Strain gauge measuring plate for dynamic tests

• Autorzy: Sobieszek A. , Skorupka Z.

Identyfikatory

DOI

10.5604/01.3001.0012.4816

• Języki publikacji: EN

Abstrakty

EN

In dynamic tests, especially landing gears, it is necessary to measure and record load levels. In this article, authors present measurement methods used in the landing gear tests on the 10-Ton Drop Test Machine, which is capable of simulating conditions similar to real landing in landing energy dissipation tests. Possible test objects include dampers, shock absorbers, and crash structures and devices. In described case load measurement can be done by several methods where one of them is strain-gauge plate based load measurement. This type of measurement is weighting system under the test object where all forces acting on it are measured. Strain gauge plate is usually tailormade measurement system, which is composed out of mechanical device (plate itself) equipped with strain gauge force sensors, strain gauge amplification system and recording system. In addition, differences between static and dynamic measurements are described as well as influence of dynamic test conditions on strain gauges behaviour. In the article, authors describe general layout of the system, advantages and disadvantages of the test stand and problems that may appear during measuring. Authors also emphasize how the accuracy of the design affects to the quality of measurement. At the end of the article, advantages and disadvantages of the test stand and problems that may appear during measuring are described.

Słowa kluczowe

EN

dynamic tests; strain gauges; measuring plate; test stand

• 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: 2018
• Tom: Vol. 25, No. 4
• Strony: 399--404
• Opis fizyczny: Bibliogr. 10 poz., rys.

Twórcy

autor

Sobieszek A.

• Institute of Aviation Department of Transport and Energy Conversion Division Krakowska Ave. 110/114, 02-256 Warsaw, Poland tel.: [phone], ext. 224, 657

autor

Skorupka Z.

• Institute of Aviation Department of Transport and Energy Conversion Division Krakowska Ave. 110/114, 02-256 Warsaw, Poland tel.: [phone], ext. 224, 657

Bibliografia

• [1] Currey, N. S., Aircraft landing gear design principles and practices, Washington AIAA 1988.
• [2] Hurlock, L., Strain gauge measurement concepts, Tektornix, Oregano 1966.
• [3] Jebácek, I., Horák, M., Measuring of a nose landing gear load during take-off and landing, 21st International Conference Engineering Mechanics 2015, Paper #176, pp. 120-121, Czech Republic 2015.
• [4] Kowalski, W., et al.,: State of the art in landing gear shock absorbers, Transactions of the Institute of Aviation, No. 181, 2005.
• [5] 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.
• [6] Skorupka, Z., Paprzycki, I., Laboratoryjne badania podwozi lotniczych, Transport przemysłowy i maszyny robocze, Wroclaw 2014.
• [7] Skorupka, Z., Laboratory investigations on landing gear ground reactions (load) measurement, Journal of KONES Powertrain and Transport, Vol. 24, No. 2, 2017.
• [8] Sobieszek, A., Paprzycki, I., Tywoniuk, A., Landing gear dynamic tests with strain gauges, Journal of KONES Powertrain and Transport, Vol. 22, No. 3, 2015.
• [9] Tang, A. N., Zhou, Z. T., Cao, J. T., A technique of landing gear loads calibration with strain gauges, Proceedings ICAS 2010, pp. 2463-2468, France 2010.
• [10] Normal, utility, aerobatic and commuter aeroplanes, CS-23, European Aviation Safety Agency (EASA), 2012.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2018).