Computational Investigation of the 3-D effects on Dynamic Fracture of Curved Composite Laminates

Date

2018-09-07

Author

Tamer Tahir, Ata
Çöker, Demirkan

Metadata

Show full item record

Item Usage Stats

196
views

0
downloads

Composite materials are used more and more in aerospace, commercial and industrial applications due to high specific stiffness, strength and damage tolerance capability. The main advantage of composite materials, it allows the stiffness and strength of the material to change with direction of loading. Hence tailoring structıres to meet load requirements reduces weight and allows designer to optimize structure. Considering all these advantages, primary and secondary structural elements of recent commercial aircrafts are made of laminated composite materials rather than aluminium alloys. In testing of L-shaped laminated composite parts [1,2], two dominant failure modes (delamination, matrix cracking) are observed which reduce the load carrying capacity of the component eventually leading to collapse of the part. In order to form an understanfing of failure types observed in recent experiments [3,4], computational simulations of the failure of L-shaped composite beams under combined moment/axial loading are carried out. The main aim of this study is to model the failure patterns according to ply sequence and to suggest reinforcement methods to increase durability of these structures. In this study, dynamic delamination under quasi- static loading is studied using implicit/explicit finite element method in conjunction with Cohesive Zone Modelling (CZM). Finite element models are generated using 3-D elements for the defined layup configuration and solutions are performed using Abaqus. The lay-ups are [0]30 and [03 /903 /03/903 /03]s The location of delamination initiation and propagation for these two different layup configurations are investigated numerically. Results verified that the location of delamination initiation is approximately half of the width. Since delamination initiates in half-width of the specimen and propagates to the edge, 2D simulations of delamination and experimental studies observe only edge delamination. Finally, the effect of cohesive element parameters on crack propagation front will be studied.

URI

https://hdl.handle.net/11511/80818

Conference Name

21th International Conference on Composite Structures

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Computational modeling of frontal polymerization Kaya, Koray; Göktepe, Serdar; Department of Civil Engineering (2022-2-09) Polymer-based composites are widely applied in high-tech areas such as aerospace, automotive, marine, and energy industries where high performance under extreme conditions is crucial. However, the traditional methods used to manufacture polymeric materials are energy-inefficient, time-consuming, complex, and costly processes. Frontal polymerization, an alternative curing method, is based on a self-propagating, self-sustained exothermic reaction front that transforms liquid monomers into cured polymers where...
MECHANICAL PROPERTIES OF REPAIRED CARBON FIBER REINFORCED POLYMER COMPOSITES Sonat, Emine Evren; Özerinç, Sezer; Department of Mechanical Engineering (2021-12-10) Carbon fiber reinforced polymer (CFRP) composites are increasingly used in the aerospace industry due to their high specific strength compared to conventional metallic materials. However, a significant shortcoming of these composites is their increased susceptibility to damage. Structural repair is a common method to restore the load-carrying capacity of a damaged part when the damage size exceeds the pre-defined tolerances. Scarf and stepped bonded repair methods are the primary choice for cases that requi...
Experimental investigation of failure mechanism in cross-ply and fabric curved composite laminates Çevik, Ahmet; Çöker, Demirkan; Department of Aerospace Engineering (2021-8) Laminated curved-shape composite parts which are used in the spar and ribs in aircraft and wind turbine blades are subjected to high interlaminar tensile and shear stresses. These stresses cause delamination and subsequent reduction in load-carrying capacity. In this study, failure mechanism of cross-ply and fabric curved composite laminates under pure transverse loading are examined experimentally using an in-house designed test fixture. Stress field over the curved beam is obtained with finite element ana...
Experimental investigation of CNT effect on curved beam strength and interlaminar fracture toughness of CFRP laminates Arca, M. A.; Çöker, Demirkan (2014-06-20) High mechanical properties and light weight structures of composite materials and advances in manufacturing processes have increased the use of composite materials in the aerospace and wind energy industries as a primary load carrying structures in complex shapes. However, use of composite materials in complex geometries such as L-shaped laminates creates weakness at the radius which causes delamination. Carbon nanotubes (CNTs) is preferred as a toughening materials in composite matrices due to their high m...
Numerical modeling of failure in composite L-beam and T-joint structures Temiz, Pakize; Çöker, Demirkan; Department of Aerospace Engineering (2022-12-02) Laminated curved-shape composite structures which are used as stiffening components in aerospace, wind, automotive and marine industries are subjected to high radial and tangential stresses. For the scope of this thesis, different modelling strategies are investigated to simulate interlaminar and intralaminar failure in composite L-beam and T-joint structures using commercial finite element (FE) code ABAQUS/Standard 2020. In the first part, [030] and [03/903/03/903/03]s laminated L-beams are evaluated using...

Citation Formats

A. Tamer Tahir and D. Çöker, “Computational Investigation of the 3-D effects on Dynamic Fracture of Curved Composite Laminates,” presented at the 21th International Conference on Composite Structures, 2018, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/80818.