Open AccessParametric investigations of strength of a composite panel after impact damage
Author(s) -
Mikhail Levchenkov
Publication year - 2021
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1925/1/012059
Subject(s) - parametric statistics , structural engineering , composite number , buckling , residual strength , stiffness , finite element method , residual , sandwich structured composite , materials science , engineering , composite material , computer science , mathematics , statistics , algorithm
Results of parametrical investigations of residual strength and buckling of damaged composite panels of civil aircrafts were considered. The investigations were performed on the base of the semi-empirical method developed by the author. The algorithm allows users to carry out the analysis of parameters of stress-strain state and to assess a general buckling behavior of composite panels in the automatic mode. The calculations were performed by using the special parametrical finite element models of composite panels that are typical for current civil aircrafts. The special models of panels consisted of composite laminated skin and different types of stiffeners have zones with reduced stiffness characteristics. The relationship between level of reducing mechanical characteristics of “damaged” zones and residual strength and buckling margins of the panels was determined.