The effect of the repair sleeve installation method on the stress-strain state of aircraft airframe parts

Аuthors

Ryzhkov M. Y.^{1, 2*}, Pykhalov A. ^{3, 2**}, Zenkov E. V.^{2, 3***}

1. PJSC Yakovlev , 68, Leningradskiy prospect, Moscow, 125315, Russia
2. Irkutsk National Research Technical University, 83, Lermontov str., Irkutsk, 664074, Russia
3. Irkutsk State Transport University (IrGUPS), 15, Chernyshevsky str., Irkutsk, 664074, Russia

*e-mail: mixa1997ruz@mail.ru
**e-mail: pykhalov_aa@mail.ru
***e-mail: jovanny1@yandex.ru

Abstract

In case of accidental damage to the skin and other parts of the airframe in the area of the mounting points, they must be repaired to restore structural strength. In this case, one of the most effective repair methods is the use of a special repair sleeve. To date, there is no data in domestic practice on the effect of the presented repair method on the fatigue and static strength of the structure. The paper presents the results of a comparison of experimental research and numerical modeling on the installation of repair bushings for aluminum alloy parts. The full-scale experiment was carried out using the Vic-3D deformation measurement system, which uses the digital image correlation technique. Numerical modeling was carried out using the finite element method by solving the problem of fitting a sleeve into a sample, taking into account physical, geometric and contact nonlinearities. Various types of deformations of the sample – a plate with a hole – were determined when the sleeve was inserted into it in various ways: cooling the sleeve in liquid nitrogen and pressing it. Based on a full-scale experiment and finite element modeling, it is shown that with different methods of installing bushings, such as pressing and installation after cooling in liquid nitrogen, a different local stress-strain state occurs in the area of the hole. When installed by cooling in nitrogen, the stress-strain state is biaxial, whereas when installed by pressing, it is triaxial. Based on this, it can be assumed that with a different initial stress-strain state in the structure, there will be a different effect of the repair sleeve on fatigue strength.

Keywords:

mechanics of a rigid deformed body, contact problem, bush, VIC3D system, stress concentration coefficient

References

1. Zou Jiansheng, Zhu Jie. Influence of repairing technique by bushing on fatigue performance of metal structure for civil aircraft. Civil Aircraft Design & Research. 2018. No. 1. P. 67-70.
2. Ryzhkov M.YU., Pykhalov A.A., Yakhnenko M.S. Mathematical Modeling of Preloaded Joints Taking into Account Their Mutual Influence on the Durability of a Prefabricated Structure. Vestnik Permskogo natsional'nogo issledovatel'skogo politekhnicheskogo universiteta. Aerokosmicheskaya tekhnika. 2023. No. 74. P. 5–19. (In Russ.). DOI: 10.15593/2224- 9982/2023.74
3. Chen Changrong, Huang Weiyang. Interference fit of bushing and hole by using cold extrusion. Aeronautical Manufacturing Technology. 1997. No. 1. P. 43-44.
4. Hampoux R.L., Landy M.A. Fatigue Life Enhancement and High Interference Bushing Installation Using the Force Mate Bushing Installation Technique. ASTM STP 927-M. 1986. P. 39-52.
5. Feigenbaum Yu.M., Dubinskii S.V. Influence of Random Operational Damage on the Strength and Resource of Aircraft Structures. Nauchnyi vestnik Moskovskogo gosudarstvennogo tekhnicheskogo universiteta grazhdanskoi aviatsii. 2013. No. 187. P. 83–91. (In Russ.)
6. Nikhamkin M.A., Voronov L.V., Konev I.P. Influence of operational damage and volumetric residual stresses on fatigue strength and resistance to the development of cracks in the compressor blades. Vestnik dvigatelestroeniya. 2006. No. 3. P. 93-97. (In Russ.)
7. Nikhamkin M.SH., Limonova V.M., Khamidullina A.K. Assessment of the decrease in the fatigue strength of the compressor blades when damaged by foreign objects Sovremennye problemy nauki i obrazovaniya. 2013. No. 5. P. 83–91. (In Russ.)
8. Jun Chen, Yuguang Ma. et al. Quasistatic Tensile and Fatigue Performances of Titanium Alloy Open Hole Structures Strengthened by Different Cold Expansion Mandrel Front Cone Angles. Fatigue & Fracture of Engineering Materials & Structures. 2025. Vol 4, No. 4. P. 1574-1588.
9. Bruno Pedrosa, Behzad V. Farahani, Carlos Rebelo, José A.F.O. Correia Fatigue Mechanisms and Crack Strain Field Measurements on Bolt Hole Detail. Fatigue & Fracture of Engineering Materials & Structures. 2025. Vol. 233. URL: https://doi.org/10.1016/j.jcsr.2025.109664
10. Borisov I.V. Osnovy teorii povrezhdaemosti i vosstanovleniya aviatsionnykh konstruktsii (Fundamentals of the Theory of Damages and Restoration of Aircraft Structures). Taganrog: Izd-vo TRTU Publ., 2006. 65 p.
11. Siwei Tao and Jiansheng Zou. Experimental study on fatigue performance of bushing repair with different fasteners. Journal of Physics Conference Series. 2021. Vol. 1885, P. 032037. DOI: 10.1088/1742-6596/1885/3/032037
12. Tret'yakova T.V., Tret'yakov M.P., Vil'deman V.E. Assessment of measurement accuracy using a video system for analyzing displacement and strain fields. Vestnik Permskogo gosudarstvennogo tekhnicheskogo universiteta. Mekhanika. 2011. No. 2. P. 92-100. (In Russ.)
13. Feodos'ev V.I. Soprotivlenie materialov (Resistance of Materials). Moscow: Izd-vo MGTU im. N.E. Baumana Publ., 1999. 592 p.
14. Ma Lifeng, et al. Formulation for Axisymmetric Non-Slipping Contacts between Dissimilar Elastic Solids. Proceedings of The Royal Society A: Mathematical, Physical and Engineering Sciences. 2025. Vol. 481, No. 2305. URL: https://doi.org/10.1098/rspa.2024.0459
15. Kogaev V.P. Raschety na prochnost' pri napryazheniyakh, peremennykh vo vremeni (Strength calculations under time-varying stresses). Moscow: Mashinostroenie Publ., 1977. 232 p.
16. Zaretskii M.V., Sidorenko A.S. Estimation of longevity index for flying vehicles structures under random loadings. Trudy MAI. 2013. No. 70. (In Russ.). URL: https://trudymai.ru/eng/published.php?ID=44479
17. Polonik E.N., Surenskii E.A., Fedotov A.A. Automation of aircraft components with geometrical stress concentrators fatigue endurance calculations. Trudy MAI. 2016. No. 86. (In Russ.). URL: https://trudymai.ru/eng/published.php?ID=67799
18. Yashutin A.G., Surenskii E.A. Software application for force distribution and detailed strength analysis. Trudy MAI. 2014. No. 74. (In Russ.). URL: https://trudymai.ru/eng/published.php?ID=49151
19. Sklyarov N.M. Aviatsionnye splavy. T. 1. Konstruktsionnye stali (Aviation Alloys. Vol. 1. Structural Steels). Moscow: ONTI Publ., 1975. 429 p.
20. Kishkin S.I. Aviatsionnye splavy. T. 4. Alyuminievye i berillievye splavy (Aviation Alloys. Vol. 4. Aluminum and Beryllium Alloys). Moscow: ONTI Publ., 1982. 626 p.

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