New approach for an inspections program and use of C-factor model for stress analysis of composite component structure

• Autorzy: Nechval Konstantin , Chatys Rafał , Petukhov Igor , Bain Alexander

Identyfikatory

DOI

10.62753/ctp.2024.07.3.3

• Języki publikacji: EN

Abstrakty

EN

A complete airplane structure is manufactured from many parts. These parts are made from sheets, extruded sections, forgings, castings, tubes, or machined shapes, which must be joined together to form subassemblies. The subassemblies must then be joined together to form larger assemblies and then finally assembled into a completed airplane. Many parts of the completed airplane must be arranged so that they can be disassembled for shipping, inspection, repair or replacement and are usually joined by bolts or rivets. In order to facilitate the assembly and disassembly of the airplane, it is desirable for such bolted or riveted connections to contain as few fasteners as possible (which is guaranteed by composite structures). Nevertheless, the impact of birds or elements during the take-off or landing (the operation) of an aircraft sometimes generates a critical dispersion of impact energy in the composite structure due to the high heterogeneity (of resin or microbubbles) of the structure. For example, a metal wing usually resists bending stresses in numerous stringers and sheet elements distributed around the periphery of the wing cross sections. The wing cannot be made as one continuous riveted assembly. The new approach to design an inspection scope and schedule based on maintenance checks brings elements of novelty. Although the maintenance schedule can be obtained through simulation, the simulation results might not be accurate enough. The obtained results provide usable analytical solutions. However, without an additional wide data-collection program, the results can serve only advisory purpose for practicians.

Słowa kluczowe

EN

aircraft riveted joints stress analysis; C-factor reliability

PL

Analiza naprężeń połączeń nitowych statków powietrznych; niezawodność współczynnika C

• Wydawca: Polskie Towarzystwo Materiałów Kompozytowych
• Czasopismo: Composites Theory and Practice
• Rocznik: 2024
• Tom: R. 24, nr 3
• Strony: 205--212
• Opis fizyczny: Bibliogr. 15 poz., rys., tab.

Twórcy

autor

Nechval Konstantin

• Riga Aeronautical Institute, 9 Mežkalna, Riga LV-1058, Latvia

autor

Chatys Rafał

• Kielce University of Technology, Faculty of Mechatronics and Mechanical Engineering, al. 1000-lecia Państwa Polskiego 7, 25-314, Kielce, Poland

autor

Petukhov Igor

• Riga Aeronautical Institute, 9 Mežkalna, Riga LV-1058, Latvia

autor

Bain Alexander

• Riga Aeronautical Institute, 9 Mežkalna, Riga LV-1058, Latvia

Bibliografia

• 1. Christensen R.M., The failure theory for isotropic materials: Proof and completion, Journal of Applied Mechanics 2020, 87(5), 051001.
• 2. Cunha A. Jr, Yanik Y., Olivieri C., da Silva S., Tresca vs. von Mises: Which failure criterion is more conservative in a probabilistic context? Journal of Applied Mechanics 2023, in press. hal-04245274 (https://hal.science/hal-04245274).
• 3. Ding B., Li X., An eccentric ellipse failure criterion for amorphous materials, Journal of Applied Mechanics 2017, 84(8), 081005.
• 4. Pavelko V.P., Pavelko I.W., Chatys R., Strength of fibrous composites with impact damage, VI Conf. Polymer Composites, 24-26.11.2007, Wisła (Poland), Prace Naukowe Politechniki Warszawskiej, Mechanika 2007, 219, 187-198.
• 5. Man N.R., Saunders S.C., On evaluation of warranty assurance when life has a Weibull distribution, Biometrika 1969, 56, 615-625.
• 6. Urbahs A., Banovs M., Turko V., Feshchuk Y., New approach to use the acoustic emission monitoring for the defects
• detection of composit-material’s design elements, Water Transport and Infrastructur: 14. Inter. Konference, Latvia, Riga 2012, April, 26-27, 45-50.
• 7. Banov M.D., Pogorodny P.G., Shestakov V., Chatys R., Quantum approach in the measurement and analysis of acoustic emission signals, AIP Conference Proceedings, Scientific Session on Applied Mechanics X, Bydgoszcz 2019, 22-30, DOI: 10.1063/1.5091867.
• 8. Mann N.R., Warranty periods based on three ordered sample observations from a Weibull population, IEEE Transactions on Reliability 1970, R-19, 167-171.
• 9. Antle C.E., Rademaker F., An upper confidence limit on the maximum of m future observations from a Type 1 extremevalue distribution, Biometrika 1972, 59, 475-477.
• 10. Fisher R.A., Two new properties of mathematical likelihood, Proceedings of the Royal Society A 1934, 144, 285-307.
• 11. Cox D.R., Some problems connected with statistical inference, The Annals of Mathematical Statistics 1958, 29,357-372.
• 12. Buehler R.J., Some validity criteria for statistical inferences, The Annals of Mathematical Statistics 1959, 30, 845-863.
• 13. Lawless J.F., Statistical Models and Methods for Lifetime Data, John Wiley, New York 1982.
• 14. Dąbek L., Kapjor A., Orman Ł.J., Ethyl alcohol boiling heat transfer on multilayer meshed surfaces, Proc. 20th Int. Scientific Conference on The Application of Experimental and Numerical Methods in Fluid Mechanics and Energy 2016, AIP Conference Proceedings 2016, 1745, 020005,DOI: 10.1063/1.4953699.
• 15. Nečvals K., Petuhovs I., Assigning warranty periods for fatigue sensitive components of aircraft structure, Proceedings of the 6th International Scientific and Practical Conference ransport, Education, Logistics and Engineering –2021, 13-27.