Relevant bibliographies by topics / Main landing gear

Contents

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

Academic literature on the topic 'Main landing gear'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Main landing gear"

1

Sartor, P., K. Worden, R. K. Schmidt, and D. A. Bond. "Bayesian sensitivity analysis of flight parameters that affect main landing gear yield locations." Aeronautical Journal 118, no. 1210 (December 2014): 1481–97. http://dx.doi.org/10.1017/s0001924000010150.

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Abstract An aircraft and landing gear loads model was developed to assess the Margin of Safety (MS) in main landing gear components such as the main fitting, sliding tube and shock absorber upper diaphragm tube. Using a technique of Bayesian sensitivity analysis, a number of flight parameters were varied in the aircraft and landing gear loads model to gain an understanding of the sensitivity of the MS of the main landing gear components to the individual flight parameters in symmetric two-point landings. The significant flight parameters to the main fitting MS, sliding tube bending moment MS and shock absorber upper diaphragm tube MS include: longitudinal tyre-runway friction coefficient, aircraft vertical descent velocity, aircraft Euler pitch angle and aircraft mass. It was also shown that shock absorber servicing state and tyre pressure do not contribute significantly to the MS.
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Wandono, Fajar Ari. "Optimization of the Main Landing Gear Structure of LSU-02NGLD." Computational And Experimental Research In Materials And Renewable Energy 4, no. 1 (May 28, 2021): 30. http://dx.doi.org/10.19184/cerimre.v4i1.24965.

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The mass of the landing gear structure becomes an important aspect of the total mass of the UAV (unmanned aerial vehicle). Therefore, many efforts have been made to reduce the mass of the landing gear by performing structural optimization. Reducing the mass of the landing gear structure can be used as a substitute to increase the payload on the UAV. The landing gear structure in this paper is the main landing gear of LSU-02NGLD (LAPAN Surveillance UAV series 02 New Generation Low Drag). LSU-02NGLD is a UAV that has 2.9 m of wingspan with a total mass of 21 kg. This paper aims to optimize the main landing gear structure so that optimization can reduce the mass. The optimization was carried out using the finite element software by modeling the main landing gear structure as a 1D beam element. There were 9 beam elements in the main landing gear structure model. The cross-sectional width (w) and the cross-sectional height (h) for each element were used as design variables. The objective of the optimization was to minimize the mass while maintaining maximum bending stress not greater than 20 MPa, displacement in y-direction not greater than 1 mm, and displacement in z-direction not greater than 0.1 mm. The optimization result showed that the mass reduction of the main landing gear structure was 50%, with all constraints fulfilled.
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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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Hidayat, Dony, Jos Istiyanto, Danardono Agus Sumarsono, and Aryandi Marta. "INVESTIGASI GAYA KONTAK/IMPAK PADA MAIN LANDING GEAR PESAWAT KOMUTER DENGAN PENDEKATAN MULTI-BODY SIMULATION (MBS) RIGID MODELS." Jurnal Teknologi Dirgantara 15, no. 1 (December 14, 2017): 1. http://dx.doi.org/10.30536/j.jtd.2017.v15.a2529.

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Landing Gear Drop Test (LGDT) which aims to determine the characteristic of contact/impact force that occurs in the time of the touchdown landing has been conducted. Experimental tests using the apparatus requires a substantial time and cost. Virtual Landing Gear Drop Test (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. Stiffness values and damping coefficient obtained from vLGDT are 5.0e5 N/m and 1600 N.sec/m. Contact/impact force that occurs on vLGDT is 75996 N, while from experimental is 73612 N. The difference between vLGDT and experimental result is 3.14%.Abstrak:Pengujian landing gear yang bertujuan untuk mengetahui karakteristik gaya kontak/impak yang terjadi saat touchdown landing telah dilakukan. Pengujian eksperimental menggunakan apparatus membutuhkan waktu yang lama dan biaya yang besar. Vitual Landing Gear Drop Test (vLGDT) menggunakan perangkat lunak MSC ADAMS merupakan salah satu alternatif untuk pengujian tahap awal landing gear. Dari simulasi menggunakan vLGDT diperoleh nilai k = 5.0e5 N/m dan cmax = 1600 N.detik/m. Gaya kontak/impak yang terjadi pada simulasi menggunakan vLGDT sebesar 75996 N, sedangkan dari eksperimental sebesar 73612 N. Hasil vLGDT lebih besar 3.14% dibandingkan eksperimental.
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Krason, W., and J. Malachowski. "Multibody rigid models and 3D FE models in numerical analysis of transport aircraft main landing gear." Bulletin of the Polish Academy of Sciences Technical Sciences 63, no. 3 (September 1, 2015): 745–57. http://dx.doi.org/10.1515/bpasts-2015-0086.

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Abstract Dynamic analyses of a transport aircraft landing gear are conducted to determine the effort of such a complex system and provide capabilities to predict their behaviour under hazardous conditions. This kind of investigation with the use of numerical methods implementation is much easier and less expensive than stand tests. Various 3D models of the landing gear part are defined for the multistage static FE analysis. A complete system of the main landing gear was mapped as a deformable 3D numerical model for dynamic analysis with the use of LS-Dyna code. In this 3D deformable FE model, developed in a drop test simulation, the following matters were taken into consideration: contact problems between collaborating elements, the phenomena of energy absorption by a gas-liquid damper placed in the landing gear and the response of the landing gear during the touchdown of a flexible wheel with the ground. The results of numerical analyses for the selected drop tests and the results from the experiments carried out on a real landing gear were used for verification of FE models and a methodology of the landing gear dynamics analysis. The results obtained from the various simulations of the touchdown have proved the effectiveness of the 3D numerical model and how many problems can be solved in the course of only one numerical run, e.g. geometric and material nonlinearities, a question of contact between the mating components, investigation of the landing gear kinematics, investigation of the energy dissipation problem in the whole system and the stresses influence on the structure behaviour, which can appear in some elements due to overload.
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Skorupka, Zbigniew. "Dynamic Fatigue Tests Of Landing Gears." Fatigue of Aircraft Structures 2020, no. 12 (December 1, 2020): 69–77. http://dx.doi.org/10.2478/fas-2020-0007.

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Abstract Landing gears are one of the main components of an aircraft. The landing gear is used not only during take-off and landing but also, in most cases, during ground manoeuvres. Due to its function, the landing gear is also one of the key safety components of the aircraft due to dissipating landing loads acting on the aircraft. The mentioned loads come from both the vertical and horizontal speeds during touchdown and by the aircraft’s losing the speed by braking. The landing gear is then loaded with constantly changing forces acting in various directions during every landing, with the only difference coming from their magnitude. The repeatable loading conditions cause significant wear of the landing gear. This wear can be divided into two categories, one is the wear of consumable parts such as the brake linings and the other is the fatigue wear of the structural components. The latter type of wear is much more dangerous due to its slow, and in many cases, unnoticeable progression. Fatigue wear can be estimated by numerical analyses – this method works with a great degree of probability on single components but due to the complexity of the landing gear as a whole it is not precise enough to be applied to the full structure. In order to evaluate the fatigue of the whole landing gear the best method accepted by regulations is the laboratory testing method. It involves a series of various drop tests resembling the real landing condition distribution. The aim of the tests is to check the fatigue wear of the landing gear and to prove its reliability for certification and/or operational purposes. In this paper the author describes the basics of the landing gear fatigue wear, possibilities of its evaluation and presents laboratory dynamic method used for extensive tests in life-like operation conditions.
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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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Chuban, Vitalii Dmitrievich. "SHIMMY ANALYSIS OF LIGHT AIRPLANE MAIN LANDING GEAR." TsAGI Science Journal 48, no. 7 (2017): 665–72. http://dx.doi.org/10.1615/tsagiscij.2018026284.

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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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Chen, Pu Woei, Shu Han Chang, and Chan Ming Chen. "Impact Loading Analysis of Light Sport Aircraft Landing Gear." Applied Mechanics and Materials 518 (February 2014): 252–57. http://dx.doi.org/10.4028/www.scientific.net/amm.518.252.

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This paper examined the critical loading condition of a light sport aircrafts main landing gear during the impact loading condition. The new category airplane was established by the FAA in 2004. The light sport aircraft has great market demand for personnel entertainment purpose and regional transportation. The main object of this research was to establish a static and dynamic loading simulation model for the aluminum alloy landing gear of a light sport aircraft. This work also examined the critical loading parameters of the main landing gear, including the maximum take-off weight and maximum stall speed. The analysis was performed using ANSYS and LS-DYNA to establish the finite element model after simplifying the geometric characteristics and verifying the results by energy conservation, hourglass energy, and sliding energy. The study tested aluminum plates with a thickness from 15~25 mm. The results showed all the samples could sustain the required loading condition, except for the thickness of 15mm that failed under impact loading. The simulation model provides a cost-saving process compared to a real crashworthiness drop test to test the main landing gears compliance with regulations.
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Dissertations / Theses on the topic "Main 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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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 cylinder diameter of 1:7 x 106. Further three-dimensional and high-order numerical simulations were conducted on models with a constant gap distance of 8.7% of the cylinder diameter. The high-order solver evaluates the three-dimensional Navier-Stokes equations in the full-conservation form, with the Zonal Detached-Eddy Simulation model. The fidelity of the numerical solver was improved in two parts. Firstly, an Eigenvalue analysis for a multiple-block environment was developed to optimise the combination of spatial and filtering schemes for maximum grid resolution that is numerically stable. Secondly, a grid quality metric, which correlates strongly to the solution accuracy, was developed. A validation database of experimental measurements on a tripped 26% scale interaction model, at a free-stream Mach number of 0.09, and a Reynolds number based on the cylinder diameter of 2 x 105, was developed at the 2:1 m x 1:5 m wind tunnel at the University of Southampton. The experimental and numerical results show that the wake generated by the interaction model is dominated by low frequencies that correspond to the vortex shedding modes of the cylinder, and the door. As the door angle is increased from 0 to 10.7 degrees, the intensity of the cylinder shedding mode decreased. The sound pressure levels of the radiated noise were calculated using the FW-H method. The dominant noise source is a compact dipole, which reduced in strength as the door angle was increased.
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Howcroft, Christopher. "A bifurcation and numerical continuation study of aircraft main landing gear shimmy." Thesis, University of Bristol, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.617699.

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This thesis presents a bifurcation and numerical continuation study into the occurrence of shimmy instability in an aircraft main landing gear (MLG) of single side-stay, dualwheel design. The dynamics are expressed in terms of three rotational degrees of freedom (Dofs) aligned with the side-stay plane, and a fourth translational DoF representing compression of the main strut. These DoFs are modelled by oscillators that are coupled directly through the geometric configuration of the system, as well as through the tyre/ground interface. Using this representation of the MLG system we focus in this thesis on the nonlinear effects of geometric orientation and mechanical freeplay employing bifurcation analysis techniques to highlight their effects on the MLG stability. First, a changing side-stay orientation angle is investigated. Shimmy is studied by means of a two-parameter bifurcation analysis in terms of the landing gear forward velocity and loading force. For this a three-DoF model is used that does not include axial compression. This formulation along with suitable parameters allows for comparison with the existing literature, and an agreement is demonstrated with previous results for a zero side-stay angle. Subsequent variation of this angle is explored and a consistent picture presented, capturing the (transition of the two-parameter bifurcation diagram us a function of this angle. This shows a considerable increase in the complexity of the dynamics for intermediate side-stay angles. The appearance of an additional shimmy mode is observed and a region of tri-stability found where three distinct shimmy types coexist. For the study of freeplay the MLG model is extended to include axial compression; this axial DoF is required to accurately represent freeplay, introduced to the torque links of the system. Parameter values are chosen here to represent a typical mid-range civil aircraft MLG. The addition of freeplay is shown to result in shimmy oscillations that occur within the MLC operating envelope; their properties depend on both the size and 'shape' of freeplay. Freeplay and geometric coupling arc also considered together via consideration of a non-zero side-stay angle. Here, additional dynamic complexity is introduced in the presence of freeplay and, again , this coincidence with the appearance of a new shimmy mode. Further complex phenomena also appear, including multiple- frequency and chaotic-type oscillations, as well as complex transients. The non-zero geometry produce asymmetry and this results in a great sensitivity of the small-amplitude MLG behaviour to the exact shape of freeplay. Therefore, geometric orientation and freeplay a.re found to have significant effects and, when combined, they work together to produce additional complex phenomena, not otherwise observed when considered in isolation.
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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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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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Ringshia, Aditya K. "Aerodynamic Measurements in a Wind Tunnel on Scale Models of a 777 Main Landing Gear." Thesis, Virginia Tech, 2006. http://hdl.handle.net/10919/34583.

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Aerodynamic measurements were taken over models of the Boeing 777 high fidelity isolated landing gear in the 6- by 6-foot Virginia Tech Stability Wind Tunnel (VT-SWT) at a free-stream Mach number of 0.16. Noise control devices (NCD) were developed at Virginia Tech [9] to reduce noise by shielding gear components, reducing wake interactions and by streamlining the flow around certain landing gear components. Aerodynamic measurements were performed to understand the flow over the landing gear and also changes in the flow between "Baseline" and "NCD" configurations (without and with Noise Control Devices respectively). Hot-film, Pitot-static measurements and flow visualization using tufts were performed over an isolated 26% scale-model high fidelity landing gear for the "Baseline" and "NCD" configurations. Contours of turbulence intensity, normalized wake velocity and normalized total pressure loss for both configurations are compared. The "Baseline" configuration was also compared with the NASA Ames study conducted by Horne et al [7]. Hot-film measurements are also compared to Microphone Phased Array results which were acquired at Virginia Tech by Ravetta [8]. A novel technique for processing hot-film measurements by breaking turbulence into octave bands as acoustic measurements is presented. Particle Image Velocimetry (PIV) measurements were taken at six different locations over the 13% scale-model landing gear with no door and at a truck angle of zero degrees. Results are compared to PIV measurements taken over the wheels of a four-wheel landing gear by Lazos [10-12]. PIV results such as average velocity contours and vectors, streamlines and instantaneous velocity contours and vectors are presented. Results presented from PIV and flow visualization are in good agreement with results from Lazos [10-12].
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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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Kubiena, Jaromír. "Návrh úpravy letadla WT10 Advantic s pevným podvozkem dle předpisu CS-23." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-318135.

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In this thesis, we deal with the design of a shock absorber variant for the type of main landing gear design of the aircraft WT10 Advantic. Then we focus on the design of the selected variant of the main landing gear. Next, we follow regulation CS-23 demands to calculate the load cases for the selected main lending gear. Then we design shock absorber based on the load during landing. We compile the equation of motion of the aircraft, which describes motion of the aircraft during landing, then we compute the equation. Finally, we focus on a stress analysis of the main landing gear and the shock absorber.
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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 and a more realistic complex geometry. Three different bogie angles have been simulated: horizontal bogie aligned with the flow, 10⁰ toe up and 10⁰ toe down. Strong streamwise vortices are generated at the front wheels of the landing gear. The trajectory of these vortices determines where the turbulent flow interacts with the downstream components. This interaction leads to surface pressure fluctuations which are a major noise source. The flow field of the simplified configurations shows a consistent trend of the trajectory of the streamwise vortices with respect to changes in bogie angle. The far field noise levels generated by the different components of the simplified configurations are related to the distance at which the streamwise vortices pass. The additional components of the complex landing gear geometry change the characteristics of the flow field. The strong streamwise vortices persist but they do not show the same trend as for the simplified configurations. The wake of the articulation link generates a turbulent in flow for the other components. The different characteristics of the flow field of the complex configurations lead to significant changes in the far field noise levels of the components compared to the simplified configurations.
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Skřivánek, Jan. "Návrh elektro-hydraulického ovládání hlavního podvozku a brzd pro malý cvičný letoun." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-377525.

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This thesis studies the design of an electro-hydraulic landing gear and brakes control system of a trainer aeroplane. In the first part there is a basic draft of the landing gear kinematics and its loads during gear retraction, flight and landing. Braking conditions are also analysed. The thesis then focuses on the design of hydraulic circuits and their control. Simulations for studying the dynamic characteristics of the braking proportional valve and the course of plane braking were created in Simulink. There is also a brief section about reliability of the proposed system.
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Books on the topic "Main landing gear"

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Daugherty, Robert H. Cornering characteristics of the main-gear tire of the space shuttle orbiter. [Washington, D.C.]: National Aeronautics and Space Administration, 1988.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Book chapters on the topic "Main landing gear"

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Sivaranjani, T., D. V. T. G. Pavan Kumar, C. M. Manjunatha, and M. Manjuprasad. "Fatigue Life Estimation of Typical Fighter Aircraft Main Landing Gear Using Finite Element Analysis." In Advances in Structural Integrity, 39–52. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-7197-3_4.

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"Cracking in an Aircraft Main Landing Gear Sliding Strut." In Handbook of Case Histories in Failure Analysis, 7–10. ASM International, 1993. http://dx.doi.org/10.31399/asm.fach.v02.c9001291.

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"Failure of a Main Landing Gear on a Light Airplane." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001018.

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"Fatigue Fracture of a C130 Aircraft Main Landing Gear Wheel Flange." In Handbook of Case Histories in Failure Analysis, 25–29. ASM International, 1992. http://dx.doi.org/10.31399/asm.fach.v01.c9001025.

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"Breakage of Main Undercarriage Axle of Landing Gear System of an Aircraft Under Simulated Testing." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001555.

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"Failure Investigation of a Structural Component of the Main Landing Gear of a Transport Aircraft." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001706.

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"Use of Electron Fractography to Diagnose Hairline Cracking in an AISI 4340 Main Landing Gear Cylinder." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001540.

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"Weight optimized main landing gears for UAV under impact loading for evaluation of explicit dynamics study." In Advanced Materials, Structures and Mechanical Engineering, 383–88. CRC Press, 2016. http://dx.doi.org/10.1201/b19693-81.

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Conference papers on the topic "Main landing gear"

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Kennedy, John, Eleonora Neri, and Gareth J. Bennett. "The Reduction of Main Landing Gear Noise." In 22nd AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2900.

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Ringshia, Aditya, Patricio Ravetta, Wing Ng, and Ricardo Burdisso. "Aerodynamic Measurements of the 777 Main Landing Gear Model." In 12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-2625.

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Finkbeiner, Josua, Patrick Dunlap, Bruce Steinetz, Jeffrey DeMange, and Daniel Newswander. "Investigations of Shuttle Main Landing Gear Door Environmental Seals." In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4155.

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4

Howcroft, C., B. Krauskopf, M. Lowenberg, S. Neild, and B. Krauskopf. "Effects of Freeplay on Aircraft Main Landing Gear Stability." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4730.

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Ito, Yasushi, Yuzuru Yokokawa, Takehisa Takaishi, Kazuomi Yamamoto, Tohru Hirai, Yosuke Ueno, Kazuhide Isotani, et al. "Noise Reduction of Regional Jet Two-Wheel Main Landing Gear." In 25th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-2481.

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6

Khorrami, Mehdi R., William M. Humphreys, and David P. Lockard. "An Assessment of Flap and Main Landing Gear Noise Abatement Concepts." In 21st AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2987.

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7

Ravetta, Patricio A., Mehdi R. Khorrami, and Ricardo Burdisso. "Acoustic Measurements of a Large Civil Transport Main Landing Gear Model." In 22nd AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2901.

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8

Knowles, James, Bernd Krauskopf, Mark Lowenberg, Simon Neild, and P. Thota. "Numerical Continuation Analysis of a Dual-sidestay Main Landing Gear Mechanism." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4800.

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9

Horne, William, Kevin James, and Bruce Storms. "Flow Survey of the Wake of a Commercial Transport Main Landing Gear." In 8th AIAA/CEAS Aeroacoustics Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2407.

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Ravetta, Patricio, Ricardo Burdisso, and Wing Ng. "Wind Tunnel Aeroacoustic Measurements of a 26%-scale 777 Main Landing Gear." In 10th AIAA/CEAS Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2885.

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Reports on the topic "Main landing gear"

1

Bozzuto, Matthew P., and Susan J. Evans. Development of the C-17 - Main Landing Gear Post Container, CNU-677/E. Fort Belvoir, VA: Defense Technical Information Center, April 2007. http://dx.doi.org/10.21236/ada470982.

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Picard, Mary. F/A-18A/B/C/D Main Landing Gear Control Unit Hydraulic 2A Supply Line Pressure Spikes and Emergency Port Restrictor Ground and Flight Tests Evaluation. Fort Belvoir, VA: Defense Technical Information Center, November 2002. http://dx.doi.org/10.21236/ada409130.

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