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

Author: Grafiati

Published: 30 May 2022

Last updated: 31 July 2025

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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 (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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Zhu, Yu Ming, and Hai Cheng Yang. "Computer-Aided Multi-Domain Unified Modeling and Simulation for Aircraft Landing Gear." Advanced Materials Research 421 (December 2011): 392–96. http://dx.doi.org/10.4028/www.scientific.net/amr.421.392.

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In order to model complex product systems and analyze their whole performance to deal with the coupling relationships between multi-domain，aircraft landing gear selected as the object, unified multi-domain modeling and simulation and for complex product systems was studied. The aircraft leading gear is decomposed as structure, and the mathematical models of the landing gear components are established. The model library of the landing gear components was developed using Modelica-based platform and multi-domain unified model of the landing gear was established. The impact work amount, the vertic

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12

Yazici, Hakan, and Mert Sever. "Active control of a non-linear landing gear system having oleo pneumatic shock absorber using robust linear quadratic regulator approach." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 13 (2017): 2397–411. http://dx.doi.org/10.1177/0954410017713773.

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This paper deals with the active control of a non-linear active landing gear system equipped with oleo pneumatic shock absorber. Runway induced vibration can cause reduction of pilot’s capability of control the aircraft and results the safety problem before take-off and after landing. Moreover, passenger–crew comfort is adversely affected by vertical vibrations of the fuselage. The active landing gears equipped with oleo pneumatic shock absorber are highly non-linear systems. In this study, uncertain polytopic state space representation is developed by modelling the pneumatic shock absorber dy

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13

Maeda, Takao, Masatsugu Otsuki, and Tatsuaki Hashimoto. "Protection against overturning of a lunar-planetary lander using a controlled landing gear." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 2 (2017): 438–56. http://dx.doi.org/10.1177/0954410017742931.

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This paper describes an attitude control method to prevent the overturning of lunar and planetary landers. The proposed control method that is based on a variable-damping shock absorber for the landing gear is experimentally validated. Conventionally, the landing gear of lunar and planetary landers has a fixed shock attenuation parameter that is not used proactively for attitude control of the lander during the touchdown sequence. The proposed method suppresses any disturbance to the attitude of the lander by adjusting the damping coefficient of each landing leg independently, based on the ang

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14

Wei, Xiao Hui, Si Jia Yu, Hong Nie, Ming Zhang, and Yi Zhou Shao. "Design and Dynamic Analysis of Magnetorheological Shock Absorber Based on the Piezoelectric Technology." Applied Mechanics and Materials 397-400 (September 2013): 505–10. http://dx.doi.org/10.4028/www.scientific.net/amm.397-400.505.

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Based on the piezoelectric effect and magnetorheological technology, a parameter adaptive shock absorber was designed. Considering the practical working conditions of landing gear, mathematical model of the parameter adaptive shock absorber was built. Then on the basis of LMS Imagine.Lab AMESim software, the whole combined simulation model of self-adaptive control system was constructed and the drop dynamic simulation was conducted. Results showed that compared with passive control system, parameter adaptive shock absorber reduced the peak of axial force by 10.5% and increased the absorber eff

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15

Liu, Ji Hong, Ying Zhong Pang, and Yu Ming Zhu. "Multi-Domain Unified Modeling and Simulation for Aircraft Landing Gear Using Modelica." Advanced Materials Research 311-313 (August 2011): 2457–60. http://dx.doi.org/10.4028/www.scientific.net/amr.311-313.2457.

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Modern products become more and more complex, the modeling and simulation of them are carried out with different software on heterogeneous platforms, which always caused the heterogeneous data, separated disciplines and cannot obtain the result of unified model correctly. Therefore, a Modelica-based modeling and simulation method for aircraft landing gear is proposed. The landing gear library based on Modelica was established. The unified physical model of landing gear which is composed of structural, thermodynamics and hydromechanics disciplines is constructed. The aircraft landing process, t

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16

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 (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

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17

Sunny, Okemini Uguzo, Nwevo Obinnaya, Chinemerem Gideon Japheth, Johnson Anamemena Nnaemeka, and Yekini Bello. "DESIGNED AND ANALYSIS OF AN SC-17M MAIN LANDING GEAR LOADING ACTION." FUTA JOURNAL OF ENGINEERING AND ENGINEERING TECHNOLOGY 16, no. 1 (2022): 20–26. http://dx.doi.org/10.51459/futajeet.2022.16.1.339.

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The concept of SC-17M aircraft design was initiated to address the shortfalls on the DO-228 and Hawker Beechcraft King Air 350i aircraft. Until recently by using a standard specification, an SC-17M landing gear design has been carried out. Detailed study of sub-part C of the certification standard aided the application and determination of the necessary loads on the landing gear. The comprehensive design employed 300M steel as the best structural material to be used in the fabrication of the landing gear. The maximum bending moment in the shock absorber and wheel axle were calculated and valid

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18

Belkin, A. E., and E. A. Nikitin. "Calculation of the Passenger Aircraft Landing Gear Shock Absorption System Exposed to Impact Loading." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 3 (146) (September 2023): 29–49. http://dx.doi.org/10.18698/0236-3941-2023-3-29-49.

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The paper considers the shock absorption system of an advanced domestic mainline passenger aircraft, which includes oleo-pneumatic shock absorbers and wheels equipped with the pneumatic tires. Nonlinear mathematical models of single-active and two-active oleo-pneumatic shock absorbers of telescopic landing gear supports are proposed. The models take into account the process of polytropic gas compression, the forces of hydraulic resistance to the working fluid flow and the forces of dry friction arising in the system moving parts. To describe the vertical compression reaction of the pneumatic t

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19

Rahmani, Mohsen, and Kamran Behdinan. "Investigation on the effect of coulomb friction on nose landing gear shimmy." Journal of Vibration and Control 25, no. 2 (2018): 255–72. http://dx.doi.org/10.1177/1077546318774440.

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Landing gear shimmy remains a challenge in aircraft design despite abundant advances in aircraft engineering in the past few decades. Accurate shimmy prediction is closely tied to availability of dynamic models with all relevant types of motions and key nonlinear elements, a matter which has been accomplished in the present study through including rotational, lateral, longitudinal, and axial degrees of freedom and tire, shock absorber, and Coulomb friction nonlinearities. Using multi-body dynamic simulations, stability of the nose landing gear is studied as a function of key system parameters.

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20

Shi, Fenghui. "Multi-objective Optimization of Passive Shock Absorber for Landing Gear." American Journal of Mechanical Engineering 7, no. 2 (2019): 79–86. http://dx.doi.org/10.12691/ajme-7-2-4.

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21

Shi, Fenghui, Warren Isaac Anak Dean, and Taikei Suyama. "Single-objective Optimization of Passive Shock Absorber for Landing Gear." American Journal of Mechanical Engineering 7, no. 3 (2019): 107–15. http://dx.doi.org/10.12691/ajme-7-3-1.

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22

Jiao, Fujun. "Oil damping energy loss analysis of landing gear shock absorber." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (2018): 3096–106. http://dx.doi.org/10.1177/0954410018793788.

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It is seen that previous research on falling vibration of landing gear only provides work–stroke diagram and damping force value. Nevertheless, the change process of buffering medium at a micro-level is yet to be analyzed. The velocity, pressure, and their change over time of fluid particle are rarely researched in reality. To improve the intuitive, concreteness, and accuracy of the falling vibration analysis, this paper uses theoretical calculation and simulation to analyze oil damping energy loss of shock absorber. On the basis of theoretical calculation, the paper provides a feasible soluti

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23

Rośkowicz, Marek, and Piotr Leszczyński. "The Selected Problems of Studies of Aircraft Landing Gear." Research Works of Air Force Institute of Technology 39, no. 1 (2016): 91–102. http://dx.doi.org/10.1515/afit-2016-0020.

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Abstract The article portrays the results of experimental studies conducted in the field of static strength test of main landing gear of lightweight aircraft as well as in the area of establishing the pneumatic tyre characteristics of main landing gear. The studies were carried out in compliance with methodologies of performing studies for the purposes of solutions implemented in aviation structures. It was stated that static strength tests of landing gear should not be done with the use of shock absorbers, due to the fact that this element, distinguished by high viscoelastic properties, by be

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24

Skorupka, Zbigniew, R. Kajka, R. Harla, et al. "Active Control of Landing Gear Shock Absorber Characteristic Using Magnetoreological Fluids." Solid State Phenomena 154 (April 2009): 195–201. http://dx.doi.org/10.4028/www.scientific.net/ssp.154.195.

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Smart materials are being used in much larger scale in mechanical solutions. Aviation usage of these materials seems to be natural because of interest in new technologies use in this industry. In this article authors discuss characteristics of magnetoreological fluids as a smart materials, examples of its industrial usage, requirements on landing gear characteristics, design and lab tests of model shock absorber in which MRF was used as damping fluid.

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25

DİNÇ, Ali. "METERING PIN DIAMETER OPTIMIZATION OF AN AIRCRAFT LANDING GEAR SHOCK ABSORBER." Eskişehir Teknik Üniversitesi Bilim ve Teknoloji Dergisi B - Teorik Bilimler 9, no. 2 (2021): 37–46. http://dx.doi.org/10.20290/estubtdb.900786.

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26

Tang, Haihong, Panglun Liu, Jianbin Ding, Jinsong Cheng, Yiyao Jiang, and Bingyan Jinag. "Numerical Prediction of Fatigue Life for Landing Gear Considering the Shock Absorber Travel." Aerospace 12, no. 1 (2025): 42. https://doi.org/10.3390/aerospace12010042.

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Due to the complexity of the landing gear’s (LG) structural integrity and its loads under various static or dynamic working conditions, the fatigue life assessment for LG is a highly challenging task. On the basis of the whole geometric model of a large passenger aircraft’s main landing gear (MLG), the quasi-static finite element model (FEM) of the whole MLG is established, and the high-cycle fatigue issue of the Main Fitting (MF) is studied by considering the variation in shock absorber travel (SAT). Firstly, the ground loads under actual fatigue conditions are equivalently converted into the

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27

Zhu, Shi Xing, and Chan Juan Chen. "Study on Variable Universe Fuzzy PID Control for Landing Gear Based on MRF (Magneto-Rheological Fluid) Damper." Applied Mechanics and Materials 233 (November 2012): 66–71. http://dx.doi.org/10.4028/www.scientific.net/amm.233.66.

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Aircraft landing gear shock system model was established, The system vibration differential equation and state-space equation were deserved。Based on the general fuzzy PID controller, the idea of fuzzy PID controller and its application in shock absorber system were studied. Based on MATLAB, the system simulation model was established, and the fuzzy PID control of semi-active suspension is analyzed compared to variable universe fuzzy PID control. The results show that the variable universe fuzzy PID control had better control effect.

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28

Du, Siyuan, Changming Zhang, Zhiqiang Jia, and Ke Zhou. "Numerical simulation of Oleo-pneumatic Two-phase flow in variable shock absorber." Journal of Physics: Conference Series 2355, no. 1 (2022): 012029. http://dx.doi.org/10.1088/1742-6596/2355/1/012029.

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Abstract In the actual operation of landing gear oil-pneumatic shock absorber, there is a complex gas-liquid two-phase flow problem inside the shock absorber. In this paper, a simplified model of a metering pin variable damping orifice shock absorber is established, and the compression process of the shock absorber is simulated numerically based on CFD method combined with dynamic mesh technology to study the gas-liquid two-phase flow characteristics and the change of oil damping force. The results show that the oil flows out of the damping orifice into the nitrogen cavity in the form of turbu

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29

Sonowal, Plabita, K. M. Pandey, and K. K. Sharma. "Design and static analysis of landing gear shock absorber of commercial aircraft." Materials Today: Proceedings 45 (2021): 6712–17. http://dx.doi.org/10.1016/j.matpr.2020.11.1032.

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Lu, Jianmin, Wenzhong Nie, Yajian Ma, and Xiaoxuan Li. "Analysis Nonlinear mechanical characteristics analysis of a UAV landing gear shock absorber." Journal of Physics: Conference Series 1684 (November 2020): 012131. http://dx.doi.org/10.1088/1742-6596/1684/1/012131.

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31

Wu, Wei-Guo, Fu-Rui Xiong, Jian-Qiao Sun, and Yong-Gang Leng. "Dynamic modeling of aircraft landing gear and multi-objective optimization with simple cell mapping method." Transactions of the Canadian Society for Mechanical Engineering 43, no. 1 (2019): 80–91. http://dx.doi.org/10.1139/tcsme-2017-0083.

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To study the dynamic characteristics of aircraft landing gear and carry out successive optimizations, a mathematical model of flexible landing gear is established by the Hamiltonian principle. The dynamic model includes a tire force estimation derived from the impact model. Dynamic analysis with the flexible model is then conducted. Stress distribution is obtained from the dynamic analysis, which can be used for fatigue analysis, optimization design, etc. To achieve better dynamic characteristics in terms of vibration reduction, a multi-objective optimization problem is formulated and solved v

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Fang, Xingbo, Hu Chen, Xiaohui Wei, and Hong Nie. "Study on the Fast Extension Mechanism of Double-Cavity Shock Absorber with High-Pressure Piston." International Journal of Aerospace Engineering 2021 (April 21, 2021): 1–9. http://dx.doi.org/10.1155/2021/5539401.

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Double-cavity shock absorber with high-pressure piston is the core component of the nose landing gear of the carrier-based aircraft, and its fast-extension performance seriously affects the safety of the catapult-assisted takeoff. The design of a carrier-based aircraft in our country is carried out based on the traditional method of fast-extension dynamics, and it is found that the fast-extension capability is larger than designed. This paper analyzes the working principle of the high-pressure piston shock absorber and explains that the high-pressure air cavity pushes the piston rod to extend

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Капитанова, Людмила Валерьевна, та Виктор Иванович Рябков. "МЕТОД І ЗАСОБИ УТРИМАННЯ НАЗЕМНИХ ЗЛІТНО-ПОСАДКОВИХ ПЕРЕМІЩЕНЬ МОДИФІКАЦІЙ ЛІТАКІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ НА РІВНІ ЇХ БАЗОВОГО ВАРІАНТА". Aerospace technic and technology, № 8 (25 грудня 2018): 10–17. http://dx.doi.org/10.32620/aktt.2018.8.02.

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The problem of improving the takeoff and landing runway characteristics of heavier modifications of the transport category aircraft was further developed on the condition of equality of ground displacements of heavier modifications and their base variant by creating a method of formation of the “take-off mass - thrust-to-weight ratio” characteristics and using the fundamentally new local structures of additional slotted spoilers in extendable flaps and additional energetic chambers in landing gear shock absorber systems. The development of such a method and the use of additional slotted spoile

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34

Brewczyński, D., and G. Tora. "Analysis of Links Positions in Landing Gear Mechanism." International Journal of Applied Mechanics and Engineering 19, no. 3 (2014): 503–12. http://dx.doi.org/10.2478/ijame-2014-0033.

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Abstract This article contains a kinematic analysis of an aircraft chassis mechanism in a range of positions. The mechanism of the chassis is made up of several smaller subsystems with different functions. The first mechanism is used to eject the chassis before landing (touchdown) and fold it to hatchway after the lift off. The second mechanism is designed to perform rotation of the crossover with the wheel, in order to adjust the position of the wheel to fit it in the limited space in the hold. The third mechanism allows movement of the chassis resulting from the change in length of the dampe

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35

Pinello, Lucio, Omar Hassan, Marco Giglio, and Claudio Sbarufatti. "Preliminary Nose Landing Gear Digital Twin for Damage Detection." Aerospace 11, no. 3 (2024): 222. http://dx.doi.org/10.3390/aerospace11030222.

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An increase in aircraft availability and readiness is one of the most desired characteristics of aircraft fleets. Unforeseen failures cause additional expenses and are particularly critical when thinking about combat jets and Unmanned Aerial Vehicles (UAVs). For instance, these systems are used under extreme conditions, and there can be situations where standard maintenance procedures are impractical or unfeasible. Thus, it is important to develop a Health and Usage Monitoring System (HUMS) that relies on diagnostic and prognostic algorithms to minimise maintenance downtime, improve safety and

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36

El Mir, Haroun, Stephen King, Martin Skote, Mushfiqul Alam, and Simon Place. "Landing Gear Health Assessment: Synergising Flight Data Analysis with Theoretical Prognostics in a Hybrid Assessment Approach." PHM Society European Conference 8, no. 1 (2024): 10. http://dx.doi.org/10.36001/phme.2024.v8i1.4085.

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This study addresses a critical shortfall in aircraft landing gear (LG) maintenance: the challenge of detecting degradation that necessitates intervention between scheduled maintenance intervals, particularly in the absence of hard landings. To address this issue, we introduce a Performance Degradation Metric (PDM) utilising Flight Data Recorder (FDR) output during the touchdown and initial roll phases of landing. This metric correlates time-series accelerometer data from a Saab 340B aircraft’s onboard sensors with non-linear response dynamic models that predict expected LG travel and reaction

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37

Lernbeiss, R., and M. Plöchl. "Simulation model of an aircraft landing gear considering elastic properties of the shock absorber." Proceedings of the Institution of Mechanical Engineers, Part K: Journal of Multi-body Dynamics 221, no. 1 (2007): 77–86. http://dx.doi.org/10.1243/1464419jmbd63.

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38

Tilley, D. G., and S. P. Tomlinson. "Computer Simulation of the Bi-Stable Valve in the A340 Landing Gear." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 210, no. 3 (1996): 261–70. http://dx.doi.org/10.1243/pime_proc_1996_210_369_02.

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The increasing use of simulation for both circuit and component analysis in the aircraft industry has come about due to the requirement for acceptable transient as well as steady state performance of aircraft systems. The computer simulation package, Bathfp, developed at the Fluid Power Centre, University of Bath, is suitable for investigations into both of these. Utilities are provided which allow a model of a complicated system or component to be built up from its elements, which can be introduced to the model library of components so that particular dedicated areas of interest such as fligh

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Luong, Quoc-Viet, Quang-Ngoc Le, Jai-Hyuk Hwang, and Thi-My-Nu Ho. "6DOF Aircraft Landing Gear System with Magnetorheological Damper in Various Taxing and Touchdown Scenarios." Micromachines 16, no. 3 (2025): 355. https://doi.org/10.3390/mi16030355.

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This manuscript presents a new approach to describe aircraft landing gear systems equipped with magnetorheological (MR) dampers, integrating a reinforcement learning-based neural network control strategy. The main target of the proposed system is to improve the shock absorber efficiency in the touchdown phase, in addition to reducing the vibration due to rough ground in the taxing phase. The dynamic models of the aircraft landing system in the taxing phase with standard landing ground roughness, one-point touchdown, two-point touchdown, and third-point touchdown are built as the first step. Af

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Wei, Xiao Hui, Yong Wei Ding, Hong Nie, and Yong Ping Li. "Discharge coefficient calculation method of landing gear shock absorber and its influence on drop dynamics." Journal of Vibroengineering 20, no. 7 (2018): 2550–62. http://dx.doi.org/10.21595/jve.2018.19049.

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Asthana, Chandra B., and Rama B. Bhat. "A Novel Design of Landing Gear Oleo Strut Damper Using MR Fluid for Aircraft and UAV’s." Applied Mechanics and Materials 225 (November 2012): 275–80. http://dx.doi.org/10.4028/www.scientific.net/amm.225.275.

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Most landing gears used in aircraft employ very efficient oleo-pneumatic dampers to absorb and dissipate the impact kinetic energy of the aircraft body frame. A single-acting shock absorber is most commonly used in the oleo strut that has a metering pin extending through the orifice, which can vary the orifice area upon compression and extension of the strut. This variation is adjusted by shaping the metering pin so that the strut load is fairly constant under dynamic loading. In this paper, it is proposed to further change the damping coefficient as a function of time in order to achieve a se

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Feria Alanis, Aaron, Ahmed A. Sheikh Al-Shabab, Antonis F. Antoniadis, Panagiotis Tsoutsanis, and Martin Skote. "A Mixed-Elastohydrodynamic Lubrication Model of a Capped-T-Ring Seal with a Sectioned Multi-Material Film Thickness in Landing Gear Shock Absorber Applications." Fluids 9, no. 12 (2024): 271. http://dx.doi.org/10.3390/fluids9120271.

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Numerical investigations of capped T-ring (CTR) seals performance in reciprocating motion for landing gear shock absorber applications are presented. A lubrication model using the Elastohydrodynamic lubrication theory and deformation mechanics is developed in a multi-material contact zone, and a procedure for coupling fluid and deformation mechanics is introduced. By conducting Finite Element Method (FEM) simulations, the static contact pressure is obtained, which subsequently is used within the model developed herein consisting of a modified Reynolds equation and an asperity contact model, to

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Sienicki, Jaroslaw, Wojciech Zórawski, Adam Dworak, Piotr Koruba, Piotr Jurewicz, and Jacek Reiner. "Cold spraying and laser cladding as an alternative to electroplating processes." Aircraft Engineering and Aerospace Technology 91, no. 2 (2019): 205–15. http://dx.doi.org/10.1108/aeat-01-2018-0071.

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Purpose The purpose of this paper is to propose cold spraying and laser cladding processes as alternatives to cadmium and chromium electroplating, respectively. There are many substances or chemicals within the coating technology that can be identified as substances of very high concern because of their carcinogenic or mutagenic nature. Cadmium and chromium undoubtedly belong to these items and are the basic constituents of electrolytic coating processes. Finding an alternative and adapting to the existing restrictions of the usage of such hazardous products stands for many to be or not to be

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Mendoza Lopetegui, José Joaquín, Gianluca Papa, Marco Morandini, and Mara Tanelli. "Shock Absorber Leakage Impact on Aircraft Lateral Stability During Ground Handling Maneuvers." Journal of Guidance, Control, and Dynamics, February 1, 2023, 1–17. http://dx.doi.org/10.2514/1.g006933.

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Aircraft braking maneuvers are safety-critical on-ground motions that exhibit complex dynamics and significant dependence on system operating conditions. The fundamental interface between the aircraft and the ground is the landing gear. Among the landing gear components, the shock absorbers may be subject to gas leakage during their lifetime, which is an anomaly that could compromise the lateral stability properties of the aircraft on the operating regimes found during braking maneuvers. In this paper, an explicit link is established between main landing gear shock absorber leakage and aircraf

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Kiefer, J., M. Ward, and M. Costello. "Rotorcraft Hard Landing Mitigation Using Robotic Landing Gear." Journal of Dynamic Systems, Measurement, and Control 138, no. 3 (2016). http://dx.doi.org/10.1115/1.4032286.

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A unique, beneficial feature of rotorcraft is their flexibility in aircraft-to-ground interfacing. For a variety of reasons, hard landings can occur when the descent rate of the aircraft is larger than intended. The resulting impact can result in vehicle damage, structural failure, injuries, etc. To reduce these risks, an attractive solution is the implementation of a robotic legged landing gear (RLLG) system. The system softens a hard landing by acting as a shock absorber with a relatively large stroke, allowing the aircraft to decelerate over a much larger distance compared with a tradition

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Arık, Ahmet Enes, and Boğaç Bilgiç. "Fuzzy control of a landing gear system with oleo-pneumatic shock absorber to reduce aircraft vibrations by landing impacts." Aircraft Engineering and Aerospace Technology, July 29, 2022. http://dx.doi.org/10.1108/aeat-01-2022-0028.

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Purpose The purpose of this paper is to control a landing gear system with an oleo-pneumatic shock absorber with the fuzzy controller. Design/methodology/approach The landing gear system with an oleo-pneumatic shock absorber is modeled mathematically. A fuzzy controller is designed for reducing aircraft vibrations. Stroke velocity and main mass velocity parameters were used to decide variable gas pressure with the fuzzy controller. Findings The fuzzy controller, designed according to stroke velocity and main mass velocity, reduces aircraft vibrations by the landing impacts. The controller can

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Kim, Tae-Uk, JeongWoo Shin, and Sang Wook Lee. "Design and Testing of a Crashworthy Landing Gear." ASCE-ASME J Risk and Uncert in Engrg Sys Part B Mech Engrg 3, no. 4 (2017). http://dx.doi.org/10.1115/1.4036663.

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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 (BOV) is implement

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Sumerin, A. A., and G. A. Shcheglov. "Simulation of the aircraft landing gear legs with the plastically deformable shock absorbers." Engineering Journal: Science and Innovation, no. 6 (138) (June 2023). http://dx.doi.org/10.18698/2308-6033-2023-6-2284.

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The paper considers possibility of using a new depreciation scheme in regard to the wheeled three-column landing gear leg of the aerospace light aircraft based on using the three-section one-time crash box, which could be replaced during the inter-flight maintenance. Normal and abnormal operation of the landing gear legs was numerically simulated in the LS-DYNA package of the ANSYS software. Energy absorbing characteristics of the crash boxes with various geometry and several landing gear leg schemes were analyzed in order to identify the design having most predictable and forecasted deformati

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"Effects of Spring and Damper Elements in Aircraft Landing Gear Dynamics." International Journal of Recent Technology and Engineering 8, no. 5 (2020): 4265–69. http://dx.doi.org/10.35940/ijrte.d9247.018520.

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In this study a typical Aircraft Landing Gear with shock absorber was modeled a Mass-Spring-Damper System. Basic components of the system were explained. The equations of the model was presented. Aircraft Landing Gear was also modeled in Matlab/Simulink for a given set of aircraft parameters. A case study for an Aircraft Landing Gear was solved and results were presented. Results included the variation of spring (k1 and k2 ) and damping coefficient (b) in a given interval to show their effects on the impact force and displacement of landing gear as main outputs to consider. Effect of damping c

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Ahmad, Muhammad Ayaz, Syed Irtiza Ali Shah, Taimur Ali Shams, Ali Javed, and Syed Tauqeer ul Islam Rizvi. "Comprehensive design of an oleo-pneumatic nose landing gear strut." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, December 13, 2020, 095441002097937. http://dx.doi.org/10.1177/0954410020979378.

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A comprehensive design cycle of a nose landing gear strut having an oleo-pneumatic shock absorber for a lightweight aircraft is proposed. Design and analysis of a retractable nose landing gear according to Airworthiness Standards FAA FAR Part 23 have been carried out. This research is focused on mathematical modeling of an oleo-pneumatic strut with an analytical solution of design variables at static and dynamic loading conditions. The variation of spring and damping characteristics of an oleo-pneumatic shock absorber with the stroke length is also presented. Feasibility of equivalent mechanic

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