Laboratory investigations on landing gear ground reactions (load) measurement

• Autorzy: Skorupka Z.

Identyfikatory

DOI

10.5604/01.3001.0010.2939

• Języki publikacji: EN

Abstrakty

EN

Ground reaction measurement in landing gear laboratory tests is used in order to gain knowledge about loads transferred to the aircraft structure. Ground reaction level is defined during aircraft design phase and it is required not to exceed limit value in real construction. Load from landing affect directly strength of aircraft structure especially mounting points what translates both strength of aircraft structure especially mounting points what translates both on safety and weight of the final design. Meeting the safety requirements is crucial in aviation regulations conformity. Landing gear ground reactions evaluation is performed during laboratory tests in order to meet the compliance with the ground load requirements assumed in design phase. Proper test method is crucial to prove the actual load. One of the methods is landing gear dynamic drop test where landing forces are measured. Force measurement is made in several ways according to test stand construction and test object specifics. In this article, three methods are described due to author’s experience in landing gear tests. Proposed techniques cover two direct and one indirect force measurements. Direct approach is based on strain gauge measurement principle. One is a strain gauge plate fixed to the ground while the second one is based on strain gauges attached to landing gear mounting nodes. Indirect approach is based on the acceleration of the tested object, which by definition is correlated with the force applied to the structure. Obtained test results allow determining the kinetic energy absorbed by landing gear during drop test. In this article author also presented numerical integration of the time history data and compared them with simulation results in order to show equivalence of all three of the test methods and to prove correctness of the test initial conditions determination.

Słowa kluczowe

EN

laboratory-testing; landing gear; load measurement; direct measurement; indirect measurement

• 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: 2017
• Tom: Vol. 24, No. 2
• Strony: 225--230
• Opis fizyczny: Bibliogr. 7 poz., rys.

Twórcy

autor

Skorupka Z.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 657, fax: [phone]

Bibliografia

• [1] Currey, N. S., Aircraft Landing Gear Design Principles and Practices, Washington AIAA, 1988.
• [2] Kowalski, W., et al., State of the art in landing gear shock absorbers, Transactions of the Institute of Aviation, No 181, 2005.
• [3] Skorupka, Z., et al., Electrically Driven and Controlled Landing Gear for UAV up to 100 kg of Take Off Mass, European Council for Modelling and Simulation proceedings, Kuala Lumpur 2010.
• [4] Skorupka, Z., Paprzycki,I., Laboratoryjne badania podwozi lotniczych, Transport przemysłowy i maszyny robocze, Wrocław 2014.
• [5] Sobieszek, A., Paprzycki, I., Tywoniuk, A., Landing Gear Dynamic Tests with Strain Gages, Journal of KONES Powertrain and Transport, Vol. 22 No. 3, 2015.
• [6] Wiśniowski, W., Specjalizacje Instytutu Lotnictwa. Przegląd i wnioski, Prace Instytutu Lotnictwa, 2014.
• [7] Normal, Utility, Aerobatic and Commuter Aeroplanes, CS-23, European Aviation Safety Agency (EASA).

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).