Powiadomienia systemowe
- Sesja wygasła!
Identyfikatory
Warianty tytułu
Języki publikacji
Abstrakty
The paper proposes a method of calculating the maximum displacement in the aircraft metal structure repaired by CPBR (bonded composite patch repair). The calculations were made based on specimens. The specimens were prepared according to the current requirements used in aviation. The 2024-T3 alloy metal sheet was a structure. To repair the structure used the boron-epoxy composite patch in prepreg technology was used. The metal structure was modeled as an isotropic elastic body. The metal structure coated with the composite patch was modeled as an orthotropic structure. Based on this, the stress was determined in the metal structure. The size opening displacement in the metal structure was determined based on the model of linear elastic fracture mechanics for the plane stress state. The calculation results were verified by measuring the displacement in laboratory conditions. The laboratory tests made it possible to demonstrate the accuracy of the proposed approach.
Słowa kluczowe
Czasopismo
Rocznik
Tom
Strony
104--110
Opis fizyczny
Bibliogr. 2 poz., fot., rys., wykr., wzory
Twórcy
autor
- Air Force Institute of Technology, Ksiecia Boleslawa 6 street, 01-494 Warsaw, Poland
autor
- Military University of Technology, Faculty of Mechanical Engineering
autor
- Air Force Institute of Technology, Ksiecia Boleslawa 6 street, 01-494 Warsaw, Poland
Bibliografia
- [1] J. German, (2001). Podstawy mechaniki kompozytów włóknistych, Politechnika Krakowska, Kraków.
- [2] T. L. Anderson, (1995). Fracture Mechanics: Fundamentals and Applications. CRC Press.
Uwagi
Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę (zadania 2017).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-e6a7a9e7-12e2-4794-b838-d7cc6c537985