Experimental and analytical testing of a composite laminate material G10/FR4 under cyclic loading

2020 ◽  
Author(s):  
M. S. Heaven Dani ◽  
G. M. Pradeep ◽  
K. Balamanikandasuthan ◽  
K. Kalaiselvan ◽  
D. Athikesavan
Keyword(s):  
Cyclic Loading ◽  
Composite Laminate ◽  
Laminate Material

Fatigue Delamination Analysis of Composite Laminates with a Central Hole Using Interface Elements

2011 ◽  
Vol 471-472 ◽  
pp. 568-571
Author(s):  
Hossein Hosseini-Toudeshky ◽  
A. Jasemzadeh ◽  
Bijan Mohammadi
Keyword(s):  
Cyclic Loading ◽  
Composite Laminates ◽  
Mixed Mode ◽  
Composite Laminate ◽  
Constitutive Law ◽  
Central Hole ◽  
Interface Element ◽  
Interface Elements

In this paper a solid like interface element along with a fatigue constitutive law is used to study the damage behaviour of holed composite laminates under cyclic loading. For this purpose a user element routine and a material routine was developed include the interface element and to handle the formulation of progressive fatigue damages. The developed procedure is used to predict delamination initiation and growth in mixed-mode condition for a typical composite laminate. The obtained results for damage and stresses are compared with the available results in the literature.

Mechanical Properties of a Centrally Notched APC-2 Composite Laminate Due to Fatigue Loading at Elevated Temperature (II)

2009 ◽  
Vol 25 (3) ◽  
pp. 251-259
Author(s):  
M.-H. R. Jen ◽  
Y.-C. Tseng
Keyword(s):  
Mechanical Properties ◽  
Elevated Temperature ◽  
Cyclic Loading ◽  
Composite Laminates ◽  
Composite Laminate ◽  
Stress Amplitude ◽  
Fatigue Loading ◽  
The Cross ◽  
Applied Stresses ◽  
Strain Model

AbstractThe temperature versus life (T-N) curves of both centrally notched and unnotched AS-4/PEEK (APC-2) composite laminates due to constant stress amplitude tension-tension (T-T) fatigue loading were investigated systematically. The cross-ply laminate possesses the higher mechanical properties than those of the quasi-isotropic laminate at elevated temperature, and also the mechanical properties of both lay-ups are degraded significantly as the temperature increasing. Combining both effects of notch and temperature at various normalized stresses it is found the cross-ply laminate possesses more resistance to cyclic loading than that of the quasi-isotropic laminate. Additionally, the predictive strain model is in a practical and simple form. Alternatively, the T-N curves, instead of conventionally S-N curves, at variously applied stresses are accomplished for preliminary designs and applications.

scholarly journals Advanced Heliopol/Stratimat Composite Laminate Material Behavior under Cyclic Bending Loads

2017 ◽  
Vol 181 ◽  
pp. 175-181
Author(s):  
Arina Modrea ◽  
Horatiu Teodorescu-Draghicescu ◽  
Ioan Szava ◽  
Renata Szava ◽  
Botond Galfi
Keyword(s):  
Composite Laminate ◽  
Material Behavior ◽  
Laminate Material ◽  
Cyclic Bending ◽  
Bending Loads

Multiple Delaminations Growth in Composite Laminates under Compressive Cyclic Loading in Post-Buckling

2012 ◽  
Vol 225 ◽  
pp. 195-200
Author(s):  
Hossein Hosseini-Toudeshky ◽  
M. Saeed Goodarzi ◽  
Bijan Mohammadi
Keyword(s):  
Cyclic Loading ◽  
Cohesive Zone ◽  
Composite Laminates ◽  
Mixed Mode ◽  
Composite Laminate ◽  
Constitutive Law ◽  
Interface Element ◽  
Delamination Growth ◽  
Post Buckling ◽  
Interface Layers

Due to discontinuity of mechanical properties in composite laminates, failure occurs in different damage mechanisms. Delamination growth of adjacent layers is a major failure mechanism in laminates with various layup configurations. Pre existing delamination may initiate in composite laminate before use, due to impact in assembly and fabrication process. Cyclic compressive loading may cause delamination growth due to both post-bucking behavior and fatigue nature of loading. In this paper, a 3D mixed-mode interface element model has been developed to simulate the growth of multiple delaminations under compressive cyclic loading. For this purpose, the presented model should be able to handle the geometry nonlinearity of post-buckling and material nonlinearity of cohesive zone constitutive law under cyclic loading at interfaces. Because of mixed-mode condition of stress field at the delamination-front of post-buckled laminates, a mixed-mode bilinear constitutive law has been used as user material in this model. Paris Law has been used to relate the energy release rate to the fatigue crack growth in cohesive zone. A composite laminate with pre-existing delamination under buckling load, available from the literature has been reproduced with the present approach. Finally, laminates containing multiple delaminations in various interface layers have been analyzed under compressive fatigue loading. It is shown that the pre-existing delamination with more depth from the surface of laminate causes more initial static and fatigue delamination growth rate.

Comparative study of the effective parameters on residual stress relaxation in welded aluminum plates under cyclic loading

2020 ◽  
Vol 21 (5) ◽  
pp. 505
Author(s):  
Yousef Ghaderi Dehkordi ◽  
Ali Pourkamali Anaraki ◽  
Amir Reza Shahani
Keyword(s):  
Residual Stress ◽  
Cyclic Loading ◽  
Stress Relaxation ◽  
Stress Amplitude ◽  
Cyclic Plasticity ◽  
Mean Stress ◽  
Effective Parameters ◽  
Perfect Plasticity ◽  
Residual Stress Relaxation ◽  
Aluminum Plates

The prediction of residual stress relaxation is essential to assess the safety of welded components. This paper aims to study the influence of various effective parameters on residual stress relaxation under cyclic loading. In this regard, a 3D finite element modeling is performed to determine the residual stress in welded aluminum plates. The accuracy of this analysis is verified through experiment. To study the plasticity effect on stress relaxation, two plasticity models are implemented: perfect plasticity and combined isotropic-kinematic hardening. Hence, cyclic plasticity characterization of the material is specified by low cycle fatigue tests. It is found that the perfect plasticity leads to greater stress relaxation. In order to propose an accurate model to compute the residual stress relaxation, the Taguchi L18 array with four 3-level factors and one 6-level is employed. Using statistical analysis, the order of factors based on their effect on stress relaxation is determined as mean stress, stress amplitude, initial residual stress, and number of cycles. In addition, the stress relaxation increases with an increase in mean stress and stress amplitude.

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