Dynamic Testing and Fatigue Analysis of the I-31P Nose Landing Gear

• Autorzy: Skorupka Zbigniew

Identyfikatory

DOI

10.2478/fas-2023-0008

• Języki publikacji: EN

Abstrakty

EN

The landing gear is a critical safety component of any aircraft, playing a key role in managing the significant loads experienced during landing and ground maneuvers. In the case of the I-31P aircraft, a redesign of the I-23 landing gear system, required comprehensive testing to validate its performance, after change of landing gear parts manufacturer and minor updates to materials and technologies. This study focuses on the dynamic testing of the I-31P nose landing gear (NLG), particularly to assess its energy dissipation and fatigue resistance under operational conditions. Dynamic tests, performed in accordance with CS-23 standards, utilized strain gauges to monitor potential stress concentrations, especially on the half-fork design. Results demonstrated that the I-31P nose landing gear meets the required safety standards, with key performance metrics such as deflection and load factors within acceptable limits. The findings also highlighted the importance of continued monitoring for potential fatigue issues, offering valuable insights for future design enhancements.

Słowa kluczowe

EN

I-31P; nose landing gear; NLG; laboratory tests; dynamic testing

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2023
• Tom: Iss.15
• Strony: 133--145
• Opis fizyczny: Bibliogr. 13 poz., fot., rys., tab., wykr.

Twórcy

autor

Skorupka Zbigniew

• Łukasiewicz Research Network - Institute of Aviation (L-Ilot), Structures Testing Laboratory, Al. Krakowska 110/114 Str., 02-256 Warsaw, Poland

• https://orcid.org/0000-0001-8021-5244

Bibliografia

• Currey, N. S. (1988). Aircraft landing gear design: Principles and practices. American Institute of Aeronautics and Astronautics.
• Dziendzikowski, M., Kurnyta, A., Reymer, P., Kurdelski, M., Klysz, S., Leski, A., & Dragan, K. (2021). Application of operational load monitoring system for fatigue estimation of main landing gear attachment frame of an aircraft. Materials, 14(21), 6564. https://doi.org/10.3390/ma14216564
• European Aviation Safety Agency (EASA). (n/a). Normal, Utility, Aerobatic and Commuter Aeroplanes (CS-23). http://easa.europa.eu
• Kurdelski, M., & Leski, A. (2011). Crack growth analysis of the landing gear pull rod of the fighter jet aircraft. Fatigue of Aircraft Structures, 2011(3). https://doi.org/10.2478/v10164-010-0039-1
• Leski, A., Reymer, P., & Kurdelski, M. (2011). Development of load spectrum for full scale fatigue test of a trainer aircraft. In J. Komorowski (Ed.), ICAF 2011 Structural Integrity: Influence of Efficiency and Green Imperatives. Springer. https://doi.org/10.1007/978-94-007-1664-3_46
• Reymer, P., Leski, A., Zieliński, W., & Jankowski, K. (2014). The concept of a full scale fatigue test of a Su-22 fighter bomber. Fatigue of Aircraft Structures, 2014(6), 79-87. https://doi.org/10.1515/fas-2014-0007
• Skorupka, Z. (2017). Laboratory investigations on landing gear ground reactions (load) measurement. Journal of KONES, 24(2), 225-230.
• Skorupka, Z., & Tywoniuk, A. (2019). Health monitoring in landing gears. Journal of KONES, 26(1), 167-174. https://doi.org/10.2478/kones-2019-0020
• Wołejsza, Z., Kowalski, W., Laffite, A., Mikulowski, G., & Remmers, L. (2005). State of the art in landing gear shock absorbers. Transactions of the Institute of Aviation, 181(2), 1-65.
• WT-800.42.00. Technical Conditions of Aircraft I-23: Front Landing Gear. Drawing No. 800.42.00.00.00.
• WT-800.42.10. Technical Conditions of Aircraft I-23: Front Landing Gear Shock Absorber. Drawing No. 800.42.10.00.
• 3900.042.100.000.00. Front Landing Gear.
• 14/ZB/BW-C6/00. Test Report: Front Landing Gear of Aircraft I-23. November 2000.