Numerical testing of landing gear system for different drop velocities

• Autorzy: Krasoń W. , Małachowski J.
• Języki publikacji: EN

Abstrakty

EN

The FEM model of the landing gear was developed to determine efforts of individual structural members while simulating the landing-gear drop, and to investigate how the energy of such a system changes; also, to find what kinds of deformations occur in individual components, and to investigate into the effectiveness of the damping system. In the developed numerical model of the landing gear account was taken also of the support-wheel-related subassembly, which includes such elements as: the wheel pin, the wheel rim, and the tyre. All parts of this subassembly, belt in the tyre excluded, were represented with the flexible hexagonal elements. results of numerical analyses for some selected drop tests and results from experiments carried out on a real landing gear confirm high quality of results gained from the dynamic simulation in the model of a complete landing-gear configuration. The advantage of the presented numerical method is applicability there of to landing gear testing for the very wide range of drop velocities, what is impossible to be performed with other methods, including experimental testing work. Paper show the geometric model of the main landing gear, a discrete model with the shock-absorber model included, the fringe of the landing gear deformation at the flnal stage of touchdown phase respectively from experimental and numerical tests and the maps ofmaximum principal stresses and how they change within the area of the welded joint that connects the upper and lower levers of the main landing gear.

Słowa kluczowe

EN

landing gear; numerical simulation; drop velocities; touchdown

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2009
• Tom: Vol. 16, No. 4
• Strony: 241--246
• Opis fizyczny: Bibliogr. 11 poz., rys.

Twórcy

autor

Krasoń W.

autor

Małachowski J.

• Department for Mechanics and Applied Computer Science Military University of Technology Gen. Sylwestra Kaliskiego 2, 00-908 Warsaw, Poland tel: [phone], fax: [phone],

Bibliografia

• [1] Airoldi, A., Janszen, G., A design solution for a crashworthy landing gear with a new triggering mechanism for the plastic collapse of metallic tubes, Aerospace Sc. and Tech., Vol. 9, 445-455, 2005.
• [2] FAR–23: Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Category Airplanes,1966.
• [3] Fukashima, T., Shimonishi, H., Hayashi, K., Shiraishi, M., Simulation of a vehicle running on to a curb by using tire and vehicle FE models, 4th European LS-Dyna Users conference, Detroid 1998.
• [4] Hallquist, J. O., LS-Dyna. Theoretical manual, California Livermore Software Technology Corporation, 2005.
• [5] Hong-Chul, Young-Ha, H., Tae-gu, K., Failure analysis of nose landing gear assembly, Engineering Failure Analysis, Vol.10, pp.77-84, 2003.
• [6] Kajka, R., Nieliniowa analiza naprężeń w konstrukcjach grubościennych w warunkach obciążeń eksploatacyjnych, Politechnika Warszawska, Warszawa 2005.
• [7] Kaplan, M. P.,Wolff, T. A., Damage tolerance assessment of CASA, landing gear, Willis & Kaplan Inc., 2002.
• [8] Khapane, P. D., Simulation of asymmetric and typical ground maneuvers for large transport aircraft, Aerospace Sc. and Tech., Vol.7, pp. 611-619, 2003.
• [9] Lee, H. C., Hwang, Y. H., Kim, T., Failure analysis of nose landing gear assembly, Engineering Failure Analysis, Vol. 10, pp. 77-84, 2003.
• [10]Małachowski, J., Krasoń, W., Budzyński, A., Numerical investigations of shimmy vibrations in transport aircraft’s landing gear, NiT-Nauka Innowacje Technika, 3(10), pp. 38-43, 2005.
• [11]Małachowski, J., Wesołowski, M., Krasoń, W., Computational study of transport aircraft landing gear during touchdown. J. KONES Powertrain and Transport, Vol. 13, pp.187-195, 2006.