Damage tolerance evaluation of the wing spar with cracked web

• Autorzy: Augustin P.
• Konferencja: Proceedings of the Fourth Seminar on Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education/seminar(IV; 30.11-02.12.2000; Warszawa, Polska)
• Języki publikacji: EN

Abstrakty

EN

Damage tolerance evaluation is required for the aircraft life determination according to FAR Part 25 regulations. This concept is based on the crack propagation and residual strength determination. The damage tolerance evaluation of an aircraft structure, results in the inspection program ensuring that fatigue initiated cracks would involve no failure prior to the detection. The inspection program must be developed for each main structural element in the aircraft. Solutions to this problem usually found in the literature deal mainly with the components subject to tension; such as stiffened panels or lugs. This paper presents the testing program and FEM analysis focused on the wing spar with cracks in the web. It is characteristic of fatigue cracks in the web that they usually change their growth direction due to a complex stress state. The crack shape measured was used for constructing of a FEM model of the spar, the residual strength was calculated and compared with the experimental results.

Słowa kluczowe

EN

aircrafts; damage tolerance evaluation; experimental procedure

PL

samoloty; kwalifikacja uszkodzeń; procedury eksperymentalne

• Wydawca: Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology
• Czasopismo: Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics
• Rocznik: 2001
• Tom: nr 11
• Strony: 7--12
• Opis fizyczny: Bibliogr. 6 poz., rys., tab.

Twórcy

autor

Augustin P.

• Institute of Aerospace Engineering, Brno University of Technology, Czech Republic