Composite rotor blades tests essential before mounting on gyroplane

• Autorzy: Sobieszek A. , Wojtas M.

Identyfikatory

DOI

10.5604/12314005.1217289

• Języki publikacji: EN

Abstrakty

EN

The article presents the course of the composite rotor blades tests. Object of study was designed in Institute of Aviation, new airfoil for gyroplane rotors and technology of manufacturing carbon rotor blades were made. When the test program was developed, we focused for special test to check not only typical rotor blades properties but also composite structures thereby technology of manufacturing. One of the basic rotor blades test is to determine the breaking force, which, taking into account the safety factor, cannot exceed the maximum centrifugal force occurring on the rotor blades during flight. The first step of rotor blades tests was static test, which gave us answer about stiffness in plane of low stiffness and torsional stiffness, it’s very important properties related to vibrations. Another mechanical properties measured during tests were centre of gravity and mass moment of inertia in rotor blade. Next step was dynamic test – tracking and balancing verification. After static and dynamics, which has proper results – good balance and no vibration on the entire range of rotational speed – rotor blades can be use on fly object. After getting proper results of static and dynamic test next step was a specially prepared test, which defined the time needed for delamination to take place. During the delamination tests, the rotor blade was subjected to adequate loads that occur in horizontal flight. That kind of test is basis to determine service life of rotor blades.

Słowa kluczowe

EN

gyroplane; strength test; blades properties; composites

• 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: 487--494
• Opis fizyczny: Bibliogr. 9 poz., rys.

Twórcy

autor

Sobieszek A.

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

autor

Wojtas M.

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

Bibliografia

• [1] Cheol-Yong, Y., et al., Dynamic characteristics of helicopter bearingless main rotor, Journal of The Korean Society Aeronautical and Space Sciences, Vol. 44, No. 5, pp. 439-446, 2016.
• [2] Delega, M., Krzymień, W., Weryfikacja rozwiązań prerotacji wirnika wiatrakowca, Transactions of the Institute of Aviation, No. 3 (236), pp. 35-40, Warsaw 2014.
• [3] Duda, H., Pruter, I., Flight performance of lightweight gyroplanes, 28th International Congress of the Aeronautical Sciences, Brisbane, Australia 2012.
• [4] Eugene, E. Niemi, Jr., Raghu Gowda B.V., Gyroplane rotor aerodynamics revisited – blade flapping and RPM variation in zero-g flight, 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida 2011.
• [5] Stalewski, W., Aerodynamic design of modern gyroplane main rotors, Transactions of the Institute of Aviation, No. 1 (242), pp. 80-93, Warsaw 2016.
• [6] Stalewski, W., Dziubiński, A., Projektowanie aerodynamiczne wirnika autorotacyjnego, XI Międzyuczelniane Inżynierskie Warsztaty Lotnicze, Bezmiechowa 2014.
• [7] Szczepanik, T., Łusiak, T., Eksploatacja wiatrakowców jako statków powietrznych, Transactions of the Institute of Aviation, No. 4 (241), pp. 87-95, Warsaw 2015.
• [8] Żurawski, R., Bezpieczne wykonywanie prób prototypów obiektów wirujących, Bezpieczeństwo na lądzie, morzu i w powietrzu w XXI wieku, CNBOP-PIB, Józefów 2014.
• [9] www.wirnikautorotacyjny.pl. 494

Uwagi

PL

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