Pub Date : 2023-11-21DOI: 10.1080/09243046.2023.2280353
Limin Bao, Yuya Tanasawa, Jian Shi, Ye Sun
Over the course of many years of use, impingement wear from dust, sand, and other materials can damage wind turbine blades, necessitating repairs and other maintenance work. Recently, wind turbine ...
{"title":"Erosion resistant effects of protective films for wind turbine blades","authors":"Limin Bao, Yuya Tanasawa, Jian Shi, Ye Sun","doi":"10.1080/09243046.2023.2280353","DOIUrl":"https://doi.org/10.1080/09243046.2023.2280353","url":null,"abstract":"Over the course of many years of use, impingement wear from dust, sand, and other materials can damage wind turbine blades, necessitating repairs and other maintenance work. Recently, wind turbine ...","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"1 1","pages":""},"PeriodicalIF":2.9,"publicationDate":"2023-11-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138531054","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Three-dimensional (3D) printing technology has revolutionized the fabrication of complex geometries, including electromagnetic wave absorbers. In this study, the multilayer radar absorbing structur...
{"title":"Fabrication of multi-layer radar absorbing structures based on continuous fiber 3D printing and thickness correction method","authors":"Do-Hyeon Jin, Jong-Min Hyun, Jung-Ryul Lee, Joon-Mo Ahn","doi":"10.1080/09243046.2023.2283681","DOIUrl":"https://doi.org/10.1080/09243046.2023.2283681","url":null,"abstract":"Three-dimensional (3D) printing technology has revolutionized the fabrication of complex geometries, including electromagnetic wave absorbers. In this study, the multilayer radar absorbing structur...","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"38 1","pages":""},"PeriodicalIF":2.9,"publicationDate":"2023-11-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138531055","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This study proposes the novel manufacturing method of adhesively bonded joint with double-sided tapes by following the concept of bi-adhesive bondline. The stress concentration at the ends of the b...
本研究以双面胶粘接线为概念，提出了双面胶粘接接头的新制造方法。b末端的应力集中…
{"title":"Toughened single-lap joints by composite bondline of adhesive and double-sided tape","authors":"Kosuke Takahashi, Zhantong Sun, Takuma Kikuzawa, Kounosuke Shimamura, Sourabh Jagrat, Nao Fujimura, Takashi Nakamura","doi":"10.1080/09243046.2023.2284057","DOIUrl":"https://doi.org/10.1080/09243046.2023.2284057","url":null,"abstract":"This study proposes the novel manufacturing method of adhesively bonded joint with double-sided tapes by following the concept of bi-adhesive bondline. The stress concentration at the ends of the b...","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"279 1","pages":""},"PeriodicalIF":2.9,"publicationDate":"2023-11-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138531053","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-11-12DOI: 10.1080/09243046.2023.2279001
Yuta Naito, Christophe Mobuchon, Anoush Poursartip, Masaaki Nishikawa, Masaki Hojo
AbstractTwo types of flow mechanisms consisting of unidirectionally arrayed fibers and uncured thermoset resin exist in prepreg materials. These mechanisms are percolation flow where resin flows out of the gaps between fibers, and shear flow where resin and fibers flow together. Based on our previous study, we assumed that percolation flow is controlled by the rheology of the matrix resin, whereas shear flow is controlled by the rheology of prepreg. Based on this assumption, we experimentally evaluated the ‘multiscale’ solidification (solidification of matrix resin and that of prepreg) process using dynamic mechanical analysis during gelation. The solidification of matrix resin was examined by observing the development of loss angle, which provides a continuous description of the solidification process. On the other hand, the solidification of prepreg was characterized by analyzing the relationship between the shear storage modulus of prepreg and that of the matrix resin. Finally, we examined the difference in the solidification process between prepreg and matrix resin during gelation.Keywords: Thermoset prepregrheological propertiesgelationphase transition;process modeling Disclosure statementNo potential conflict of interest was reported by the author(s).Additional informationFundingThis work was supported by JSPS KAKENHI Grant Number JP17H03144/JP20H02028. This research was partially supported by JSPS KAKENHI 23H01604. This work was supported by Council for Science, Technology and Innovation (CSTI), Cross-ministerial Strategic Innovation Promotion Program (SIP) ‘“Materials Integration” for revolutionary design system of structural materials’ (Funding agency: JST).
{"title":"Experimental characterization of multiscale solidification in thermoset CFRP during gelation for flow and stress modeling","authors":"Yuta Naito, Christophe Mobuchon, Anoush Poursartip, Masaaki Nishikawa, Masaki Hojo","doi":"10.1080/09243046.2023.2279001","DOIUrl":"https://doi.org/10.1080/09243046.2023.2279001","url":null,"abstract":"AbstractTwo types of flow mechanisms consisting of unidirectionally arrayed fibers and uncured thermoset resin exist in prepreg materials. These mechanisms are percolation flow where resin flows out of the gaps between fibers, and shear flow where resin and fibers flow together. Based on our previous study, we assumed that percolation flow is controlled by the rheology of the matrix resin, whereas shear flow is controlled by the rheology of prepreg. Based on this assumption, we experimentally evaluated the ‘multiscale’ solidification (solidification of matrix resin and that of prepreg) process using dynamic mechanical analysis during gelation. The solidification of matrix resin was examined by observing the development of loss angle, which provides a continuous description of the solidification process. On the other hand, the solidification of prepreg was characterized by analyzing the relationship between the shear storage modulus of prepreg and that of the matrix resin. Finally, we examined the difference in the solidification process between prepreg and matrix resin during gelation.Keywords: Thermoset prepregrheological propertiesgelationphase transition;process modeling Disclosure statementNo potential conflict of interest was reported by the author(s).Additional informationFundingThis work was supported by JSPS KAKENHI Grant Number JP17H03144/JP20H02028. This research was partially supported by JSPS KAKENHI 23H01604. This work was supported by Council for Science, Technology and Innovation (CSTI), Cross-ministerial Strategic Innovation Promotion Program (SIP) ‘“Materials Integration” for revolutionary design system of structural materials’ (Funding agency: JST).","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"6 7","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135036684","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
AbstractComposite fan blades made of CFRP have been developed and investigated to reduce the weight of aircraft engines. Aircraft fan blades are subjected to high-speed impact by foreign objects, such as bird strikes. Because CFRP has lower impact resistance than metal materials, it is necessary to focus on possible failure not only at the impact point but also at the tip and trailing edge of the fan blade. This paper developed a finite element analysis model of fan blade geometry and investigated the dynamic deformation that may induce peripheral fracture when a bird strike occurs on a composite fan blade. Natural vibration analysis and transient response analysis were performed to analyze the vibration behavior at the fan blade periphery. The natural vibration analysis showed that the vibration modes in the out-of-plane direction of the blade are of low order. In the transient response analysis, when a group of particles defined by the equation of state and the SPH method collided, a sudden deformation in the periphery, called a whipping motion, was observed immediately after the impact. The spanwise strain has a peak value at the trailing edge of the fan blade, while the chordwise strain has a peak value at the leading edge of the fan blade. Furthermore, the transient response analysis with the fan blades rotating showed an increase in the peak strain value. A comparison of the impact loads and displacements immediately below the impact indicated that the centrifugal force increased the geometric stiffness, which increased the reaction force due to the fan blade, increasing the peak value.Keywords: Finite element method (FEM)LS−DYNAsmoothed particle hydrodynamics method (SPH)natural frequency analysisdynamic transient response analysis Disclosure statementNo potential conflict of interest was reported by the author(s).
{"title":"Whipping motion of airplane composite fan blades due to bird strike","authors":"Sho Kajihara, Ryo Higuchi, Takahira Aoki, Shinya Fukushige","doi":"10.1080/09243046.2023.2280347","DOIUrl":"https://doi.org/10.1080/09243046.2023.2280347","url":null,"abstract":"AbstractComposite fan blades made of CFRP have been developed and investigated to reduce the weight of aircraft engines. Aircraft fan blades are subjected to high-speed impact by foreign objects, such as bird strikes. Because CFRP has lower impact resistance than metal materials, it is necessary to focus on possible failure not only at the impact point but also at the tip and trailing edge of the fan blade. This paper developed a finite element analysis model of fan blade geometry and investigated the dynamic deformation that may induce peripheral fracture when a bird strike occurs on a composite fan blade. Natural vibration analysis and transient response analysis were performed to analyze the vibration behavior at the fan blade periphery. The natural vibration analysis showed that the vibration modes in the out-of-plane direction of the blade are of low order. In the transient response analysis, when a group of particles defined by the equation of state and the SPH method collided, a sudden deformation in the periphery, called a whipping motion, was observed immediately after the impact. The spanwise strain has a peak value at the trailing edge of the fan blade, while the chordwise strain has a peak value at the leading edge of the fan blade. Furthermore, the transient response analysis with the fan blades rotating showed an increase in the peak strain value. A comparison of the impact loads and displacements immediately below the impact indicated that the centrifugal force increased the geometric stiffness, which increased the reaction force due to the fan blade, increasing the peak value.Keywords: Finite element method (FEM)LS−DYNAsmoothed particle hydrodynamics method (SPH)natural frequency analysisdynamic transient response analysis Disclosure statementNo potential conflict of interest was reported by the author(s).","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":" 15","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135240729","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-31DOI: 10.1080/09243046.2023.2274211
Jae Seong Bae, Sung Nam Jung
AbstractA variationally consistent analytical beam model that describes the theory in a Timoshenko-Vlasov level is developed based on Reissner’s mixed variational theorem. Starting from a shell theory, all the field-governing equations (equilibrium and continuity) and the boundary conditions of the shell wall are derived in closed form, and the mixed method enables finding the explicit forms of the reactive stresses and sectional warpings which are evaluated progressively depending on the level of beam model to be analyzed. The stress recovery part is incorporated in the post-stage of the analysis to compute the layer-wise distribution of stresses over the beam cross-section. The present analysis is validated against numerous benchmark examples available in the literature, including beams with multi-layered strip section, thin-walled anisotropic box sections with elastic couplings, and two-cell airfoil section. The comparison study demonstrates excellent correlations with the results from detailed three-dimensional finite element analysis and other up-to-date beam approaches. Also presented are symbolically expressed stiffness coefficients and the sectional warping modes of coupled composite beams to demonstrate the strength of the proposed beam model.Keywords: Beamsection analysiswarpingstress recovery; stiffness matrix Nomenclature a=Local shell radius of curvatureFx=Axial force along x axisFy, Fz=Shear forces along y and z axesMx=Torsional moment about x axisMy, Mz=Bending moments about y and z axesMω=Torsional bi-momentMxx, Mss, Mxs=Bending and twisting couples of the shell wallNxx, Nss, Nxs=In-plane stress resultants of the shell wallNxn, Nsn=Transverse shear stress resultants of the shell wallU, V, W=Translational displacements of beam sectional reference origin along x, y, z axesu, v, w=Translational displacements of an arbitrary material point of beam section along x, y, z axesux, us, un=Translational displacements of the shell wall along x, s, n axesβy, βz=Sectional rotation angles about y and z axesγxn,γsn=Transverse shear strains of the shell wallγxn,γsn=Transverse shear strains of the beam in x-y, x-z planesγxs=In-plane shear strain of the shell wallisinxx,isinss=In-plane normal strains of the shell wallκxx,κss,κxs=Curvatures of the shell wallϕ=Sectional rotation angle about x axisψx, ψs=Rotation angles of the shell wall about s, x axesωx=Contour warping function along x axisSubscripts=(),x, (),s=∂()/∂x, ∂()/∂sSuperscripts=()T=Transpose of an array()−1=Inversion of an arrayDisclosure statementThe authors declare that they have no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.Additional informationFundingThis work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korea government (MSIT) (No. 2022R14A1018884). This work was supported by Korea Research Institute for defense Technology planning and advancement (KRIT) gr
{"title":"Fully analytical solution framework for general thin-walled composite beams with mixed variational approach","authors":"Jae Seong Bae, Sung Nam Jung","doi":"10.1080/09243046.2023.2274211","DOIUrl":"https://doi.org/10.1080/09243046.2023.2274211","url":null,"abstract":"AbstractA variationally consistent analytical beam model that describes the theory in a Timoshenko-Vlasov level is developed based on Reissner’s mixed variational theorem. Starting from a shell theory, all the field-governing equations (equilibrium and continuity) and the boundary conditions of the shell wall are derived in closed form, and the mixed method enables finding the explicit forms of the reactive stresses and sectional warpings which are evaluated progressively depending on the level of beam model to be analyzed. The stress recovery part is incorporated in the post-stage of the analysis to compute the layer-wise distribution of stresses over the beam cross-section. The present analysis is validated against numerous benchmark examples available in the literature, including beams with multi-layered strip section, thin-walled anisotropic box sections with elastic couplings, and two-cell airfoil section. The comparison study demonstrates excellent correlations with the results from detailed three-dimensional finite element analysis and other up-to-date beam approaches. Also presented are symbolically expressed stiffness coefficients and the sectional warping modes of coupled composite beams to demonstrate the strength of the proposed beam model.Keywords: Beamsection analysiswarpingstress recovery; stiffness matrix Nomenclature a=Local shell radius of curvatureFx=Axial force along x axisFy, Fz=Shear forces along y and z axesMx=Torsional moment about x axisMy, Mz=Bending moments about y and z axesMω=Torsional bi-momentMxx, Mss, Mxs=Bending and twisting couples of the shell wallNxx, Nss, Nxs=In-plane stress resultants of the shell wallNxn, Nsn=Transverse shear stress resultants of the shell wallU, V, W=Translational displacements of beam sectional reference origin along x, y, z axesu, v, w=Translational displacements of an arbitrary material point of beam section along x, y, z axesux, us, un=Translational displacements of the shell wall along x, s, n axesβy, βz=Sectional rotation angles about y and z axesγxn,γsn=Transverse shear strains of the shell wallγxn,γsn=Transverse shear strains of the beam in x-y, x-z planesγxs=In-plane shear strain of the shell wallisinxx,isinss=In-plane normal strains of the shell wallκxx,κss,κxs=Curvatures of the shell wallϕ=Sectional rotation angle about x axisψx, ψs=Rotation angles of the shell wall about s, x axesωx=Contour warping function along x axisSubscripts=(),x, (),s=∂()/∂x, ∂()/∂sSuperscripts=()T=Transpose of an array()−1=Inversion of an arrayDisclosure statementThe authors declare that they have no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.Additional informationFundingThis work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korea government (MSIT) (No. 2022R14A1018884). This work was supported by Korea Research Institute for defense Technology planning and advancement (KRIT) gr","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135870318","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-30DOI: 10.1080/09243046.2023.2274203
Dong-Hyeop Kim, Mohammad Amir, Sang-Woo Kim
AbstractThis study presents a comprehensive investigation of the static analysis of a shear-deformable aircraft wing made of functionally graded materials (FGMs). A finite element-based multilayered FGM model is employed for this purpose. In order to ensure the safe structural design of the aircraft wing, it is crucial to analyze the transverse displacement of the wing under various loading conditions. The presented model employs a power-law distribution based on the rule of mixture to derive the effective material properties of the FGM wing. The analysis focuses on three standard FGM aircraft wing profiles, namely NACA 0009, NACA 2424, and NACA 4415, which are representative of commonly used geometries in aircraft design. Additionally, the study explores the effects of volume fraction index, loading conditions, boundary conditions, and aspect ratio on the static analysis of the shear-deformable FGM aircraft wing. These parameters play a significant role in shaping the static behavior of the wings and offer valuable insights into the design of FGM aircraft wings.Keywords: Static analysisFGM aircraft wingmultilayered FGM modelNACA airfoil profilesfinite element analysis AcknowledgementsThis work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korea government (MSIT) (No. 2022R1F1A1069025). This research was supported by Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Education (grant number: 2022R1A6A1A03056784).Disclosure statementNo potential conflict of interest was reported by the authors.Data availability statementThe authors confirm that the data supporting the findings of this study are available within the article.Additional informationFundingThis work was supported by the National Research Foundation of Korea [2022R1F1A1069025]; National Research Foundation of Korea [2022R1A6A1A03056784].
{"title":"Static analysis of shear-deformable aircraft wings using a multilayered functionally graded material model","authors":"Dong-Hyeop Kim, Mohammad Amir, Sang-Woo Kim","doi":"10.1080/09243046.2023.2274203","DOIUrl":"https://doi.org/10.1080/09243046.2023.2274203","url":null,"abstract":"AbstractThis study presents a comprehensive investigation of the static analysis of a shear-deformable aircraft wing made of functionally graded materials (FGMs). A finite element-based multilayered FGM model is employed for this purpose. In order to ensure the safe structural design of the aircraft wing, it is crucial to analyze the transverse displacement of the wing under various loading conditions. The presented model employs a power-law distribution based on the rule of mixture to derive the effective material properties of the FGM wing. The analysis focuses on three standard FGM aircraft wing profiles, namely NACA 0009, NACA 2424, and NACA 4415, which are representative of commonly used geometries in aircraft design. Additionally, the study explores the effects of volume fraction index, loading conditions, boundary conditions, and aspect ratio on the static analysis of the shear-deformable FGM aircraft wing. These parameters play a significant role in shaping the static behavior of the wings and offer valuable insights into the design of FGM aircraft wings.Keywords: Static analysisFGM aircraft wingmultilayered FGM modelNACA airfoil profilesfinite element analysis AcknowledgementsThis work was supported by the National Research Foundation of Korea (NRF) grant funded by the Korea government (MSIT) (No. 2022R1F1A1069025). This research was supported by Basic Science Research Program through the National Research Foundation of Korea (NRF) funded by the Ministry of Education (grant number: 2022R1A6A1A03056784).Disclosure statementNo potential conflict of interest was reported by the authors.Data availability statementThe authors confirm that the data supporting the findings of this study are available within the article.Additional informationFundingThis work was supported by the National Research Foundation of Korea [2022R1F1A1069025]; National Research Foundation of Korea [2022R1A6A1A03056784].","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"624 ","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136068587","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-18DOI: 10.1080/09243046.2023.2269743
Musthafa Akbar, Satoshi Kobayashi
AbstractComposite overwrapped pressure vessels are designed to contain fluids that operate under high pressures. In addition to internal pressure, the design needs to account for out-of-plane loading in the form of low-velocity impact. In this study, a numerical analysis of four models of composite overwrapped pressure vessels with different stacking sequences is performed. A three-dimensional explicit finite element model using multi-layer stacked shell elements was used in the impact zone region to obtain reasonable computation time. Utilizing the bilinear traction-separation law, cohesive zone elements were used to simulate the delamination failure and as bonding between eight layers of CFRP covering the aluminum liner. The simulation results were then validated using drop-weight impact tests, which revealed that the response of contact force to impact time was comparable for both types of analysis. Prediction of failure was carried out by assessing the quantity of energy absorbed by the CFRP layers and was confirmed by shell element data that failed during simulations. In addition, the Hashin damage model confirmed that the matrix tensile failure mode was the predominant failure mode for all discussed impact scenarios. Model-A with Al + [90]8 stacking sequence was found to have the highest impact resistance based on the prediction of the composite’s failure area and the energy absorbed by the CFRP layers. Furthermore, it was found that COPVs with combinations of helical and hoop sequences tend to have larger areas of delamination due to high interlaminar shear stress between the CFRP layers.Keywords: low-velocity impactcohesive zone elements;Hashin damage model impact energy absorption Disclosure statementNo potential conflict of interest was reported by the author(s).
{"title":"Numerical and experimental investigations of low-velocity impact on composite overwrapped pressure vessel with different stacking sequences","authors":"Musthafa Akbar, Satoshi Kobayashi","doi":"10.1080/09243046.2023.2269743","DOIUrl":"https://doi.org/10.1080/09243046.2023.2269743","url":null,"abstract":"AbstractComposite overwrapped pressure vessels are designed to contain fluids that operate under high pressures. In addition to internal pressure, the design needs to account for out-of-plane loading in the form of low-velocity impact. In this study, a numerical analysis of four models of composite overwrapped pressure vessels with different stacking sequences is performed. A three-dimensional explicit finite element model using multi-layer stacked shell elements was used in the impact zone region to obtain reasonable computation time. Utilizing the bilinear traction-separation law, cohesive zone elements were used to simulate the delamination failure and as bonding between eight layers of CFRP covering the aluminum liner. The simulation results were then validated using drop-weight impact tests, which revealed that the response of contact force to impact time was comparable for both types of analysis. Prediction of failure was carried out by assessing the quantity of energy absorbed by the CFRP layers and was confirmed by shell element data that failed during simulations. In addition, the Hashin damage model confirmed that the matrix tensile failure mode was the predominant failure mode for all discussed impact scenarios. Model-A with Al + [90]8 stacking sequence was found to have the highest impact resistance based on the prediction of the composite’s failure area and the energy absorbed by the CFRP layers. Furthermore, it was found that COPVs with combinations of helical and hoop sequences tend to have larger areas of delamination due to high interlaminar shear stress between the CFRP layers.Keywords: low-velocity impactcohesive zone elements;Hashin damage model impact energy absorption Disclosure statementNo potential conflict of interest was reported by the author(s).","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135825144","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-15DOI: 10.1080/09243046.2023.2270379
Muhammad Usama Zaheer, Seung-Hwan Chang
AbstractConventional sensors can detect the various physical and chemical changes that occur during deformation and the states of materials with a high accuracy. However, almost all existing sensors are bulky and stiff, making them highly susceptible to failure when used in large deformation-compliant structures. By contrast, despite their relatively-low resolution and accuracy, the demand for flexible and stretchable sensors used in detecting human motion and vital signs has drastically increased. There are several types of stretchable sensors that contain functional materials such as carbon nanotubes (CNTs). These stretchable sensors have different working principles and applications based on the attributes of their core components. Several electrical signals are used in the measurement of the different physical parameters such as the electrical resistance and capacitance. Triboelectric nanogeneration or voltage signals that can be identified under contact or impact loading conditions are employed in some measurement methods. Additionally, an array of microstructures with a special shape that is directly related to movement and deformation detection, as well as conductive nano-particles that are elaborately aligned along a certain direction for specific sensor applications, are used in the other methods. In this study, a review of the recently-developed high-performance stretchable sensors made from functional materials using new sensing mechanisms for wearable robot applications is provided.Keywords: Stretchable sensorswearable robotsnano-compositesgauge factor Disclosure statementNo potential conflict of interest was reported by the author(s).Additional informationFundingThe work was supported by the Chung-Ang University [2020 Young Scientist Scholarship]; National Research Foundation of Korea [RS-2023-00208286].
{"title":"Recent trend in stretchable composite sensors for wearable robot applications","authors":"Muhammad Usama Zaheer, Seung-Hwan Chang","doi":"10.1080/09243046.2023.2270379","DOIUrl":"https://doi.org/10.1080/09243046.2023.2270379","url":null,"abstract":"AbstractConventional sensors can detect the various physical and chemical changes that occur during deformation and the states of materials with a high accuracy. However, almost all existing sensors are bulky and stiff, making them highly susceptible to failure when used in large deformation-compliant structures. By contrast, despite their relatively-low resolution and accuracy, the demand for flexible and stretchable sensors used in detecting human motion and vital signs has drastically increased. There are several types of stretchable sensors that contain functional materials such as carbon nanotubes (CNTs). These stretchable sensors have different working principles and applications based on the attributes of their core components. Several electrical signals are used in the measurement of the different physical parameters such as the electrical resistance and capacitance. Triboelectric nanogeneration or voltage signals that can be identified under contact or impact loading conditions are employed in some measurement methods. Additionally, an array of microstructures with a special shape that is directly related to movement and deformation detection, as well as conductive nano-particles that are elaborately aligned along a certain direction for specific sensor applications, are used in the other methods. In this study, a review of the recently-developed high-performance stretchable sensors made from functional materials using new sensing mechanisms for wearable robot applications is provided.Keywords: Stretchable sensorswearable robotsnano-compositesgauge factor Disclosure statementNo potential conflict of interest was reported by the author(s).Additional informationFundingThe work was supported by the Chung-Ang University [2020 Young Scientist Scholarship]; National Research Foundation of Korea [RS-2023-00208286].","PeriodicalId":7291,"journal":{"name":"Advanced Composite Materials","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136185386","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-10-12DOI: 10.1080/09243046.2023.2253097
Peter Nyanor, Hossam M. Yehia, Abdollah Bahador, Junko Umeda, Katsuyoshi Kondoh, Mohsen A. Hassan
AbstractTo use Al composites in structural applications, we need to improve strength and ductility at the same time. In this article, we explore three main concepts to solve this problem: improving the dispersion uniformity of CNTs in Al powder without damaging its structure by solution coating technique, fabricating a hybrid composite by reinforcing Al with nano-TiC-CNT, comparing the properties of nano-TiC-CNT and micron-TiC-CNT hybrid composites. Microstructure observation by SEM, TEM, and XRD revealed well-dispersed and preserved CNTs without the formation of a second phase. The Al-0.5CNT composite showed good tensile strength and elongation at break of 278 MPa and 14%, respectively. Further improvements in tensile strength and ductility of 285 MPa and 23%, respectively, were measured after the addition of 2.5 wt%; (1.4 vol%) TiC nanoparticles to Al-0.5CNT composite. However, the introduction of 2.5 wt-% TiC macroparticles only improved the tensile strength by 48% but elongation at break was up to 32%. The improved strength and ductility are attributed to the introduction of geometrical necessary dislocation and Orowan looping of dislocations leading to back stress strengthening. The new Al composite is expected to find application in automotive and aerospace component manufacture and thermal management.Keywords: Aluminium matrix compositestitanium carbide nanoparticlescarbon nanotubes (CNT)strength-ductilitysolution coating process Disclosure statementNo potential conflict of interest was reported by the author(s).
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