Characterization of bi-stable pure and hybrid composite laminates – An experimental investigation of the static and dynamic responses

In this study, the static and dynamic responses of bi-stable hybrid composite laminates [0/AL/90]T and [02/AL/902]T were scrutinized, and their behavior was compared to bi-stable pure composite laminates including [0/90]T and [02/902]T. The work consisted of an analytical study that was validated experimentally. An analytical method based on Hamilton’s principle was developed to investigate the static and vibration characteristics of the laminates. Experimentally, curvatures and out-of plane-displacement, and snap-through load were measured using a quasi-static loading on a universal testing machine. Further experimental analysis was performed to characterize the damping viscous ratio, natural frequency, and critical base excitation that cause the snapping between the two different stable shapes. The results show that the hybridization of bi-stable pure composite laminates has the potential to increase the stable curvatures and enhance the static load-carrying capability up to five times when compared to a pure bi-stable composite laminate of the same thickness. It was also observed that the hybridization of bi-stable pure composite laminates may result in a dramatic change in the dynamic response. The natural frequencies of bi-stable hybrid composite laminates are increased in comparison with bi-stable pure composite laminates. The critical base excitation required for snapping has increased significantly for the hybrid composite laminate. The qualitative and quantitative comparisons between the analytical and experimental results were very promising and they agreed well.

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Characterization and optimization of hybrid carbon–glass epoxy composites under combined loading

Journal of Composite Materials ◽

10.1177/0021998319834673 ◽

2019 ◽

Vol 53 (18) ◽

pp. 2593-2605 ◽

Cited By ~ 2

Author(s):

V Infante ◽

JFA Madeira ◽

Rui B Ruben ◽

F Moleiro ◽

Sofia Teixeira de Freitas

Keyword(s):

Hybrid Composite ◽

Composite Plates ◽

Experimental Tests ◽

Combined Loading ◽

Design Variables ◽

Out Of Plane ◽

Global And Local Optimization ◽

Plane Displacement ◽

Global And Local ◽

Hybrid Carbon

This work is intended to characterize the mechanical behavior of hybrid carbon–glass composite plates under combined loading of bending and torsion, and to determine the optimal ply fiber orientations to minimize the maximum out-of-plane displacement under such loading conditions. Hybrid composite plates were manufactured with 10 plies each and different stacking sequences using hand lay-up, with carbon fiber and glass fiber reinforcements in an epoxy matrix. Two experimental setups (involving two distinct boundary conditions) are here considered to test the composite plates, both simulating combined loading of bending and torsion. Numerical simulations of the experimental tests were performed in ABAQUS® and validated with the experimental data. Using the ply fiber orientations as design variables, the hybrid composite plates were then optimized using global and local optimization using direct search (GLODS). The objective function of minimization of the maximum out-of-plane displacement is carried out through an interactive cycle between GLODS and ABAQUS®. Specimens of three optimized laminates were also manufactured for experimental validation. The optimization process contributed to improve the performance of the hybrid composite plates in more than 30% when compared to some non-optimized plates.

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The Effect of a Coupling Agent on the Impact Behaviour of Flax Fibre Composites

Journal of Engineering Materials and Technology ◽

10.1115/1.4050637 ◽

2021 ◽

pp. 1-17

Author(s):

Cihan Kaboglu ◽

Jun Liu ◽

Haibao Liu ◽

Pietro Russo ◽

Giorgio Simeoli ◽

...

Keyword(s):

Impact Loading ◽

Coupling Agent ◽

Testing Machine ◽

Natural Fibers ◽

Flax Fiber ◽

Image Correlation ◽

Impact Tests ◽

Out Of Plane ◽

Plane Displacement ◽

The Impact

Abstract The effects of a coupling agent on the behavior of flax fiber reinforced composites have been investigated by testing the specimens under both quasi-static indentation and high velocity impact loading. The specimens are manufactured embedding a commercial flax fiber fabric in a polypropylene (PP) matrix, neat and pre-modified with a maleic anhydride grafted PP, the latter acting as a coupling agent to enhance the interfacial adhesion. Quasi-static (QS) compressive tests were performed using a dynamometer testing machine equipped with a high-density polyethylene indenter having the same geometry of the projectile employed in the impact tests. The impact tests were conducted setting three different impact velocities. Digital Image Correlation maps of out-of-plane displacement were employed to compare the specimens with and without the coupling agent. The QS testing results indicate that the coupling agent has an enhancing influence on the bending stiffness of tested flax composites. The testing results show that the coupling agent improves the mechanical behavior by decreasing the out-of-plane displacement under impact loading. This approach gives rise to new materials potentially useful for applications where impact performance is desired whilst also providing an opportunity for the incorporation of natural fibers to produce a lightweight composite.

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Behaviour of Hybrid Titanium Composite Laminate (HTCL) under In-Plane Loading

Advanced Composites Letters ◽

10.1177/096369350401300104 ◽

2004 ◽

Vol 13 (1) ◽

pp. 096369350401300 ◽

Cited By ~ 1

Author(s):

G. Allegri ◽

S. Corradi ◽

M. Marchetti ◽

L. Suanno

Keyword(s):

Hybrid Composite ◽

Composite Laminates ◽

Composite Laminate ◽

Damage Mechanics ◽

Fatigue Loading ◽

Harsh Environments ◽

Fatigue Properties ◽

Mechanical Degradation ◽

Titanium Grade ◽

Good Agreement

The Hybrid Titanium Composite Laminate (HTCL) incorporates the mechanical advantages of existing hybrid composite laminates such as ARALL and GLARE while extending their applications to harsh environments. Hybrid composite laminates, consisting of layers of Titanium Grade 2 foils bonded together with fibre-reinforced prepreg plies, have been tested under fatigue loading. HTCL has proven to possess exceptional strength and fatigue resistance. Degraded stiffness and ultimate resistances are provided through experimental stress-strain response of HTCL laminates, which are compared with predicted results by a laminate analysis code. The roles of mechanical degradation, the static and dynamic behaviour and fatigue properties of HTCL are addressed. The development of damage in HTCL specimens during fatigue is shown including titanium ply cracking, interfacial debonding, and layer failure. These tests provided several parameters in order to calibrate a numerical Lamaitre's Continuous Damage Mechanics (CDM) fatigue model, which resulted in good agreement with experimental data. The influence of the fatigue properties of titanium layers on the fatigue of HTCL is discussed. The performance of HTCL laminates in fatigue is shown superior to that of the monolithic titanium alloy for room-temperature conditions.

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Quality Inspection of Flip Chip Solder Bumps Using Integrated Analytical, Numerical, and Experimental Modal Analyses

Journal of Electronic Packaging ◽

10.1115/1.2957328 ◽

2008 ◽

Vol 130 (3) ◽

Cited By ~ 6

Author(s):

Jin Yang ◽

I. Charles Ume

Keyword(s):

Modal Analysis ◽

Manufacturing Industry ◽

Flip Chip ◽

Solder Bump ◽

Dynamic Responses ◽

Mode Shapes ◽

Inspection System ◽

Solder Bumps ◽

Out Of Plane ◽

Plane Displacement

Solder bump inspection of surface mount packages has been a crucial process in the electronics manufacturing industry. A solder bump inspection system has been developed using laser ultrasound and interferometric techniques. In this research, modal analysis is important to correlate the defects with dynamic responses of packaged electronic devices under pulsed laser loading. The effect of solder bump defects on the mode frequencies and mode shapes is reported in this paper. The objective is to develop a modal analysis approach, which integrates analytical, numerical, and experimental methods. In particular, this paper discusses the analytical modeling, numerical modeling, and transient out-of-plane displacement measurements for a 6.35×6.35×0.6mm3 PB18 flip chip mounted on a FR4 board.

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Bi-stable hybrid composite laminates containing metallic strips: an experimental and numerical investigation

Smart Materials and Structures ◽

10.1088/1361-665x/ab1183 ◽

2019 ◽

Vol 28 (5) ◽

pp. 055030 ◽

Cited By ~ 2

Author(s):

A Firouzian-Nejad ◽

C Bowen ◽

S Mustapha ◽

M Ghayour ◽

S Ziaei-Rad

Keyword(s):

Numerical Investigation ◽

Hybrid Composite ◽

Composite Laminates ◽

Stable Hybrid

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Thermally Induced Vibration Analysis of Composite Laminate Based on Equivalent Displacement Method

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.576.87 ◽

2014 ◽

Vol 576 ◽

pp. 87-93

Author(s):

Xiang Hong Kong ◽

Zhi Jin Wang

Keyword(s):

Composite Laminates ◽

Composite Laminate ◽

Dynamic Responses ◽

Displacement Method ◽

Fe Method ◽

Thermally Induced ◽

Post Process ◽

Shear Theory ◽

Classic Theory ◽

Close Proximity

Thermally induced vibration (TIV) of composite laminate subjected to suddenly applied heating is studied using finite element (FE) method in this paper. Some Python programs written by the authors are used to process the data of the analysis flow, and complete the pre- and post-process of FE models used in the four analyses. An equivalent displacement method is proposed to calculate equivalent temperature load. Dynamic responses of six composite laminates with different sizes are analyzed with solid FE models and shell FE models. The results gotten by FE method are in close proximity to that gotten by classic theory and shear theory under certain conditions. It is proved that the TIV analysis method proposed in this paper is reliable and efficient. The TIV analysis with FE method based on equivalent displacement method can solve the dynamic response of a structure due to sudden changes of temperature or suddenly applied heating.

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Restraint Performance of Stud Connection during Lateral-Torsional Buckling under Synchronized In-Plane Displacement and Out-of-Plane Rotation

Journal of Structural Engineering ◽

10.1061/(asce)st.1943-541x.0002582 ◽

2020 ◽

Vol 146 (4) ◽

pp. 04020029

Author(s):

Atsushi Suzuki ◽

Kanako Abe ◽

Yoshihiro Kimura

Keyword(s):

Plane Rotation ◽

Lateral Torsional Buckling ◽

Torsional Buckling ◽

Out Of Plane ◽

Plane Displacement ◽

Stud Connection

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Sensor Integrated Load-Bearing Structures: Measuring Axis Extension with DIC-Based Transducers

Sensors ◽

10.3390/s21124104 ◽

2021 ◽

Vol 21 (12) ◽

pp. 4104

Author(s):

Nassr Al-Baradoni ◽

Peter Groche

Keyword(s):

Cost Effective ◽

Image Correlation ◽

Maximum Deviation ◽

Single Image ◽

Eccentric Load ◽

Load Bearing ◽

Out Of Plane ◽

Axis Extension ◽

Plane Displacement ◽

Imaging Sensor

In this paper we present a novel, cost-effective camera-based multi-axis force/torque sensor concept for integration into metallic load-bearing structures. A two-part pattern consisting of a directly incident and mirrored light beam is projected onto the imaging sensor surface. This allows the capturing of 3D displacements, occurring due to structure deformation under load in a single image. The displacement of defined features in size and position can be accurately analyzed and determined through digital image correlation (DIC). Validation on a prototype shows good accuracy of the measurement and a unique identification of all in- and out-of-plane displacement components under multiaxial load. Measurements show a maximum deviation related to the maximum measured values between 2.5% and 4.8% for uniaxial loads ( and between 2.5% and 10.43% for combined bending, torsion and axial load. In the course of the investigations, the measurement inaccuracy was partly attributed to the joint used between the sensor parts and the structure as well as to eccentric load.

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