Experimental analysis of ultralight aircraft tyre behaviour under aircraft landing phase

    Andrzej Kubit   Affiliation
    ; Tomasz Trzepieciński   Affiliation
    ; Łukasz Święch   Affiliation
    ; Romuald Fejkiel Affiliation


The aim of the research described in this paper is analysis of the deformation of the aircraft tyre subjected to static load. Based on the results of experimental tests with a different value of inflation pressure, favorable pressure conditions for use in the tyre of an ultralight aircraft were determined. The deflection characteristics of the tyre depending on the nominal pressure was determined using the digital image correlation technique. In the range of loads not leading to excessive tyre deflection, quite linear relation between vertical deflection and vertical force is observed. The safe minimum pressure in tyre loaded with a force of 12 kN is 2.5 bar. The experimental results will be used to select a shock absorber for a 600 kg ultralight, light sport aircraft commercialised by the company Ekolot (Krosno, Poland).

Keyword : digital image correlation, landing impact, light sport aircraft, tyre, tyre deflection, touchdown

How to Cite
Kubit, A., Trzepieciński, T., Święch, Łukasz, & Fejkiel, R. (2022). Experimental analysis of ultralight aircraft tyre behaviour under aircraft landing phase. Aviation, 26(2), 124–129.
Published in Issue
Jun 23, 2022
Abstract Views
PDF Downloads
Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.


Alroqi, A. A., & Wang, W. (2015). Comparison of aircraft tire wear with initial wheel rotational speed. International Journal of Aviation, Aeronautics, and Aerospace, 2(1), 1–28.

Arif, N., Rosu, I., Lebon, F., & Elias-Birembaux, H. (2018). On the modeling of light aircraft landing gears. Journal of Aeronautics and Aerospace Engineering, 23(3), 1–9.

Batterbee, D. C., Sims, N. D., Stanway, R., & Wolejsza, Z. (2007a). Magnetorheological landing gear. Part 1: A design methodology. Smart Materials and Structures, 16(6), 2429–2440.

Batterbee, D. C., Sims, N. D., Stanway, R., & Rennison, M. (2007b). Magnetorheological landing gear. Part 2: Validation using experimental data. Smart Materials and Structures, 16(6), 2441–2452.

Biot, M. A., & Bisplinghoff, R. L. (1944). Dynamic loads on airplane structures during landing. In NACA Wartime Report, W-92. National Advisory Committee for Aeronautics.

Chester, D. H. (2000). A parametric study of aircraft landing-impact, with emphasis on nose gear landing conditions (pp. 1–14). In ICAS Congress.

Conway, H. G. (1958). Landing gear design. Chapman & Hall.

Currey, N. S. (1988). Aircraft landing gear design: Principles and practices. American Institute of Aeronautics and Astronautics.

Daughetee, C. C. (1974, 17–19 April). Drop testing naval aircraft and the VSD landing gear dynamic test facility. In 15th ASME Structures, Structural Dynamics and Materials Conference, AIAA Paper (pp. 758–764). Las Vegas.

Dubey, A., Undavalli, V. K., Gupta, S. S., & Bodramoni, B. (2015). Landing gear of an aircraft structure: A review. International Journal of Engineering Research & Technology, 4(12), 20–25.

Essienubong, I. A., Ikechukwu, O., & Paul, S. (2018). Finite element analysis of aircraft tire behaviour under overloaded aircraft landing phase. Reproductive System and Sexual Disorder International Journal, 2(1), 32–37.

Flugge, W. (1952). Landing gear impact (Technical note). In NACA TN 2743. Defence Technical Information Center.

Franz, M. (1937). Theoretical and experimental principles of landing gear research and development. Luftfahrtforschung, 14(8), 387–419.

Ghiringhelli, G. L. (2000). Testing of semiactive landing gear control for a general aviation aircraft. Journal of Aircraft, 37(4), 606–616.

Hać, M., & From, K. (2008). Design of retraction mechanism of aircraft landing gear. Mechanics and Mechanical Engineering, 12(4), 357–373.

Lee, D. Y., Nam Y. J., Yamane, R., & Park, M. K. (2009). Performance evaluation on vibration control of MR landing gear. Journal of Physics: Conference Series, 149, 012068.

Luong, Q. V., Jang D. S., & Hwang, J. H. (2020). Robust adaptive control for an aircraft landing gear equipped with a magnetorheological damper. Applied Sciences, 10(4), 1459.

Milwitzky, B., & Cook, F. E. (1953). Analysis of landing-gear behavior. In NACA, TN1154. NASA Technical Reports Server.

Sivakumar, S., & Haran, A. P. (2015). Mathematical model and vibration analysis of aircraft with active landing gears. Journal of Vibra Control, 21(2), 229–245.

Temple, G. (1945). Prediction of undercarriage reactions. In R & M No. 1927, 1944, RAE Report, S.M.E. 3298. Aeronautical Research Committee Reports and Memoranda.

Wu, D.-S., Gu, H.-B., & Liu, H. (2007). GA-based model predictive control of semi-active landing gear. Chinese Journal of Aeronautics, 20(1), 47–54.

Yazici, H., & Sever, M. (2018). Active control of a non-linear landing gear system having oleo pneumatic shock absorber using robust linear quadratic regulator approach. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 232(13), 2397–2411.