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Relevant bibliographies by topics / Calculation of landing gear loading

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Academic literature on the topic 'Calculation of landing gear loading'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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Journal articles on the topic "Calculation of landing gear loading"

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Protsenko, V. O., V. O. Nastasenko, M. V. Babiy, and A. O. Bilokon. "MARINE RAM-TYPE STEERING GEAR DETAILS LOAD TRANSFER FEATURES." Shipping & Navigation 30, no. 1 (2020): 107–16. http://dx.doi.org/10.31653/2306-5761.30.2020.107-116.

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he article deals with steering gears, used on marine and river ships, namely with ram-type steering gears. Article topicality due to the fact that ship controllability and sailing safety depends of steering gears reliability. Reliability could be increased through the refinement of processes, which took place during the perception and transfer of load. Process of lateral force perception by plungers and guide beams is studied theoretically. It is shown that perception depends of gap size between plunger and sleeve and could pass in one, two or three stages. Those stages are characterized chang

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Онищенко, В. М. "МАТЕМАТИЧНЕ МОДЕЛЮВАННЯ УДАРУ ПРУЖНОГО ЛІТАЛЬНОГО АПАРАТА НА ПОСАДЦІ". Open Information and Computer Integrated Technologies, № 84 (2 липня 2019): 165–69. http://dx.doi.org/10.32620/oikit.2019.84.09.

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The development of a direction oriented towards the creation and advanced operation of mathematical models (MM) of aircraft - their mathematical doublers on the example of calculating the impact dynamics and loading of an elastic plane on landing is shown. The relevance of such an approach in the design and operation of aircraft due to the complexity and limited capabilities of terrestrial experimental facilities and flight experiment are noted. The example of a lightweight aircraft presents the results of the application of a simplified MM and the numerical calculation of the impact dynamics

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Soetanto, Maria Fransisca, and Rachmad Imbang Tritjahjono. "Study the Strength of Material and Composite Structures of Belly-Landing Mini UAV." Applied Mechanics and Materials 842 (June 2016): 178–85. http://dx.doi.org/10.4028/www.scientific.net/amm.842.178.

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This paper consists of the design and analysis of the strength of material composite of the fuselage of a Belly-Landing Mini Unmanned Aerial Vehicle (UAV). A belly landing UAV occurs when an UAV lands without its landing gear and uses its underside, or belly, as its primary landing device. Belly landings carry the risk that the UAV may flip over, disintegrate, or catch fire if it lands too fast or too hard [1], so the more important designs parameters for materials used are the specific strength and specific stiffness. Specific strength is defined as the ultimate tensile strength divided by ma

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Конышев, Д. С. "МЕТОД ВИЗНАЧЕННЯ ОСНОВНИХ ПАРАМЕТРІВ ВАНТАЖНОГО ЛЮКА В ХВОСТОВІЙ ЧАСТИНІ ФЮЗЕЛЯЖУ ЛІТАКІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ". Open Information and Computer Integrated Technologies, № 87 (30 червня 2020): 52–71. http://dx.doi.org/10.32620/oikit.2020.87.02.

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A method has been developed for determining principal parameters for aft cargo door of transport aircraft. A list of input data is given and a technique for finding them is described. An example based on an existing transport aircraft is considered. The following has been used as source data: basic cargo nomenclature to be transported by the designed aircraft, cargo overall dimensions and weight, methods of loading and mooring, loading facilities. More over the design, operational and regulatory parameters are needed, such as landing gear configuration, its bottoming system, extension of rails

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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 (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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Ma, Jun Gong, Zhong Zhi Wu, Hao Ran Guo, and Jia Li. "Design and Simulation Study of a Certain Landing Gear Loading Simulation System." Advanced Materials Research 871 (December 2013): 69–76. http://dx.doi.org/10.4028/www.scientific.net/amr.871.69.

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The landing gear ground loading tests is a vital part before flight. As the motion of landing gear is three-dimensional motion,the traditional loading method cannot effectively simulate the pneumatic load on the ground. In order to simulate the load in the process of retraction/extension, a loading simulation system is proposed, including retractile system, position follow-up system and force servo loading system. This paper analyzes retraction/extension mechanism of the landing gear and builds up its mathematical model. A co-simulation model is developed in which the hydraulic system model an

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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

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Zhang, Lin Hai, Xiao Ye Qi, Jun Gong Ma, and Rong Rong Yang. "The Load Simulation Research of Nose Landing Gear Steering." Applied Mechanics and Materials 687-691 (November 2014): 701–5. http://dx.doi.org/10.4028/www.scientific.net/amm.687-691.701.

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The nose landing gear is a vital component of an aircraft,which has an important impact on the safety of the aircraft.This paper studies the system of nose landing gear steering on the basis of the gear and rack mechanism durability test of a certain type of civil aircraft landing gear steering. Furthermore,it puts forward a method of passive loading,which can simulate the friction when the nose landing gear reciprocating turning,and establishes the mathematical model. The simulation results show that the simulator can meet the requirements of load,and laid a theoretical foundation for the sub

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Zhang, Wei, Qian Dong, and Xian Min Zhang. "Study on Mechanical Response Changes of Pavement to Aircraft Loads with Different Landing Gear Configurations." Applied Mechanics and Materials 723 (January 2015): 60–64. http://dx.doi.org/10.4028/www.scientific.net/amm.723.60.

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The finite element model of runway is established based on elastic layered theory and it is used for analyzing the influence on mechanical responses due to changes of main landing gear configurations. The results show that the more the total number of wheels on a main landing gear is, the smaller displacement peak, maximum tensile stress under panel bottom and solid foundation influence depth are in conditions that aircraft loads are equal. When the landing gear spacing is smaller, the displacement curves in the loading area are gentler. The changes of configurations influence little on displa

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Chen, Fei, Yong Lv, and Zhi Wei Xing. "The Strength Analysis of Aircraft Landing Gear Strut Based on ANSYS." Advanced Materials Research 490-495 (March 2012): 2686–90. http://dx.doi.org/10.4028/www.scientific.net/amr.490-495.2686.

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Because the landing gear structure is complicated, it is difficult to draw accurate stress and strain distribution through the theoretical calculation. In this paper, based on the modeling and stress analysis of the buffer mechanism of aircraft landing gear, by converting the stress of a dynamic system into a static stress, the force of the landing gear struts are calculated. This paper analyzes the strength of the aircraft main landing gear by using computer simulation technology and finite element analysis, it provides an effective basis for maintenance and the damage prediction

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Dissertations / Theses on the topic "Calculation of landing gear loading"

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Chren, Tibor. "Návrh podvozku pro letoun Rapid 600." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-229317.

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This diploma thesis deals with design of retractable landing gear for Rapid 600 aircraft. The main purpose of this thesis is to analyze different retraction options for front and main landing gear and resulting selection of suitable variants. The thesis is consequently concerned with design of selected options including proposal of automatic landing gear control system and specifying the features and characteristics of this system. In the thesis there is also included the analysis of critical flight conditions which could be detected by this system.

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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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Cejpek, Jakub. "Analysis of Aeronautical Composite Structures under Static Loading." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-385288.

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Poměrně velké množství soukromých firem v České republice vyrábí lehká sportovní letadla. Značná část těchto letadel využívá kompozitní pružiny ve svých přistávacích zařízení. Tyto pružiny jsou buďto menší díly, absorbující energii (na příďové noze či ostruze), anebo jde celé pružnice hlavního podvozku. Všechny tyto pružiny sdílí základní charakteristiky: jsou vyrobeny převážně z jednosměrného kompozitu s významnou tloušťkou, hlavním druhem zatížení je ohybový moment a jsou očekávány velké deformace. Podobnou charakteristiku můžeme použít i při popisu hlavního nosníku křídla. Jak vypadá návrh

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Riccardo, Michele. "Calculation and tests for Shark CS-LSA type certification and preliminary design for CS-VLA certification." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

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The purpose of this work was to calculate and to test different aircraft components according to the CS-LSA (Light Sport Aircraft) airworthiness for Shark s.r.o. Shark was designed to fit into European ultralight category and it was approved according to the UL-2 Czech Republic requirement of Light Aircraft Association and LTF-UL German requirement for “Sport Flying Vehicles”. In the design phase were considered also the ASTM standards for Light Sport Aircraft (LSA) valid in USA and accepted by European regulation CS-LSA. The maximum take-off weight will be increased from 472.5 kg up to 600 kg

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Štěpánek, Jan. "Návrh konstrukce křídla a podvozku kluzáku TST 14 MC." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228596.

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Modification of TST-14 MC glider, calculation of flight envelope, distribution of lift on the wing, calculation of loading cases of the wing, strength check of choosen construction nodes, design of the landing gear retraction mechanism, setting up loading of landing gear according to ULKM, strength check of landing gear

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Růžička, Miroslav. "Návrh repliky letounu L-40 "Meta Sokol" - trup." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2008. http://www.nusl.cz/ntk/nusl-227921.

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This diploma thesis deals with the design of all-metal construction of fuselage of the replica L-40 Meta Sokol aircraft on the basis of CS-VLA regulation. As far as the aircraft is concerned, the thesis establishes the load of tail surfaces, landing gear and engine bed. Futhermore, it designs the construction of fuselage, tail landing gear, including the system of its retraction, wing-fuselage connection, engine bed and the primary design of cockpit. In the end, the thesis focuses on the fuselage production technology.

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Chen, Chan-Ming, and 陳建銘. "The Critical Loading Analysis ofLight-Sport Aircraft Landing Gear." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/59916265678686668374.

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碩士<br>淡江大學<br>航空太空工程學系碩士班<br>96<br>This research dependent on Finite Element Method to building up analyzing ability of light sport aircraft critical parts loading capability to reduce exploitation time of developing light-sport aircraft design. By using the main landing gear of Zenith STOL CH 701 as simulate test object, construct the static analyze and dynamic drop test base on the Finite Element Method, and use the static/dynamic tests to analyze landing gear structure of STOL CH 701, obtain and discuss the results under the static/dynamic tests. This research use a systematize analyze proc

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Yu, Tsung-Hsign, and 游宗憲. "Loading Effect of Material and Shape on The Light-Sport Aircraft Landing Gear." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/51003143309915907149.

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碩士<br>淡江大學<br>航空太空工程學系碩士班<br>99<br>As the material development of commercial aircraft, light sport aircraft markets are starting to focus on useing composite materials.The U.S. light sport aircraft market by regulatory S-LSA (Special Light-Sport Aircraft) are standard models in 53% of the light sport aircraft to use composite materials, which means that composite materials have become the mainstream of light sport aircraft manufacturing materials. The purpose of this research is use ANSYS, LS-DYNA, HyperMesh to analysis the different materials,different loads,different shape,different spee

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Book chapters on the topic "Calculation of landing gear loading"

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Cosseron, Kévin, Renaud Gras, David Mellé, Jean-Frédéric Diebold, François Hild, and Stéphane Roux. "Inverse Identification of the Loading Applied by a Tire on a Landing Gear Wheel." In Residual Stress, Thermomechanics & Infrared Imaging, Hybrid Techniques and Inverse Problems, Volume 7. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-95074-7_3.

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Conference papers on the topic "Calculation of landing gear loading"

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Lockard, David, Mehdi Khorrami, and Fei Li. "High Resolution Calculation of a Simplified Landing Gear." In 10th AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2887.

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Jacazio, Giovanni, and Gualtiero Balossini. "A Mechatronic Active Force Control System for Real Time Test Loading of an Aircraft Landing Gear." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-86148.

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This paper describes an electronically controlled active force control system that was recently developed to provide real time loading for the tests of a landing gear. As the landing gear moves during the test, a force is generated on the landing gear in order to ensure that its dynamics is identical to that that would occur during its operation in an actual flight. Since landing gear deployment and retraction can occur at different environmental and flight conditions, the load profile that must be developed by the force control system depends on the simulated flight condition and is determine

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Pugh, Steven Daniel, Juan Juan Zhu, and Rob S. Dwyer-Joyce. "Experiments on Grease Performance in Aircraft Landing Gear Pin Joints." In STLE/ASME 2010 International Joint Tribology Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ijtc2010-41101.

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A pin joint simulation machine has been built to test a real landing gear pin joint under realistic loading and reciprocation conditions. The pin is loaded hydraulically using a hydraulic actuator to apply a fixed displacement cycle whilst measuring the reactive torque. The machine was used to measure the torque cycle (and hence friction coefficient) required to operate the joint. In this work a method of evaluating different formulation greases has been proven. This involved measuring their frictional torque and also evaluating performance using a Sommerfeld type approach that displays the di

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Wang, Yue, Dan Gao, and Li Wang. "An Engineering Software Developed Based on ICAO Standard Calculation Method for Analyzing Civil Jet Landing Gear Floating Characteristics." In the 2018 International Conference. ACM Press, 2018. http://dx.doi.org/10.1145/3230348.3230373.

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Yang, Yu, Hu Tengyue, Zeng Chenhui, Bian Zhi, and Meng Lihua. "Element analysis and wear longevity calculation of an O-ring in the actuator cylinder of a certain aircraft landing gear." In 2017 Prognostics and System Health Management Conference (PHM-Harbin). IEEE, 2017. http://dx.doi.org/10.1109/phm.2017.8079282.

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Syzrantsev, Vladimir N., Juriy G. Denisov, Vyacheslav P. Wiebe, and Andrey A. Pazyak. "The Design and Production of Drives Based on Pan Precess Gear for Oil and Gas Machinery." In ASME 2015 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/detc2015-47096.

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The paper describes the results of design and production of new generation valve drives for oil and gas machinery. The drives are based on the use of pan precess gear. The gear has a high performance coefficient (88…90%), smooth operation, low starting torque and ability to remain functioning even under severe conditions of operation. Basic dependencies for geometric calculation of the gear are showed. The problem of synthesizing geometric parameters of the gear as well as calculating parameters and settings of tools (circular cutting heads) and gear-cutting machines has been solved. The resul

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Gabrys, Jonathan W., and Joshua K. Schatz. "Simulation of a CH-47 Water Crash Event." In ASME 2002 Pressure Vessels and Piping Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/pvp2002-1467.

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According to a Naval Aircraft Crash Report for 1972 to 1981, 45.3 % of helicopter mishaps occurred on water. For these incidents, the landing gear would not be effective. Instead, the lower portion of the helicopter is directly involved. Understanding how a helicopter reacts to such loading is critical for designing them to survive these incidents. This analysis investigates a CH-47 water crash event for various impact-speeds and predicts pilot accelerations during each event. The finite element analysis package LS-DYNA was used to simulate the fluid structure event between a full CH-47 model

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Das, Partha S. "Design and Analysis of a New Accessory Gearbox Housing for a Gas Turbine Engine." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-46747.

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Accessory Gearbox (AGB) Housing is one of the most critical components of a gas turbine engine that lies between the core engine & the aircraft. The function of the AGB Housing is to provide support for the gear drive assembly that transfers power from the engine to the engine accessories and to the power takeoff drive for the aircraft accessories. The housing also functions as an oil tight container and passageway for lubrication. In addition, the AGB housing provides mount points to attach engine/aircraft support accessories, including the engine mount points to the aircraft. The complex

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Chuanping, Liu, Tianluan Liu, and Jian Jia. "Study on bearing structure and joint seismic resistance of large span non-landing arch on high-speed railway station." In IABSE Congress, New York, New York 2019: The Evolving Metropolis. International Association for Bridge and Structural Engineering (IABSE), 2019. http://dx.doi.org/10.2749/newyork.2019.2295.

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<p>The main entrance of Chongqing West Railway Station adopts the non-landing compound arch with a span of 108m. In this paper, the nonlinear finite element theory is applied to analyze the bearing capacity and seismic ductility of the compound arch joints. Low frequency cyclic loading tests are performed on the 1/5 scale model. Based on the calculation and test results, a double beam structure and a section of steel truss are placed in the arch joints to bear the force of the arch. Moreover, the buckling-restrained brace (BRB) is placed in the lower part of the arch that enables most fo

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Reports on the topic "Calculation of landing gear loading"

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Heymsfield, Ernie, and Jeb Tingle. State of the practice in pavement structural design/analysis codes relevant to airfield pavement design. Engineer Research and Development Center (U.S.), 2021. http://dx.doi.org/10.21079/11681/40542.

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An airfield pavement structure is designed to support aircraft live loads for a specified pavement design life. Computer codes are available to assist the engineer in designing an airfield pavement structure. Pavement structural design is generally a function of five criteria: the pavement structural configuration, materials, the applied loading, ambient conditions, and how pavement failure is defined. The two typical types of pavement structures, rigid and flexible, provide load support in fundamentally different ways and develop different stress distributions at the pavement – base interface

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