Relevant bibliographies by topics / Landing gear shock-absorber

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

Academic literature on the topic 'Landing gear shock-absorber'

Author: Grafiati
Published: 30 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Landing gear shock-absorber"

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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 (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 a
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Dinc, Ali, Faruk Yildiz, Junkun Ma, et al. "Dynamics of Oleo-Pneumatic Landing Gear Systems for Carrier-Based Unmanned Aerial Vehicles." Aerospace 12, no. 2 (2025): 127. https://doi.org/10.3390/aerospace12020127.

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This paper presents a comprehensive analysis of the dynamics and design of oleo-pneumatic shock absorbers for the landing gear of carrier-based Unmanned Aerial Vehicles (UAVs). Carrier-based operations impose unique challenges due to high-impact landings, necessitating robust landing gear systems capable of withstanding significant g-forces. The study investigates the performance of landing gears designed for carrier operations under various sink rates, utilizing computer simulations to model the dynamics of both sprung and unsprung masses. The design process for an oleo-pneumatic main landing
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Le, Quang-Ngoc, Hyeong-Mo Park, Yeongjin Kim, Huy-Hoang Pham, Jai-Hyuk Hwang, and Quoc-Viet Luong. "An Intelligent Control and a Model Predictive Control for a Single Landing Gear Equipped with a Magnetorheological Damper." Aerospace 10, no. 11 (2023): 951. http://dx.doi.org/10.3390/aerospace10110951.

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Aircraft landing gear equipped with a magnetorheological (MR) damper is a semi-active system that contains nonlinear behavior, disturbances, uncertainties, and delay times that can have a huge impact on the landing’s performance. To solve this problem, this paper adopts two types of controllers, which are an intelligent controller and a model predictive controller, for a landing gear equipped with an MR damper to improve the landing gear performance considering response time in different landing cases. A model predictive controller is built based on the mathematical model of the landing gear s
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Kang, Byung-Hyuk, Jai-Hyuk Hwang, and Seung-Bok Choi. "A New Design Model of an MR Shock Absorber for Aircraft Landing Gear Systems Considering Major and Minor Pressure Losses: Experimental Validation." Applied Sciences 11, no. 17 (2021): 7895. http://dx.doi.org/10.3390/app11177895.

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This work presents a novel design model of a magnetorheological (MR) fluid-based shock absorber (MR shock absorber in short) that can be applied to an aircraft landing gear system. When an external force acts on an MR shock absorber, pressure loss occurs at the flow path while resisting the fluid flow. During the flow motion, two pressure losses occur: the major loss, which is proportional to the flow rate, and the minor loss, which is proportional to the square of the flow rate. In general, when an MR shock absorber is designed for low stroke velocity systems such as an automotive suspension
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Kiselev, A. V., E. V. Poznyak, and M. M. Kruchinin. "APPLICATION OF A GENETIC ALGORITHM FOR OPTIMIZATION OF THE PNEUMOHYDRAULIC SHOCK ABSORBER OF THE HELICOPTER LANDING GEAR." Spravochnik. Inzhenernyi zhurnal, no. 336 (March 2025): 36–45. https://doi.org/10.14489/hb.2025.03.pp.036-045.

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The development of an impact protection system based on a pneumohydraulic shock absorber of a helicopter landing gear is a complex task leading to the problem of multidimensional global optimization with limitations. The goal of optimization is to maximize the absorption of landing impact energy. The objective function depends on seven optimization parameters that determine the characteristics of the shock absorber. Each of the parameters is subject to limitations related to the design requirements of the system. The pneumohydraulic shock absorber model was developed in the Simcenter Amesim so
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Yadav, D., and R. P. Ramamoorthy. "Nonlinear Landing Gear Behavior at Touchdown." Journal of Dynamic Systems, Measurement, and Control 113, no. 4 (1991): 677–83. http://dx.doi.org/10.1115/1.2896474.

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Landing gear dynamics for an aircraft has been analyzed with a heave-pitch model having telescopic main gear and articulated nose gear using oleopneumatic shock absorber. System equations have been presented incorporating the effects of linkage dynamics, frictional forces, and nonlinearities in the tyre, air spring, and oleo damping forces. Sensitivity of the system response to variations in some shock strut parameters has been investigated for the landing touchdown impact phase to bring about improvement in the performance.
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Wu, Wei Guo, Zhen Tao Wang, and Teng Jia. "Nonlinear Dynamic Response Analysis of Aircraft Landing Gear with Finite Element Modeling." Applied Mechanics and Materials 826 (February 2016): 23–27. http://dx.doi.org/10.4028/www.scientific.net/amm.826.23.

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The precise model and the analysis of nonlinear response are important for the landing gear research. In this paper, the FEM model of landing gear was established. The shock absorber is modeled with the nonlinear spring and damper. Random displacements were applied for simulating runway unevenness at aircraft taxiing. Through the simulation, the nonlinear FEM dynamic response of landing gear was acquired. The results show that: the stress of landing gear is large in the landing progress, especially for the random displacements; the weakness of landing gear is the axle sleeve. So the material a
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Li, Long Shuang, Hong Nie, and Xin Xu. "Simulation and Experiment on Landing Gear Component Noise." Applied Mechanics and Materials 170-173 (May 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 no
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Liu, Wenbin, and Youshan Wang. "Improved Multi-Body Dynamic Simulation of Landing Gear Drop Test Incorporating Structural Flexibility and Bearing Contact." Aerospace 11, no. 7 (2024): 543. http://dx.doi.org/10.3390/aerospace11070543.

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The investigation of multi-body dynamics (MBD) modeling for landing gear drop tests is a hot topic in the realm of landing gear design. The current results were primarily focused on the multi-rigid body simulation or a simple multi-flexible body simulation, with little regard for the correctness of longitudinal loads and their experimental confirmation, particularly wheel–axle loads. Based on a genuine oleo-pneumatic landing gear drop test of a large civil aircraft, enhanced multi-body dynamics simulation research is carried out, considering the structural flexibility and bearing support by ad
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Viana, Felipe A. C., Valder Steffen Jr., Marcelo A. X. Zanini, Sandro A. Magalhães, and Luiz C. S. Góes. "Identification of a Non-Linear Landing Gear Model Using Nature-Inspired Optimization." Shock and Vibration 15, no. 3-4 (2008): 257–72. http://dx.doi.org/10.1155/2008/246271.

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This work deals with the application of a nature-inspired optimization technique to solve an inverse problem represented by the identification of an aircraft landing gear model. The model is described in terms of the landing gear geometry, internal volumes and areas, shock absorber travel, tire type, and gas and oil characteristics of the shock absorber. The solution to this inverse problem can be obtained by using classical gradient-based optimization methods. However, this is a difficult task due to the existence of local minima in the design space and the requirement of an initial guess. Th
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Dissertations / Theses on the topic "Landing gear shock-absorber"

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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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Marcinko, Peter. "Návrh řízeného příďového podvozku pro letoun PS-28 Cruiser." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-254223.

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This diploma thesis deals with the design of the front landing gear with steering nose leg and hydropneumatic shock absorber, designed for aircraft PS - 28 Cruiser. In the thesis there was created design of basic types of front landing gear and the best option was selected. The work is further elaborated design of hydropneumatic shock absorber and comparise with the measured load. At the end of the work it was created the structural design of the front landing gear.
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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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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
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Lin, Tianhong, and Тяньхун Лінь. "Preliminary design of long range cargo aircraft with 240 passengers." Thesis, National Aviation University, 2021. https://er.nau.edu.ua/handle/NAU/53188.

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Робота публікується згідно наказу Ректора НАУ від 27.05.2021 р. №311/од "Про розміщення кваліфікаційних робіт здобувачів вищої освіти в репозиторії університету". Керівник роботи: доцент, к.т.н. Юцкевич Святослав Сергійович<br>This diploma work is dedicated to the design of cargo long-range aircraft with passenger capacity 240 and its design characteristic estimation. The methods of design are analysis of the prototypes and selections of the most advanced technical decisions, analysis of center of gravity position. The diploma work contains drawings of the long-range aircraft with a carrying
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Books on the topic "Landing gear shock-absorber"

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Schmidt, Robert Kyle. The Design of Aircraft Landing Gear. SAE International, 2021. http://dx.doi.org/10.4271/9780768099430.

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The aircraft landing gear and its associated systems represent a compelling design challenge: simultaneously a system, a structure, and a machine, it supports the aircraft on the ground, absorbs landing and braking energy, permits maneuvering, and retracts to minimize aircraft drag. Yet, as it is not required during flight, it also represents dead weight and significant effort must be made to minimize its total mass. The Design of Aircraft Landing Gear, written by R. Kyle Schmidt, PE (B.A.Sc. - Mechanical Engineering, M.Sc. - Safety and Aircraft Accident Investigation, Chairman of the SAE A-5
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Book chapters on the topic "Landing gear shock-absorber"

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"Shock Absorber Design." In Aircraft Landing Gear Design: Principles and Practices. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/5.9781600861468.0069.0121.

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Conference papers on the topic "Landing gear shock-absorber"

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Heirendt, Laurent, Hugh H. T. Liu, and Phillip Wang. "Characteristic Aircraft Landing Gear Thermo-Tribo-Mechanical Model." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-86621.

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A methodology for studying the characteristic thermal response of a landing gear (LG) shock absorber is presented. Rough runways induce high loads on the shock absorber bearings and because of high relative sliding speeds of the shock absorber piston, heat is dissipated which is known to have led to structural damage. In this work, an overall model has been developed that is used to outline the characteristics of the thermal behavior and identify the heat sources and sinks in the landing gear shock absorber. The developed thermo-tribo-mechanical model (TTM model) is subdivided into four parts,
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Ji Teng and A. Z. Shahneh. "Design of Landing Gear Shock Absorber Using Magnetorheological Fluid." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018). Institution of Engineering and Technology, 2018. http://dx.doi.org/10.1049/cp.2018.0227.

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Maemori, Ken’ichi, Naoki Tanigawa, Reiko Koganei, and Toshio Morihara. "Optimization of a Semi-Active Shock Absorber for Aircraft Landing Gear." In ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/detc2003/dac-48765.

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We propose an optimization method for a semi-active shock absorber for use in aircraft landing gear, in order to handle variations in the maximum vertical acceleration of an aircraft during landing caused by the variation of the aircraft mass due to the variations in the number of passengers, and the amounts of cargo and fuel. In this optimization, the maximum vertical acceleration of an aircraft is set as an objective function to be minimized. Design variables searched in the first step of this optimization are discrete orifice areas formed by the outer surface of a hollow metering pin and a
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Guida, M. "Landing gear shock absorbers guidelines." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-19.

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Abstract. This paper is based on an old paper presented by Eng. Ermanno Bazzocchi almost seventy years ago [1] and is here presented again in his memory, to take the opportunity for showing to young generation of engineers how applied research was performed and presented when the computer age was not still born. The topic is on landing gear shock absorber design guidelines, and it has been selected because of the importance of such device for airplanes, which represents a very important system for the efficiency of the entire aircraft. The original paper [1] has represented a milestone for the
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Kim, Tae-Uk, Sung Joon Kim, and Seunggyu Lee. "Crashworthy Landing Gear Design Using a Composite Tube by Extra Energy Absorber." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36452.

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Landing gear is the one of the key components for improving aircraft crashworthiness because its primary function is the energy absorption. But, in general, the shock absorbers are designed to have best efficiency for normal landing cases and can be ineffective when faced with very high sink speed. Thus special design and implementation are necessary for landing gear to have crashworthiness. For this purpose, various concepts have been studied and put to practical use such as structural pin, pressure relief valve and additional energy absorbing devices, etc. In this paper, the composite tube i
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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
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Shu, Ning, Hongbin Gu, and Hui Liu. "Analysis of temperature effect on damping characteristics of landing gear shock absorber." In ICASIT 2020: 2020 International Conference on Aviation Safety and Information Technology. ACM, 2020. http://dx.doi.org/10.1145/3434581.3434593.

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Yang, Hui, Fangyi Wan, and Weimin Cui. "Failure simulation and identification of shock absorber in carrier-based aircraft landing gear." In 2016 IEEE International Conference on Prognostics and Health Management (ICPHM). IEEE, 2016. http://dx.doi.org/10.1109/icphm.2016.7542833.

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Shuhua Zhu, Mingbo Tong, and Jie Xu. "Design of an adaptive shock absorber of landing gear and preliminary analysis on taxiing performance." In 2008 Asia Simulation Conference - 7th International Conference on System Simulation and Scientific Computing (ICSC). IEEE, 2008. http://dx.doi.org/10.1109/asc-icsc.2008.4675338.

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Maemori, Ken’ichi, Naoki Tanigawa, and Feng-Hui Shi. "Optimization of a Semi-Active Shock Absorber Using a Genetic Algorithm." In ASME 2004 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/detc2004-57115.

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We propose an optimization method for a semi-active shock absorber for use in aircraft landing gear using Carroll’s FORTRAN Genetic Algorithm (GA) Driver. This method is compared with Powell’s conjugate direction method, a nonlinear programming (NP) approach, which uses not gradients, but only function values. In these optimizations, we handle variations in the maximum vertical acceleration of an aircraft during landing caused by the variation of the aircraft mass due to variations in the number of passengers and the amounts of cargo and fuel. The maximum vertical acceleration of an aircraft i
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