 2018): 388–95. http://dx.doi.org/10.1051/jnwpu/20183620388.

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Shimmy stability of the nose landing gear of an aircraft is studied in this paper. Firstly, Shimmy model was built considering the dynamic characteristics of the airframe. Then the critical damping, critical velocity and frequency range of the shimmy are obtained by introducing relevant parameters into the shimmy model. The research shows that the problem of shimmy is a tire type shimmy caused by insufficient damping of dampers and brings coupled resonance with the vibration mode of the airframe, which can be avoided by increasing the damping of the shimmy. At the same time, the influence of airframe dynamics and tire stiffness on the shimmy characteristics of the landing gear is also studied. With the increase of tire torsion and lateral stiffness, the critical velocity, maximum critical damping value and shimmy frequency of the landing gear increase. However, the elasticity of the airframe makes the frequency of the aircraft landing gear lower and the stable region of the shimmy smaller, so that the phenomenon of shimmy is more likely to occur. Therefore, the influence of airframe dynamic characteristics can not be ignored when studying the shimmy stability of the landing gear of a modern large passenger aircraft.
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Dissertations / Theses on the topic "Nose landing gear"

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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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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 components were carefully modeled using contact analysis. The tire was modeled using the eye-bar theory. The results obtained in this work are consistent with the Federal Aviation Administration’s recommendations for physical testing.
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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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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 stability via a Hopf bifurcation. The bifurcating steady-state periodic solution gives the maximum amplitude of the self-sustained shimmy oscillation, which are dominated by one of the vibrational modes of the gear. The Hopf bifurcation points can be continued in two parameters where they form stability boundaries for the gear's equilibrium solution over gear vertical loading and ground speed. The nose landing gear model is then coupled to a two degree of freedom model, consisting of two mass spring damper systems acting at the nose landing gear-fuselage attachment point in the lateral and vertical directions. These represent any local displacement resulting from flexible deformation of the fuselage. Shimmy onset is found to be sensitive to the lateral, but not the vertical, motion of the fuselage. However, the amplitude and frequency of shimmy oscillations are influenced by the vertical mode. The latter part of the thesis presents an extended nose landing gear-fuselage model. Here the fuselage model includes a rigid body lateral fuselage mode that represents lateral motion of the fuselage at the nose landing gear-fuselage attachment point due to fuselage yaw; it also comprises roll and pitch rotations which present themselves as rotations in the nose landing gear. The gear model also includes axial compression of the strut, has a dual wheel configuration and includes their gyroscopic effects. The shimmy dynamics of the gear are found to be virtually unaffected by the presence of the rigid body fuselage model, whilst the two wheels and their gyroscopic effects are found to strongly influence the shimmy onset point. The gear's design and tyre parameters are investigated next. The increase in separation distance merges the two shimmy oscillations into one displaying large amplitudes in both modes. It is also found that a decreased rake angle and increased caster length stabilises the gear considerably. The gear's tyre relaxation length and contact patch length are found to stabilise the gear when increased and decreased, respectively. This effect, along with that of the flexible fuselage, however, is dwarfed by the influence of the rake angle and caster length. Moreover, the gear was found to be very sensitive to the change in magnitude of the self-aligning moment. Thus, it is concluded that the fuselage dynamics play little part in the onset of shimmy, and that when considering shimmy onset particular attention should be paid to the rake angle, caster length and self-aligning moment which appear to be highly influential in triggering shimmy.
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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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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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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 feasibility for the case of future implementation.
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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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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 developed that combines near field flow computations with an integral radiation model to enable the far field signal to be evaluated without the need to directly resolve the propagation of the acoustic waves. The recent advances in the CAA methods are implemented with high-order finite difference compact schemes and a characteristics-based multi-block interface treatment. Aerodynamic noise from a generic two-wheel landing gear model, provided by Airbus LAGOON (landing gear noise database for CAA validation) program, is predicted by using the hybrid approach and compared with the LAGOON database. The unsteady flow field is computed by using a compressible Navier-Stokes solver based on high-order finite difference schemes. The calculated time history of surface data is used in a FW-H solver to predict the far field noise levels. Both aerodynamic and aeroacoustic results are compared with wind tunnel measurements in good agreement. Individual contributions from three components, i.e. wheels, axle and strut of the landing gear model are also investigated to identify the major noise source component. It is found that strong flow-body interaction noise is generated by the flow separated from tire rim impinging on the axle. Based on the same landing gear model, the comparison study using conventional CFD solver FLUENT is performed with a second-order Navier-Stokes finite volume solver to compute the unsteady near field flow and the built-in FW-H solver to calculate the far field sound propagation. The comparison suggests that although conventional CFD method can obtain good timeaveraged aerodynamic results, its ability of predicting sound radiation is limited by the inherent low-order numerical discretizations. The aerodynamic noise from the isolated undercarriage wheel with detailed hub configuration is also investigated using FLUENT. The asymmetric phenomenon in the mean flow is discovered in the wake region of the wheel, which contributes to a positive lift force for the wheel. It is predicted that the isolated wheel radiates relatively strong noise to the sides with several strong tonal noise.
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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. Fáze zkoušení prototypu definuje způsob ověření únosnosti zkouškou. Závěr obsahuje podrobnou technickou dokumentaci.
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Books on the topic "Nose landing gear"

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Flight investigation of the use of a nose gear jump strut to reduce takeoff ground roll distance of STOL aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

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L, Martin James, Hardy Gordon H, and Ames Research Center, eds. Flight investigation of the use of a nose gear jump strut to reduce takeoff ground roll distance of STOL aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

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Book chapters on the topic "Nose landing gear"

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Langtry, R., and P. Spalart. "Detached Eddy Simulation of a Nose Landing-Gear Cavity." In IUTAM Symposium on Unsteady Separated Flows and their Control, 357–66. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-1-4020-9898-7_31.

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Guertsman, V. Y. "A Case Study of Nose Landing Gear Failure Caused by Fatigue." In ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives, 635–44. Dordrecht: Springer Netherlands, 2011. http://dx.doi.org/10.1007/978-94-007-1664-3_51.

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Tian, Wei, and Qin Sun. "Applied Design Optimization of Nose Landing Gear Cabin Structure of Airplane." In Lecture Notes in Electrical Engineering, 557–64. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54233-6_61.

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Wang, Jian, Wenjiang Wang, and Kangle Xu. "Acoustical Wind Tunnel Studies of Landing Gear Noise." In Fluid-Structure-Sound Interactions and Control, 69–75. Berlin, Heidelberg: Springer Berlin Heidelberg, 2015. http://dx.doi.org/10.1007/978-3-662-48868-3_11.

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Wang, L., C. Mockett, T. Knacke, and F. Thiele. "Noise Prediction of a Rudimentary Landing Gear Using Detached-Eddy Simulation." In Progress in Hybrid RANS-LES Modelling, 279–89. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-31818-4_24.

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"Cracking in an Aircraft Nose Landing Gear Strut." In Handbook of Case Histories in Failure Analysis, 11–14. ASM International, 1993. http://dx.doi.org/10.31399/asm.fach.v02.c9001292.

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Nonato, Raphael Basilio Pires, and Alexander Dias Lopes. "STRUCTURAL OPTIMIZATION OF A NOSE LANDING GEAR FOR CESSNA 172 AIRPLANE." In Engenharia mecânica: A influência de máquinas, ferramentas e motores no cotidiano do homem 2, 34–48. Atena Editora, 2021. http://dx.doi.org/10.22533/at.ed.1732118063.

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"Use of Electron Fractography to Diagnose Cracking in an AISI 4340 Nose Landing Gear Cylinder." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001538.

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"Use of Electron Fractography to Dianose Stress-Corrosion Cracking of an AISI 4340 Nose Landing Gear Cylinder." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001542.

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Rahmani, M., and K. Behdinan. "On the analysis of passive vibration mitigation of nose landing gears." In Advances in Engineering Materials, Structures and Systems: Innovations, Mechanics and Applications, 43–48. CRC Press, 2019. http://dx.doi.org/10.1201/9780429426506-7.

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Conference papers on the topic "Nose landing gear"

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Barnes, John, Jerri McMichael, Jared Walker, Robert Olliffee, and B. Baker. "Nose Landing Gear Door Re-design." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-2077.

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Vuillot, Francois, Nicolas Lupoglazoff, David Luquent, Laurent Sanders, Eric Manoha, and Stephane Redonnet. "Hybrid CAA solutions for nose landing gear noise." In 18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2283.

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Dahan, Jeremy, Ciaran O'Reilly, and Gunilla Efraimsson. "Numerical Investigation of a Realistic Nose Landing Gear." In 20th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2077.

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Tartaruga, Irene, Mark H. Lowenberg, Jonathan E. Cooper, Pia Sartor, and Yves Lemmens. "Bifurcation Analysis of a Nose Landing Gear System." In 15th Dynamics Specialists Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1572.

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Neri, Eleonora, John Kennedy, and Gareth J. Bennett. "Characterization of Low Noise Technologies Applied to a Full Scale Fuselage Mounted Nose Landing Gear." In ASME 2015 Noise Control and Acoustics Division Conference at InterNoise 2015. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/ncad2015-5911.

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The negative impact of aircraft noise includes effects on population’s health, land use planning and economic issues such as building restrictions and operating restrictions for airports. Thus, the reduction of noise generated by aircraft at take-off and approach is an essential consideration in the development of new commercial aircraft. Among the different aircraft noise sources, landing gear noise is one of the most significant during approach. This research presents results from the European Clean Sky funded ALLEGRA project, which investigated a full-scale Nose Landing Gear (NLG) model featuring the belly fuselage, bay cavity and hydraulic dressing. Tests were performed for a variety of wind speeds and yaw angles. In this paper, a characterization of the noise generated by the full-scale Nose Landing Gear (NLG) model is presented and the different techniques used for characterizing acoustic sources on the NLG are described. The landing gear noise source is characterized in terms of OASPL, directivity, source spectra, PNL and PNLT. A comparison between the NLG with and without the application of low noise technology is presented.
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Neuhart, Dan, Mehdi Khorrami, and Meelan Choudhari. "Aerodynamics of a Gulfstream G550 Nose Landing Gear Model." In 15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3152.

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Kim, Tae-Uk, JeongWoo Shin, and Sang Wook Lee. "Design and Testing of a Crashworthy Landing Gear." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-52474.

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The development of a crashworthy landing gear is presented based on the civil regulations and the military specifications. For this, two representative crashworthy requirements are applied to helicopter landing gear design; the nose gear is designed to collapse in a controlled manner so that it does not penetrate the cabin and cause secondary hazards, and the main gear has to absorb energy as much as possible in crash case to decelerate the aircraft. To satisfy the requirements, the collapse mechanism triggered by shear-pin failure and the shock absorber using blow-off valve are implemented in the nose and main gear, respectively. The crash performance of landing gear is demonstrated by drop tests. In the tests, performance data such as ground reaction loads and shock absorber stroke are measured and crash behaviors are recorded by high-speed camera. The test data shows a good agreement with the prediction by simulation model, which proves the validity of the design and analysis.
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Rahmani, Mohsen, and Kamran Behdinan. "Performance Analysis and Parametric Studies of Nose Landing Gear Shimmy Dampers." In ASME 2019 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/imece2019-10167.

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Abstract Self-induced mechanical oscillation of nose landing gears designated as shimmy is a major safety challenge for aircrafts. The rotational-lateral shimmy vibrations can occur during takeoff, taxiing, and landing and needs to be sufficiently controlled to avoid escalation and catastrophic failure of the landing gear system. Existing solutions for shimmy problem are largely passive control strategies known as shimmy dampers. Despite numerous studies on the source of shimmy and its trends, investigations on the design and performance analysis of shimmy dampers are scarce. From a design perspective, it is crucial to quantify the effective stiffness and damping supplied by the shimmy damper to the system in different operation states. Furthermore, the sensitivity of the damper performance to its design parameters needs to be thoroughly investigated in order to optimize the design for a particular aircraft. In this study, core relationships for three shimmy dampers are presented and used to perform sensitivity studies. These dampers are concepts by Boeing, Collins Aerospace (formerly UTAS), and a new one designated as the Symmetric Torque Link Damper (STLD). The influence of design parameters on the dampers’ performance is studied and observed trends are discussed in the light of inherent trade-offs. Subsequently, a nonlinear Multibody Dynamic model of the landing gear is utilized to obtain sample time histories of oscillations for each shimmy damper in order to highlight the performance differences and to demonstrate the influence of design parameters. Directions for designing future shimmy dampers and recommendations for optimizing them are offered.
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Zawodny, Nikolas S., Derek Dussault, Lawrence S. Ukeiley, Fei Liu, and Louis N. Cattafesta. "Characterization of Noise Generation on a Canonical Nose Landing Gear Sub-system." In 19th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2116.

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de Paula, Adson A., Rudner Queiroz, and Julio Meneghini. "Computational Aeroacoustics Analysis for Noise Minimization on the G550 Nose Landing Gear." In 53rd AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1217.

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Reports on the topic "Nose landing gear"

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Sullivan, Joel A., and Susan J. Evans. Development of the C-17 Nose Landing Gear Container, CNU-691/E. Fort Belvoir, VA: Defense Technical Information Center, April 2007. http://dx.doi.org/10.21236/ada470353.

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