One of the major concerns for the structural failure of an airplane wing is due to the initiation of crack and its propagation. The literature survey on aircraft failure indicates that the main source of failure is due to fatigue cracks, which propagate from the wing root region. The modal analyses is one of the important tool used to determine the dynamics behaviour of airplane wing structure including natural frequencies and modes shapes. In the present study, an attempt has been made to perform the modal analyses of aircraft wing structure without cracked airplane wing structure and with cracked airplane wing structure (NACA2415). The results of modal analyses for uncracked wing structure are compared with the results reported in the literature. The main objective of the present study to do the comparative study of modal analyses for with or without crack in aircraft wing and analyses the results which show that natural frequency is affected in presence of crack. The effect of the crack length, depth of the crack and location of the crack on natural frequency is also investigated.
A Numerical Study to Investigate the Modal Analyses of Cracked Airplane Wing (NACA2415)
Lect.Notes Mechanical Engineering
2020-02-02
7 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Cracked airplane wing structure , Finite element analysis , Triangular crack Engineering , Engineering Thermodynamics, Heat and Mass Transfer , Automotive Engineering , Tribology, Corrosion and Coatings , Engineering Design , Engineering Fluid Dynamics , Computer-Aided Engineering (CAD, CAE) and Design