Prototype test stand for testing insolated rotor systems

• Autorzy: Wojtas Małgorzata , Czajkowski Łukasz

Identyfikatory

DOI

10.2478/kones-2019-0081

• Języki publikacji: EN

Abstrakty

EN

The article discusses assumptions for a prototype test stand designed for testing rotors in the conditions of work at their nominal speed, in particular gyrocopter and helicopter rotors. In the work presents an overview of similar solutions of test stand presented in the available literature and solutions proposed by companies, such as Swangate International or Luftfahrttechnik GmbH. Beyond these solutions the article also contains test stand used so far at the Institute of Aviation, these solutions were prepared for testing one type of rotor (for example: only for gyroplane rotors). The article provides the steps of designing a new test stand, which one of the basic assumptions is that it will be a universal test stand, giving the possibility to test different types of rotors. The article discusses two concepts of the stand with electric engine as a drive, gives the advantages and disadvantages of each concept, and indicates the selected solution. In addition to design and applied drive solution of the stand, the measuring part and data acquisition were also discussed. Moreover, the article focus on the advantages of rotor testing using the presented solution, as well as problems encountered during tests, in particular related to construction free vibrations and resonance. Vibration and resonance of the test stand are very important aspect of the entire design process, because it affects the quality and safety of the tests.

Słowa kluczowe

EN

test stand; main rotor; design; construction resonance

• 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: 2019
• Tom: Vol. 26, No. 3
• Strony: 257--264
• Opis fizyczny: Bibliogr. 10 poz., rys.

Twórcy

autor

Wojtas Małgorzata

• Łukasiewicz Research Network – Institute of Aviation Centre of Transportation and Energy Conversion Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 224

autor

Czajkowski Łukasz

• Łukasiewicz Research Network – Institute of Aviation Centre of Transportation and Energy Conversion Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 224

Bibliografia

• [1] Kim, D.-K., et al., An operational test and dynamic balancing sensitive study of the rotor blade on the whirl tower, Vol. 1, pp. 412-421, 38th European Rotorcraft Forum, Amsterdam 2012.
• [2] Ergul, B. P., Yasa, O. A., Tursun, G., Determination of structural integrity of teetering rotor system by whirl tower tests, 39th European Rotorcraft Forum, Moscow 2013.
• [3] Ezertas, A., Yucekayali, A., Ortakaya, Y., Hover performance assessment of 3 meter radius rotor on whirl tower, 39th European Rotorcraft Forum, Moscow 2013.
• [4] Feszty, D., Nietzsche, F., Review of Active Rotor Control Research in Canada, International Journal of Aeronautical and Space Science, Vol. 12 (2), pp. 93-114, 2011. 263
• [5] Sobieszek, A., Wojtas, M., Composite rotor blades tests essential before mounting on gyroplane, Journal of KONES Powertrain and Transport, Vol. 23, No. 4, pp. 487-494, 2016.
• [6] Szczepanik, T., Analysis of the state of the gyroplane world market, Transactions of the Institute of Aviation, No. 3 (244), pp. 227-238, Warsaw 2016.
• [7] Żurawski, R., Bezpieczne wykonywanie prób prototypów obiektów wirujących, Bezpieczeństwo na lądzie, morzu i w powietrzu w XXI wieku, CNBOP-PIB, Józefów 2014.
• [8] https://www.rotorblades.com.
• [9] http://swangate.com.
• [10] https://www.zf.com.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).