Laminated textile composites – Problems with bonding layers and sewing

2021 ◽  
pp. 152808372110194
Author(s):  
Stana Kovačević ◽  
Darko Ujević ◽  
Jacqueline Domjanić ◽  
Samir Pačavar
Keyword(s):  
Automotive Industry ◽  
Laminated Composites ◽  
Laminated Composite ◽  
Textile Composites ◽  
Woven Fabric ◽  
Back Side ◽  
Systematic Analysis ◽  
Needle Penetration ◽  
Technical Textiles ◽  
Penetration Force

In this paper laminated composites with woven fabric on the front side, polyurethane foam (PU) in the middle and knitted fabric on the back side were analyzed. These materials are widely used in the automotive industry, medicine, protection activities and other groups of technical textiles Based on analyses and problems encountered in practice, the hypothesis was made that the speed of joining the components into a laminated composite influences the needle penetration force and finally the seam quality when sewing. Investigations were performed using three GB needle systems, two PU thicknesses (2 and 4 mm) and three joining speeds (30, 35 and 40 m/min). According to the results obtained, it can be concluded that higher joining speeds determine lower penetration forces. By systematic analysis of the sewing seam the deformation of laminated composites occur at stitch points, which is caused by hardened PU residues after the lamination of components to a composite. Heating the needle during sewing resulted in partial melting of PU and adhesion of needle to the material is penetrating through which means damage to the needle and seam. This negative occurrence is more pronounced at lower bonding speeds, for higher PU thickness and thicker needle. Based on the results obtained it can be claimed that bonding speed, polyurethane thickness (PU) as well as needle type affected the penetration forces of sewing and seam quality.

Experimental Researches on Temperature-Dependent Tensile Properties of Laminated Resin Composites Reinforced by Plain Woven Fabric

2010 ◽  
Vol 33 ◽  
pp. 119-122
Author(s):  
Guang Wei Chen ◽  
Jia Lu Li ◽  
G.F. He
Keyword(s):  
Tensile Strength ◽  
High Temperature ◽  
Tensile Property ◽  
Room Temperature ◽  
Laminated Composites ◽  
Tensile Load ◽  
Laminated Composite ◽  
Tensile Tests ◽  
Woven Fabric ◽  
Resin Composites

The purpose of this paper is to investigate the tensile property of laminated resin composites reinforced by carbon fiber plain woven fabric at relatively high temperature. For this purpose, the tensile tests of laminated resin composites are carried out at room temperature(20°C) and high temperature(150°C and 180°C). The effect rules of different temperature on the tensile property of these composites are discussed. The reasons for the variations of tensile property of these composites at different temperature are also analyzed. At 150 °C and 180 °C, the tensile strength of laminated composite decreased by 13.3% and 34.42% respectively, compared with that at room temperature, which shows that the tensile strength of resin laminated composites is sensitive at high temperature. The reason of the tensile strength of resin laminated composites declined at high temperature is that resin has been damaged and can not transfer tensile load, which makes resin and fiber can not bear the tensile load together at high temperature. The research results will provide a basic reference for the application of plain woven fabric reinforced resin laminated composites at room temperature to 180°C.

scholarly journals Comparative study of elastic properties and mode I fracture energy of carbon nanotube/epoxy and carbon fibre/epoxy laminated composites

2020 ◽  
Vol 8 (1) ◽  
Author(s):  
Jyotikalpa Bora ◽  
Sushen Kirtania
Keyword(s):  
Carbon Nanotube ◽  
Carbon Fibre ◽  
Fracture Energy ◽  
Elastic Properties ◽  
Volume Fraction ◽  
Laminated Composites ◽  
Laminated Composite ◽  
Fe Analysis ◽  
Mode I ◽  
Mode I Fracture

Abstract A comparative study of elastic properties and mode I fracture energy has been presented between conventional carbon fibre (CF)/epoxy and advanced carbon nanotube (CNT)/epoxy laminated composite materials. The volume fraction of CNT fibres has been considered as 15%, 30%, and 60% whereas; the volume fraction of CF has been kept constant at 60%. Three stacking sequences of the laminates viz.[0/0/0/0], [0/90/0/90] and [0/30/–30/90] have been considered in the present analysis. Periodic microstructure model has been used to calculate the elastic properties of the laminated composites. It has been observed analytically that the addition of only 15% CNT in epoxy will give almost the same value of longitudinal Young’s modulus as compared to the addition of 60% CF in epoxy. Finite element (FE) analysis of double cantilever beam specimens made from laminated composite has also been performed. It has been observed from FE analysis that the addition of 15% CNT in epoxy will also give almost the same value of mode I fracture energy as compared to the addition of 60% CF in epoxy. The value of mode I fracture energy for [0/0/0/0] laminated composite is two times higher than the other two types of laminated composites.

Effects of hostile solutions on the static and dynamic behavior of carbon/epoxy composites

2021 ◽  
pp. 002199832110200
Author(s):  
H Ersen Balcıoğlu ◽  
Raif Sakin ◽  
Halit Gün
Keyword(s):  
Bending Strength ◽  
Laminated Composites ◽  
Fatigue Behavior ◽  
Laminated Composite ◽  
Test Sample ◽  
Solution Concentration ◽  
Static Stability ◽  
Three Point Bending ◽  
Sem Image ◽  
Solution Type

Fiber-reinforced laminated composite is often used in harsh environments that may affect their static stability and long-term durability as well as residual strength. In this study, the effect of heavy chemical environments such as acid and alkaline and retaining time for these environments on flexural strength and flexural fatigue behavior of carbon/epoxy laminated composites were investigated. In this context, carbon/epoxy was retained into an acidic and alkaline solution having 5%, 15%, and 25% concentration by weight for 1–4 months. Fatigue behavior of carbon/epoxy was determined under dynamic flexural load, which corresponds to 80%, 70%, 60%, 50%, and 40% of static three-point bending strength of the test sample. SEM image of damaged specimens was taken to describe the failure mechanism of damage which occurs after fatigue. Also, to better understand environmental condition on the fatigue life, results were compared with results of carbon/epoxy laminated composites, which were not retained into any environments (unretained). The test results showed that the solution type, solution concentration, and retaining time caused noticeable changes in the static and dynamic strengths of carbon/epoxy laminated composites.

Strength Prediction of Laminated Composites upon Independent Constituent Properties

2015 ◽  
Vol 665 ◽  
pp. 153-156
Author(s):  
Zheng Ming Huang ◽  
Li Min Xin
Keyword(s):  
Ultimate Strength ◽  
Input Data ◽  
Laminated Composites ◽  
Laminated Composite ◽  
Failure Detection ◽  
Strength Prediction ◽  
Internal Stresses ◽  
Matrix Properties

To predict ultimate strength of a laminated composite subjected to any load only using its constituent fiber and matrix properties measured independently, three challenging problems must be resolved with high success. First, internal stresses in the fiber and matrix must be accurately determined. Second, efficient failure detection for laminae and laminate upon the internal stresses must be achieved. Last but not the least, input data for the in-situ strengths of the constituents must be defined correctly from their original counterparts, as the former, different from the latter, are immeasurable. This presentation briefly summarizes our work on the targeted subject. All of the three issues have been systematically addressed with reasonable success.

Effects of Accelerated Aging Period of Time at 180°C on Tensile Property of Plain Woven Fabric/Epoxy Resin Laminated Composites

2012 ◽  
Vol 182-183 ◽  
pp. 76-79 ◽  
Author(s):  
Lei Lei Song ◽  
Quan Rong Liu ◽  
Jia Lu Li
Keyword(s):  
Tensile Strength ◽  
Carbon Fiber ◽  
Epoxy Resin ◽  
Laminated Composites ◽  
Accelerated Aging ◽  
Woven Fabric ◽  
Accelerated Ageing ◽  
Time Intervals ◽  
Composite Samples

In this paper, carbon fiber reinforced resin matrix composites were produced by stacking eight pieces of carbon fiber woven plain fabric and subjected to accelerated ageing. Accelerated ageing was carried out in oven at 180°C for three different time intervals (60 hours, 120 hours and 180 hours). The influence of different ageing time intervals at 180°C on tensile properties of laminated composites was examined, compared with the composites without aging. The appearance and damage forms of these laminated composites were investigated. The results revealed that the tensile strength of the laminates declined significantly after long term accelerated aging at 180°C. The average tensile strengths of composite samples aged 60 hours, 120 hours, and 180 hours period of time at 180°C are 80.36%, 79.82%, 76.57% of average tensile strength of composite samples without aging, respectively. The high temperature accelerated aging makes the resin macromolecular structure in the composites changed, and then the adhesive force between fiber bundles and resin declines rapidly which result in the tensile strength of composites aged decrease. This research provides a useful reference for long term durability of laminated/epoxy resin composites.

The Effects of Fiber Volume Fraction on the Experiment Modal Behavior of 45°/-45° Carbon Fiber Plain Woven Fabric/Epoxy Resin Composites

2012 ◽  
Vol 583 ◽  
pp. 150-153
Author(s):  
Qian Liu ◽  
Xiao Yuan Pei ◽  
Jia Lu Li
Keyword(s):  
Carbon Fiber ◽  
Epoxy Resin ◽  
Natural Frequency ◽  
Fiber Volume Fraction ◽  
Volume Fraction ◽  
Laminated Composites ◽  
Woven Fabric ◽  
Resin Composites ◽  
Fiber Volume ◽  
Epoxy Resin Composites

The modal properties of carbon fiber woven fabric (with fiber orientation of 45°/-45°) / epoxy resin composites with different fiber volume fraction were studied by using single input and single output free vibration of cantilever beam hammering modal analysis method. The effect of different fiber volume fraction on the modal parameters of laminated composites was analyzed. The experimental results show that with the fiber volume fraction increasing, the natural frequency of laminated composites becomes larger and damping ratio becomes smaller. The fiber volume fraction smaller, the peak value of natural frequency becomes lower and the attenuating degree of acceleration amplitude becomes faster.

Mechanical Behavior of Anti-Symmetrically Laminated Composite Blades

2005 ◽  
Author(s):  
Masahiro Hojo ◽  
Ryosaku Hashimoto ◽  
Akinori Ogawa ◽  
Yasushi Sofue ◽  
Yukio Matsuda
Keyword(s):  
Finite Element ◽  
Mechanical Behavior ◽  
Rotational Speed ◽  
Laminated Composites ◽  
Laminated Composite ◽  
Aircraft Engines ◽  
Finite Element Analyses ◽  
Coupling Effects ◽  
Angle Change ◽  
Composite Blades

Anti-symmetrically laminated composites have coupling effects between tensile stress and twisting deformation, and are very attractive as fan blade materials of aircraft engines. Blades fabricated by anti-symmetrically laminated composites can automatically adjust the stagger angle to better aerodynamic conditions with change of axial force or rotational speed owing to the coupling effects. Thus, the anti-symmetrically laminated composite blades are expected to improve aerodynamic efficiency and the stability of aircraft engines. In this paper, the mechanical behavior of anti-symmetrically laminated composite blades is evaluated by spin tests and finite element analyses. Three kinds of blades fabricated by carbon/epoxy laminated composites in different anti-symmetrical stacking sequences were tested. A non-contact measurement technique using a multi-channel optical fiber sensor was used for measurements of blade deformations at high-speed rotating conditions, up to 10,000 rpm. The twisted angle change at the blade tip could be successfully measured. The twisted angle change increased in proportion to the second power of rotational speed, and the maximum angle change was about 4 degree at 10,000 rpm. The finite element analysis results agreed well with the spin test results. Furthermore, the three-dimensional deformation of the test blades was evaluated based on finite element analyses.

scholarly journals Mechanisms of Mode I Interlaminar Fracture of Glass Woven Fabric Composites

2000 ◽  
Vol 9 (3) ◽  
pp. 096369350000900 ◽  
Author(s):  
M. Kotaki ◽  
T. Kuriyama ◽  
H. Hamada ◽  
Z. Maekawa ◽  
I. Narisawa
Keyword(s):  
Fracture Toughness ◽  
Laminated Composites ◽  
Damage Zone ◽  
Woven Fabrics ◽  
Woven Fabric ◽  
Mode I ◽  
Interlaminar Fracture ◽  
Woven Fabric Composites ◽  
Fabric Composites ◽  
Silane Concentration

Mode I interlaminar fracture behaviours were investigated on the laminated composites reinforced with plain glass woven fabrics which were treated with different silane concentrations. The low silane concentration specimen indicated higher fracture toughness, compared to the high silane concentration specimen. This is due to the occurrence of the micro crack in the fibre strands. In the low silane concentration specimen, larger damage zone due to the micro crack was formed ahead of the crack tip.

Enhanced Plasticity of Cu-Based Laminated Composites Produced by Cold Roll-Bonding

2010 ◽  
Vol 667-669 ◽  
pp. 1015-1020
Author(s):  
H.S. Liu ◽  
Bin Zhang ◽  
G.P. Zhang
Keyword(s):  
Laminated Composites ◽  
Uniform Elongation ◽  
Laminated Composite ◽  
Plastic Instability ◽  
Interface Bonding ◽  
Roll Bonding ◽  
Cold Roll ◽  
Submicron Scale ◽  
Cold Roll Bonding ◽  
Cold Rolled

Two different laminated composites with submicron-scale grain size and strong interface bonding toughness, Cu/Al and Cu/Cu, were fabricated by cold-roll bonding at ambient temperature, and then annealing of the laminated composites was conducted to get different interface bonding toughness. It was found that a better strength-plasticity combination for the laminated composites could be obtained through stronger interface bonding toughness, which effectively delayed the onset of plastic instability and premature local necking of the material. Uniform elongation of both Cu/Al and Cu/Cu laminated composites was enhanced compared with that of the cold-rolled Cu. At the same strength level, plasticity of the Cu/Cu laminated composite is better than that of the Cu/Al one and that of the cold-rolled Cu. Mechanisms of plasticity instability and fracture of the laminated composites were evaluated.

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