scholarly journals Prediction of Progressive Failure Behaviour of Composite Skewed Hypar Shells Using Finite Element Method

2014 ◽  
Vol 2014 ◽  
pp. 1-8 ◽  
Author(s):  
Arghya Ghosh ◽  
Dipankar Chakravorty
Keyword(s):  
Finite Element ◽  
Shear Failure ◽  
Progressive Failure ◽  
Laminated Composite ◽  
Practical Significance ◽  
Plane Stress Condition ◽  
Failure Behaviour ◽  
Failure Loads ◽  
Element Approach ◽  
Failure Theories

Progressive failure behaviour of laminated composite skewed hypar shells is investigated in this paper through finite element approach. For composite materials which are weak in transverse shear, failure may initiate at any inner lamina or interface and may remain undetected and unattended to. Such latent damages may progress gradually and lead to a sudden total ply failure. An iterative method is adopted using the various failure theories to predict the first ply failure load. After the first ply failure, the stiffness of the failed element is totally discarded from the laminate and the remaining laminate is considered for further analysis. The developed finite element code is validated through solution of a benchmark problem. Numerical experiments are carried out to obtain the first ply and progressive failure of simply supported hypar shells under transverse distributed load. While obtaining the failure loads, the shell is considered to be under plane stress condition and in linear elastic range. Results are studied meticulously to extract a set of conclusions of practical significance regarding the failure characteristics of composite hypar shells.

Progressive Failure Analysis of Unidirectional-Fabric Laminated Composite Joints under Pin-Loading

2007 ◽  
Vol 334-335 ◽  
pp. 1-4
Author(s):  
Jin Hwe Kweon ◽  
Hee Jin Son ◽  
Ji Young Choi ◽  
So Young Shin ◽  
Jin Ho Choi ◽  
...  
Keyword(s):  
Finite Element ◽  
Failure Analysis ◽  
Progressive Failure ◽  
Laminated Composite ◽  
Shell Element ◽  
Failure Criteria ◽  
Composite Joints ◽  
Element Analysis ◽  
Progressive Failure Analysis ◽  
Failure Loads

A two-dimensional progressive failure analysis is conducted to predict the failure loads and modes of carbon-epoxy composite joints under pin-loading. An eight-node laminated shell element is used for the finite element modeling. Post-failure stiffness is evaluated based on the complete unloading model combined with various failure criteria. The comparison of finite element and experimental results shows that the finite element analysis based on the combined maximum stress and Yamada-Sun criteria most accurately predicts the failure loads of the composite laminated joints.

Design and Analysis of an Aircraft Composite Hinge Bracket Using Finite Element Approach

2014 ◽  
Vol 629 ◽  
pp. 158-163
Author(s):  
Wai Chee Mun ◽  
Ahmad Rivai ◽  
Omar Bapokutty
Keyword(s):  
Finite Element ◽  
Composite Structures ◽  
Laminated Composite ◽  
Composite Plates ◽  
Metallic Structures ◽  
Aircraft Structures ◽  
Finite Element Approach ◽  
Heterogeneous Nature ◽  
Element Approach ◽  
Margin Of Safety

The use of composite materials in aircraft structures have been increasing for the past decade. The anisotropic and heterogeneous nature of composites remains a major challenge to the design and analysis of composite aircraft structures. Composite structures require a different design approach compared to the design of metallic structures. This paper aims to provide a step by step definitive guide to design and analyze composite structures using finite element approach. A simplified design model for the composite structural design was used to analyze an aircraft composite hinge bracket. The composite hinge bracket which is made of IM7/8552 laminated composite plates was successfully designed with a margin of safety of 0.216 and a weight savings of 43.77 percent was estimated.

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