Gyroplane rotors vibration tests

• Autorzy: Wojtas M. , Trendak M.

Identyfikatory

DOI

10.5604/01.3001.0010.3222

• Języki publikacji: EN

Abstrakty

EN

The article presents vibration test of three different types of gyroplane main rotors. The test was carried out on a specially prepared test bench using a Red Led Tacho Sensor measuring system. Tests were conducted for the project „Research and development works on innovative construction of aircrafts of weight over 560 kilograms at the company Trendak Aviation”. The work outlines the basic properties of the gyroplane vibration and gives their sources. The research focused on the gyroplane main rotor vibration related inter alia to the rotor imbalance as well as rotor hub connector construction. Tested rotors consisted of three different types of gyroplane rotor blades and innovative universal hub connector with positive coning angle of 2.8º. The article summarized the basic properties of three types of gyroplane the rotor blade, marks advantages of use hub connector witch constructional dihedral angle. Discusses the principle of operation of measuring device, tests methodology starting from instrument calibration. The results of the measurements are shown in the graphs in polar coordinates. The vibration measurement is carried out in two axes, in x-axis, longitudinal, along the rotor radius and in y-axis, perpendicular to the x-axis, in the direction of the chord of the rotor blades.

Słowa kluczowe

EN

rotor vibration; rotor blades; teetering rotor; hub connector; rotor imbalance

• 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. 4
• Strony: 349--354
• Opis fizyczny: Bibliogr. 12 poz., rys.

Twórcy

autor

Wojtas M.

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

autor

Trendak M.

• AVIATION Artur Trendak Nowowiejskiego Street 26A, 96-313 Jaktorów Kolonia, Poland tel.: [phone]

Bibliografia

• [1]Bramwell, A. R. S., Done, G., Balmford, D., Bramwell’s Helicopter Dynamics, Butterworth-Heinemann, 2001.
• [2]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.
• [3]Cieślak, S., Instability of the gyroplane teetering rotor in axial flow, Transactions of theInstitute of Aviation, No. 2 (235), pp. 28-37, Warsaw 2014.
• [4]Kania, M., Modeling of helicopter blades flapping in CATIA V5, Postępy nauki i techniki,No.7, p. 94-101, 2011.
• [5]Krzymień, W., Vibration properties of the gyrocopter, Transactions of the Institute ofAviation, No. 219, pp. 234-239, Warsaw 2011.
• [6]Red LED Tacho Sensor User Manual, Smart Avionics Ltd., 2013.
• [7]Sobieszek, A., Wojtas, M., Composite rotor blades tests essential before mounting ongyroplane, Journal of KONES Powertrain and Transport, Vol. 23, No. 4, pp. 487-494, 2016.
• [8]Stalewski, W., Aerodynamic design of modern gyroplane main rotors, Transactions of theInstitute of Aviation, No. 1 (242), pp. 80-93, Warsaw 2016.
• [9]Trendak, A., Łącznik wirnika wiatrakowca, RP Patent PL409109, 2014.
• [10]Vainilavičius, D., Vygantas, A., Marius, M., Analysis of autogyro rotor balancing andvibration, IEEE Metrology for Aerospace Conference, Conference paper, pp. 416-420, 2015.
• [11]Wiśniowski, W., Identification of main helicopters resonances by ground vibration test,Journal of KONES Powertrain and Transport, Vol. 22, No. 2, pp. 287-291, 2015.
• [12]www.wirnikautorotacyjny.pl.

Uwagi

PL

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