Relevant bibliographies by topics / Landing gear leg

Contents

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

Academic literature on the topic 'Landing gear leg'

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

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Journal articles on the topic "Landing gear leg"

1

Miyata, Kazunori, Takamasa Sasagawa, Takahiro Doi, and Kenjiro Tadakuma. "A Study of Leg-Type Landing Gear for Aerial Vehicles - Development of One Leg Model -." Journal of Robotics and Mechatronics 23, no. 2 (April 20, 2011): 266–70. http://dx.doi.org/10.20965/jrm.2011.p0266.

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The novel aerial landing gear we propose has multiple articulated legs requiring no flat facilities such as landing fields. Smooth landing in rough terrain is enabled by multiple articulated legs changing shape and mechanical impedance as needed. For soft landings, it decreases velocity from fast to slow. Mechanical leg design is discussed and soft landing performance demonstrated.
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Doi, Takahiro, Kazunori Miyata, Takamasa Sasagawa, and Kenjiro Tadakuma. "Multi-Leg System for Aerial Vehicles." Journal of Robotics and Mechatronics 24, no. 1 (February 20, 2012): 174–79. http://dx.doi.org/10.20965/jrm.2012.p0174.

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The multi-leg system concept for aerial vehicles proposed here is a novel alternative to conventional landing gear and realizes adaptation to undulating terrain, shock absorption, ground-surface gripping, and chassis support after landing. The sections that follow discuss multi-leg system concept, mechanical shock absorption design, simulation, and experimental results.
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Gerhardinger, David, Anita Domitrović, and Ernest Bazijanac. "Fatigue Life Prognosis of a Light Aircraft Landing Gear Leg." Annual Conference of the PHM Society 12, no. 1 (November 3, 2020): 9. http://dx.doi.org/10.36001/phmconf.2020.v12i1.1245.

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Aircraft components are subject to fatigue damage. The prediction of fatigue life has significant influence on maintenance and flight operations. Light aircraft, designed for recreational purposes, have vital components that are subject to a hard time maintenance approach. The focus of this article is on a simple method for predicting fatigue life. The method is applied to a light aircraft’s fixed landing gear leg. The landing gear leg is modelled in a computer aided design environment. The load spectrum is determined, based on a characteristic flight profile. Principal strains are determined with finite element analysis. Fatigue life is calculated with the Coffin-Manson low cycle fatigue relation. The Palmgren-Miner rule is applied, and cumulative damage is determined. The results are compared to actual landing gear leg fatigue damage and the hard time replacement interval which is given in the corresponding maintenance manual.
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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 (December 12, 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 angular velocity and displacement velocity of each landing leg. First, the control method for the variable damper is presented. Second, the result of a landing experiment conducted in a two-dimensional plane is shown. These results indicate that the proposed semi-active landing gear system is effective for preventing the overturning of the lander on inclined terrain.
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Lefánti, R., Gabor Kalácska, I. Oldal, and K. Petróczki. "Developing small-aircraft service and re-construction of landing-gear leg support." International Journal Sustainable Construction & Design 2, no. 1 (November 6, 2011): 99–105. http://dx.doi.org/10.21825/scad.v2i1.20465.

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The programs of air-operation and service in the aviation engineering - within this at light-aircraft too - takeplace according to rigorous regulations [6, 7]. There are such machine units and parts which regulation areincomplete, for instance such is the landing-shaft seating. We have developed a new maintenance modelbased on the traditional ones, which offers new information exchange modul for e.g. weak point reconstruction and uses paper based documentation and modern remote maintenance as well. Beside thenew model we have worked out a renewing solution of the often failed landing-gear leg support applyingfield and laboratory test and FEM modelling to fill up as an engineering example for the information modulof the new maintenance model.
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MIYATA, Kazunori, Takamasa SASAGAWA, Takahiro DOI, and Kenjiro TADAKUMA. "1A2-C22 A study of Leg-type Landing Gear for Aerial Vehicles : Development of One Leg Model." Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2010 (2010): _1A2—C22_1—_1A2—C22_4. http://dx.doi.org/10.1299/jsmermd.2010._1a2-c22_1.

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Bagrov, K. V. "Numerical simulation of planar oscillations of a landing gear leg along the longitudinal axis of an aircraft during the landing impact." Sibirskii zhurnal industrial'noi matematiki 22, no. 3 (June 14, 2018): 3–7. http://dx.doi.org/10.33048/sibjim.2019.22.301.

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Bagrov, K. V. "Numerical Simulation of Planar Oscillations of a Landing Gear Leg along the Longitudinal Axis of an Aircraft During the Landing Impact." Journal of Applied and Industrial Mathematics 13, no. 3 (July 2019): 385–89. http://dx.doi.org/10.1134/s1990478919030013.

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SASAGAWA, Takamasa, Kazunori MIYATA, Takahiro DOI, and Kenjiro TADAKUMA. "1A2-O01 A Study of Leg-type Landing Gear for Aerial Vehicles : Development of Two Leg Model(Aerial Robot and Mechatronics)." Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2011 (2011): _1A2—O01_1—_1A2—O01_4. http://dx.doi.org/10.1299/jsmermd.2011._1a2-o01_1.

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DOI, Takahiro, and Kenjiro TADAKUMA. "2A1-I08 A Study of Leg-type Landing Gear for Aerial Vehicles : Development of Flying Three Leg Modelt(Aerial Robot and Mechatronics(1))." Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2012 (2012): _2A1—I08_1—_2A1—I08_2. http://dx.doi.org/10.1299/jsmermd.2012._2a1-i08_1.

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Dissertations / Theses on the topic "Landing gear leg"

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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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Book chapters on the topic "Landing gear leg"

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Spalart, P., M. Shur, M. Strelets, and A. Travin. "Initial RANS and DDES of a Rudimentary Landing Gear." In Progress in Hybrid RANS-LES Modelling, 101–10. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14168-3_8.

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

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Borkowski, Paweł, Adam Dacko, and Mirosław Rodzewicz. "Synthesis and Structural Analysis of High Strength Composite Flexible Landing Gear Legs." In Proceedings of the 13th International Scientific Conference, 49–61. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-50938-9_6.

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4

"Failures in Landing Gear Spring Legs." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001902.

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Conference papers on the topic "Landing gear leg"

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Chong, Chung-Ook, and Rollin Dix. "Impulse-Momentum in Spacecraft Landing: Analysis and Experiment." In ASME 7th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2004. http://dx.doi.org/10.1115/esda2004-58054.

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Impulse-momentum methods of analysis developed for rigid body impacts are applied in this paper to predict forces acting in a simplified spacecraft model during a touchdown impact. This paper presents both analytic and experimental effort for a complex, multi-body impacting system that include friction and deformable elements. Specifically, we analyze a vertically moving guided mass representing a landing spacecraft to which is attached a telescopic, energy-absorbing leg. The landing gear, which is used in our study, employs crushable material in the leg, strut, and foot plus surface friction to absorb the landing shock. The experimental setup consists of simplified landing system, and accelerometers for the dynamic measurement. Acceleration data collected via data acquisition system is converted to the crushing, normal and tangential velocities. The results showed good agreement between the analysis and experiment for the first phase of motion. The derivation of limiting condition equations for all possible alternatives for the second phase is incomplete. We conclude that the challenges of deriving and testing for all motion phase ending events make the impulse-momentum method inferior to straight-forward dynamic simulation as a design tool.
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Peng, Chengyang, A. M. Masum Bulbul Chowdhury, Jinsai Cheng, Richard L. George, and Tao Shen. "Development of a Robotic Landing System for UAVs Applied in Various Terrains." In ASME 2020 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/detc2020-22606.

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Abstract Unmanned Aerial Vehicles (UAVs), often referred as drones, have been widely implemented for civilian, commercial, search and rescue, and military operations with the advantages of easy deployment, low cost, automation, as well as, most importantly, allowing the execution of dangerous or difficult tasks remotely and safely. However, current UAVs are equipped with a skid or wheel landing gear that limits the application of UAVs to an even and flat ground for safe landing and taking off; this constraint impedes the development of UAVs for application in extreme environments, such as war fields and remote wilderness where proximate level ground is inaccessible. The ability of UAVs to land on un-level ground would help broaden the application of UAVs; in particular, the ability to go beyond thermal imaging to locate a lost hiker with the ability to land and deliver life-sustaining resources in a more timely manner offers a benefit to human rescue missions. This paper presents an innovative robotic landing system consisting of three slanted legs, each individually controlled by a motor. The footpad of each leg has an integrated force sensor for detecting ground touch. An inclinometer is installed on the platform of the landing system to sense the UAVs orientation during landing. Thus, the landing system can keep the platform horizontal when it lands on the ground by extending or retracting the legs. The feasibility and effectiveness of the robotic method have been demonstrated by several indoor and outdoor experiments.
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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, all using simplified but representative equations. Emphasis is placed on developing a methodological framework and studying the evolution of the average temperature in the TZI (thermal zone of interest) while taxiing and taking-off.
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Giret, Jean-Christophe, Alois Sengissen, Stephane Moreau, and Jean-Christophe Jouhaud. "Prediction of LAGOON landing-gear noise using an unstructured LES Solver." In 19th AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2113.

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Peng, Shia-Hui. "Hybrid RANS-LES Computations of Turbulent Flow over Rudimentary Landing Gear." In 31st AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2913.

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Nadan, Paul M., and Christopher L. Lee. "Computational Design of a Bird-Inspired Perching Landing Gear Mechanism." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-86615.

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To support the design of a mechanism with two opposing, underactuated, multi-segmented feet that enables a small UAV to grasp and perch upon a branch or similar structure, a hybrid empirical-computational model has been developed that can be used to predict whether the mechanism can kinematically grasp structures with a range of cross-section shapes and sizes in various orientations and to quantify the forces exerted by the grasp. The model, based on experimentally-determined parameters, relates the curvature of the feet to the displacement and tension of the cable tendon which is related in turn to the weight of the UAV. The working principle of the landing gear follows the anatomy of birds that grasp and perch as tendons in their legs and feet are tensioned. Results demonstrate how the model can be used to simulate and evaluate grasping in order to determine the size and weight of a UAV for landing and perching upon a range of target structures.
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Hooper, Joshua, Martin Garcia, Paul Pena, and Ayse Tekes. "Design of a Compliant Jumping Robot With Passive Stabilizer." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23171.

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Abstract This study presents the design and development of a compliant multi-link hopping mechanism actuated by a single DC motor. Two main design goals are to have a single piece designed main body for the jumping robot and a passive stabilizer to allow consecutive jumps. Mechanism consists of monolithically designed large deflecting main body incorporating the gears and initially curved flexure hinge. Due to the limitations of the design goal, revolute motion between top and bottom legs on the main body are realized by a compliant link which replaces the need of ball bearings. Also, continuous energy store and release during jumping is ensured by the same flexure hinges. Passive self-righting cage is attached to the bottom of the main body to maintain upright position both in landing and takeoff. The cage allows the center of mass to stay in the vertical plane to prevent tilting. During landing, cage absorbs the impact and allows the main body to roll to its initial configuration so that the robot can complete jumping. Mechanism parts including the cage are 3D printed using PETG. Design optimization of the body parts including the rigid legs and flexure hinges are analyzed both experimentally and analytically. Finite element analysis is performed to calculate the equivalent stiffness and natural frequency of the jumping robot and simplified mathematical model is derived using rigid body dynamics.
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