An energy absorption dynamic test of landing gear for 1400 kg general aviation aircraft

• Autorzy: Jakubowski R. , Tywoniuk A.

Identyfikatory

DOI

10.5604/12314005.1217202

• Języki publikacji: EN

Abstrakty

EN

Landing gear as one of the most crucial systems ensuring safe take-off and landing must be rigorously tested before first flight of each newborn aeroplane. In the static and dynamic tests strength, functionality and energy absorption capability of landing gear components (wheel, brake, shock absorber, support structure and retraction system) are verified. One of the most important is an energy absorption dynamic test. During drop, test campaign a landing gear damping system is not only verified but also optimized by changing parameters like: damping orifice diameter, geometry of gas and oil chambers and shock absorber and tire inflation pressures. This process often takes substantial amount of time because of influence of the mentioned parameters on landing gear energy absorption efficiency. Other factors like landing configuration spin up and spring back effects generated during wheel contact with the ground [1] also have to be considered in the energy absorption optimization process. The paper describes the landing gear drop test campaign and main challenges, which have to be overcome to achieve optimal dynamic characteristics of the system. The tested object was the main landing gear of the 1400 kg General Aviation aircraft certified in accordance with EASA CS-23 regulations. The drop test campaign was carried out in Warsaw Institute of Aviation Landing Gear Laboratory.

Słowa kluczowe

EN

landing gear; energy absorption; drop test; shock absorber

• 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: 2016
• Tom: Vol. 23, No. 4
• Strony: 159--165
• Opis fizyczny: Bibliogr. 5 poz., rys.

Twórcy

autor

Jakubowski R.

• Warsaw Institute of Aviation Department of Transport and Energy Conversion Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: [phone]

autor

Tywoniuk A.

• Warsaw Institute of Aviation Department of Transport and Energy Conversion Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: [phone]

Bibliografia

• [1] Currey, N., Aircraft Landing Gear Design: Principles and Practices, AIAA (American Institute of Aeronautics & Ast, 1988.
• [2] Skorupka, S., Paprzycki, I., Laboratoryjne badanie podwozi lotniczych, Institute of Aviation, Warsaw 2014.
• [3] Zaleski, J., Obciążenia podwozia samolotu AT-6 wg przepisów CS-23 dla masy startowej 1400 kg, AT-P AVIATION Sp. z o.o., Warsaw 2014.
• [4] Certification Specifications for Normal, Utility, Aerobatic, and Commuter Category Aeroplanes CS23, European Aviation Safety Agency, 2009.
• [5] Wykonanie próby zrzutowej z energią dopuszczalną i nadmiarową podwozia głównego nr AT6.41.000.00.0 do samolotu AT-6, na zgodność z przepisami, 0114/09/LW/2015/RAP CS-23, Institute of Aviation, Warsaw 2015.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.