Analytical studies and numerical predictions of stresses in shear joints of layered composite panels for aerospace applications

2021 ◽  
Vol 255 ◽  
pp. 112927
Author(s):  
C.K. Krishnadasan ◽  
N. Siva Shanmugam ◽  
B. Sivasubramonian ◽  
B. Nageswara Rao ◽  
R. Suresh
Keyword(s):  
Layered Composite ◽  
Composite Panels ◽  
Aerospace Applications ◽  
Numerical Predictions ◽  
Analytical Studies

scholarly journals Static and Fatigue Failures of Adhesively Bonded Laminate Joints in Moist Environments

2011 ◽  
Vol 20 (8) ◽  
pp. 1217-1242 ◽  
Author(s):  
K. B. Katnam ◽  
A. D. Crocombe ◽  
H. Sugiman ◽  
H. Khoramishad ◽  
I. A. Ashcroft
Keyword(s):  
Cohesive Zone ◽  
Experimental Tests ◽  
Static Fatigue ◽  
Test Results ◽  
Adhesively Bonded ◽  
Aerospace Applications ◽  
Numerical Predictions ◽  
Fatigue Failures ◽  
Good Agreement

Advanced structural adhesives are now an important joining technique in automobile and aerospace applications. The perceived uncertainty in the long-term structural performance of bonded members when subjected to static/fatigue loads in aggressive environments is probably restricting an even more widespread use of this joining technology. In this article, the effect of moisture on the static and fatigue resistances of adhesively bonded laminate joints was investigated. Experimental tests were performed on both aged and unaged adhesively bonded laminate joints for static and fatigue responses. Further, using a cohesive zone approach for the adhesive bondlines, a combined diffusion–stress analysis was developed to predict the progressive damage observed in the joints tested experimentally. The numerical predictions were found to be in good agreement with the experimental test results.

A novel composite model for vibration of thin-walled layered composite panels incorporating the agglomeration of CNTs

2021 ◽  
pp. 106897
Author(s):  
Mohammad Amin Shahmohammadi ◽  
Mojtaba Azhari ◽  
Hamzeh Salehipour ◽  
Ömer Civalek
Keyword(s):  
Layered Composite ◽  
Composite Model ◽  
Composite Panels ◽  
Thin Walled

Blast Resistance of Hybrid Elastomeric Composite Panels

2016 ◽  
Vol 846 ◽  
pp. 458-463 ◽  
Author(s):  
Phuong Tran ◽  
Abdallah Ghazlan ◽  
Tuan D. Ngo
Keyword(s):  
Blast Resistance ◽  
Element Model ◽  
Layered Composite ◽  
Unidirectional Composite ◽  
Constitutive Law ◽  
Composite Panel ◽  
Composite Panels ◽  
Failure Model ◽  
Cohesive Law ◽  
Deformation And Failure

In this study, a finite element model was developed to understand the deformation and failure mechanisms of a multi-layered composite panel under blast. Fibre (E-glass fiber) and matrix (vinylester resin) damage and degradation of individual unidirectional composite laminas were modelled using the Hashin failure model. The delamination between laminas was modelled by a traction-separation cohesive law. A Polyurea layer was placed at the rear of the panel to study its effects on the damage evolution in the composite laminas, and was modelled using a Mooney-Rivlin constitutive law. The model-predicted deformation histories, fiber/matrix damage patterns, and inter-lamina delamination were compared between monolithic and composite panels. The model revealed that the Polyurea plays an important role in improving the panel’s performance.

scholarly journals Experimental Characterization of a High-Damping Viscoelastic Material Enclosed in Carbon Fiber Reinforced Polymer Components

2020 ◽  
Vol 10 (18) ◽  
pp. 6193 ◽  
Author(s):  
Marco Troncossi ◽  
Sara Taddia ◽  
Alessandro Rivola ◽  
Alberto Martini
Keyword(s):  
Viscoelastic Material ◽  
Composite Laminates ◽  
Vehicle Body ◽  
Composite Panels ◽  
Damping Properties ◽  
Aerospace Applications ◽  
Body Shell ◽  
Promising Solution ◽  
Noise Vibration ◽  
Thin Panel

This work aims to identify the damping properties of a commercial viscoelastic material that can be embedded and cured between the layers of composite laminates. The material may be adopted for reducing the vibration response of composite panels, typically used in automotive and aerospace applications, e.g., as vehicle body shell components. In order to objectively estimate the actual potential to enhance the noise vibration and harshness aspects, the effects of the viscoelastic material on the modal parameters of carbon/epoxy thin panels are quantitatively assessed through experimental modal analysis. Two different experiments are conducted, namely impact hammer tests and shaker excitation measurements. Based on the results of the experimental campaign, the investigated material is confirmed as a promising solution for possibly reducing the severity of vibrations in composite panels, thanks to its high damping properties. Indeed, the presence of just one layer proves to triple the damping properties of a thin panel. An approximate damping model is derived from the measured data in order to effectively simulate the dynamic response of new design solutions, including thin composite panels featuring the viscoelastic material.

scholarly journals Numerical analysis of layered composite panel behavior with interlaminar defects subject to dynamic loads

2019 ◽  
Vol 15 (2) ◽  
pp. 127-134
Author(s):  
Aleksandr L Medvedskiy ◽  
Mikhail I Martirosov ◽  
Anton V Khomchenko
Keyword(s):  
Pressure Field ◽  
Normal Modes ◽  
Failure Criteria ◽  
Layered Composite ◽  
Unidirectional Composite ◽  
Dynamic Loads ◽  
Composite Panel ◽  
Composite Panels ◽  
Modeling Methodology ◽  
Multiple Delamination

Aims of research. Polymer unidirectional composite laminate panel behavior with interlaminate defects under action of different dynamic loads is consider. Methods. Normal modes and eigenvalues of rectangular composite panels in the presence multiple delamination different sizes ellipsoidal form are calculated. The dependences of the maximum deflections from the frequency of the stationary pressure field action are constructed. Distribution field of panels plies failure index under action of nonstationary pressure field by using different failure criteria for composites is determined. Results. Modeling methodology composite panels behavior in the presence multiple interlaminar defects under action of different dynamic loads is developed. Analysis of failure panel with the use of different failure criteria for composites is carried out.

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