Applied Composite Materials最新文献

Experimental and Numerical Study of Damage Performance and Sensitivity of Thin-Walled Carbon Fiber Tubes to Low-Energy Transverse Impact

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-30 DOI: 10.1007/s10443-024-10290-5

Zhong Luo, Xinyu Sun, Bing Yu, Chengshuang Zhang

引用次数: 0

Failure Analysis of Glass/Epoxy Composite Subjected to Different In-Plane Biaxial Loading Conditions 玻璃/环氧树脂复合材料在不同平面内双轴载荷条件下的失效分析

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-27 DOI: 10.1007/s10443-024-10297-y

A. Kobeissi, P. Rahme, L. Leotoing, D. Guines

{"title":"Failure Analysis of Glass/Epoxy Composite Subjected to Different In-Plane Biaxial Loading Conditions","authors":"A. Kobeissi, P. Rahme, L. Leotoing, D. Guines","doi":"10.1007/s10443-024-10297-y","DOIUrl":"10.1007/s10443-024-10297-y","url":null,"abstract":"<div><p>In recent years, several studies have been initiated to comprehend and predict the failure mechanisms of composite materials. The principal objective of these investigations is to develop a robust failure theory capable of accurately predicting the behavior of composite materials under various loading conditions. The absence of a reliable failure theory capable of effectively predicting composite failure under multi-axial loading makes this area of research particularly promising. Numerous investigations have been carried out to characterize the behavior of composite materials under diverse multi-axial loading conditions. These studies involve the generation of failure envelopes and subsequent comparisons with various failure theories. In this specific study, the traction/traction quadrant of the experimental failure envelope for a 0.5 mm thick plain-weave glass/epoxy composite is generated. Biaxial tests on cruciform specimens are conducted to obtain failure stresses under different loading conditions. The failure investigation validates the capability of the original composite cruciform specimen combined with aluminum tabs for accurately assessing the biaxial failure of composites. Subsequently, the experimental failure envelope is compared with various interactive and non-interactive failure criteria. Notably, the Tsai-Hill and Norris Distortional Energy theories demonstrate substantial agreement with the experimental results.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"525 - 542"},"PeriodicalIF":2.3,"publicationDate":"2024-12-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778072","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Failure Analysis and Process Optimization in Hydroforming of Fiber Metal Laminates: An Experimental and Numerical Investigation 金属纤维层压板水压成型中的失效分析和工艺优化：实验与数值研究

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-26 DOI: 10.1007/s10443-024-10299-w

Cheng Gang, Hamza Blala, Cheng Pengzhi, Zhang Shenglun, Ruan Shangwen, Meng Zhang

{"title":"Failure Analysis and Process Optimization in Hydroforming of Fiber Metal Laminates: An Experimental and Numerical Investigation","authors":"Cheng Gang, Hamza Blala, Cheng Pengzhi, Zhang Shenglun, Ruan Shangwen, Meng Zhang","doi":"10.1007/s10443-024-10299-w","DOIUrl":"10.1007/s10443-024-10299-w","url":null,"abstract":"<div><p>This paper explores the application of active hydroforming for Fiber Metal Laminates (FMLs) in aircraft fairing components, in response to the aerospace industry's growing demand for lightweight yet robust materials. Despite the significant potential of FMLs, their complex structure presents major challenges in forming processes. This study investigates the effects of critical parameters, including Bulging Pressure (B<sub>P</sub>) and Blank Holder Pressure (B<sub>HP</sub>), on FML thickness reduction, surface quality, and filling rate. Simulations were conducted using Abaqus, while Hashin's theory was applied to predict damage initiation in the fiber layers. The results revealed a significant interaction between B<sub>P</sub> and B<sub>HP</sub>, which must be carefully managed to avoid defects. A bulging pressure between 1.2 and 2.4 MPa produced well-formed FML parts without defects, although the deformation was insufficient to achieve full die cavity filling and shape accuracy. The minimum required liquid pressure was derived from the FML's ultimate tensile strength, thickness, and sample radius. Finally, a novel active hydroforming curve was introduced, leading to complete FML filling. This research addresses critical forming challenges and demonstrates the feasibility of transitioning from traditional aluminum or composite fairings to advanced FML components in aerospace applications, paving the way for broader adoption.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"733 - 761"},"PeriodicalIF":2.3,"publicationDate":"2024-12-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778074","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Micro-Scale Orthogonal Cutting of CFRP/AFRP Laminates: Modeling and Experimental Analysis CFRP/AFRP 层压板的微尺度正交切割：建模与实验分析

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-20 DOI: 10.1007/s10443-024-10288-z

Huan Chen, Hualin Zheng, Xinman Yuan, Guixin Wang

{"title":"Micro-Scale Orthogonal Cutting of CFRP/AFRP Laminates: Modeling and Experimental Analysis","authors":"Huan Chen, Hualin Zheng, Xinman Yuan, Guixin Wang","doi":"10.1007/s10443-024-10288-z","DOIUrl":"10.1007/s10443-024-10288-z","url":null,"abstract":"<div><p>With the ongoing advancement of composite materials, CFRP/AFRP laminates, which integrate the benefits of carbon fiber-reinforced polymer (CFRP) and aramid fiber-reinforced polymer (AFRP), have become increasingly utilized in aerospace applications. The distinct material properties of carbon fibers and aramid fibers result in differing fracture and damage mechanisms during machining. Thus, understanding the cutting and damage mechanisms of CFRP/AFRP composites is crucial to achieving high-quality machined surfaces. In this study, a micro-scale orthogonal cutting finite element model (FEM) is developed for CFRP/AFRP laminates, and corresponding orthogonal cutting experiments are conducted. The cutting process and damage formation mechanisms are analyzed for four typical fiber cutting angles from a microscopic perspective. The findings reveal that carbon fibers, due to their brittleness, primarily undergo shear and bending fractures, while aramid fibers, exhibiting higher ductility, predominantly experience shear and tensile fractures. The surface quality of CFRP/AFRP laminates declines as the fiber cutting angle increases. The cutting force initially rises and then declines as the fiber angle increases, peaking at a 90° fiber cutting angle. The simulated cutting process and cutting forces correspond well with experimental results. Additionally, subsurface damage is assessed, showing that it increases with cutting depth and decreases with cutting speed, stabilizing at higher cutting speeds.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"763 - 790"},"PeriodicalIF":2.3,"publicationDate":"2024-12-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778075","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Fatigue Damage Evolution Model of Ceramic Matrix Composites Structures Based on Hysteresis loss Energy and life Prediction at Elevated Temperatures

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-14 DOI: 10.1007/s10443-024-10295-0

Sheng Zhang, Tong Wang, Chengqian Dong, Xiaoqiang Liang, Xiguang Gao, Yingdong Song, Fang Wang

{"title":"Fatigue Damage Evolution Model of Ceramic Matrix Composites Structures Based on Hysteresis loss Energy and life Prediction at Elevated Temperatures","authors":"Sheng Zhang, Tong Wang, Chengqian Dong, Xiaoqiang Liang, Xiguang Gao, Yingdong Song, Fang Wang","doi":"10.1007/s10443-024-10295-0","DOIUrl":"10.1007/s10443-024-10295-0","url":null,"abstract":"<div><p>Due to the multiple damage modes and the variable amplitude cyclic loading, fatigue life prediction for ceramic matrix composites structures is still a challenge. In the present study, to measure the fatigue damage degree, the accumulated hysteresis loss energy was used. A linear function is used to describe the growth law of accumulated hysteresis loss energy with the number of cycles. The growth rate of the accumulated hysteresis loss energy is positively associated with the temperature. A unified equation was then developed to describe the degradation of the residual modulus. To describe the fatigue damage evolution under variable amplitude cyclic loading, the concept of the equivalent number of cycles was proposed. Based on the developed fatigue damage evolution model, the fatigue life of a SiC/SiC dovetail was predicted. Experimental validation revealed that the damage evolution model developed in the present work, which is based on hysteresis loss energy, can effectively predict the fatigue life of ceramic matrix composite structures, and the maximum deviation is less than 20% from the experimental results.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"599 - 623"},"PeriodicalIF":2.3,"publicationDate":"2024-12-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778076","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Fatigue Characterization of Composite Laminates with Interface Hybrid Toughening Using a Single-Step Joint Configuration 使用单步接合配置对界面混合增韧复合材料层压板进行疲劳表征

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-12 DOI: 10.1007/s10443-024-10292-3

Sheng Wang, Oğuzcan İnal, Kali Babu Katnam, Zhenmin Zou, Prasad Potluri, Constantinos Soutis

{"title":"Fatigue Characterization of Composite Laminates with Interface Hybrid Toughening Using a Single-Step Joint Configuration","authors":"Sheng Wang, Oğuzcan İnal, Kali Babu Katnam, Zhenmin Zou, Prasad Potluri, Constantinos Soutis","doi":"10.1007/s10443-024-10292-3","DOIUrl":"10.1007/s10443-024-10292-3","url":null,"abstract":"<div><p>This study investigates the effect of interface hybrid toughening on the fatigue performance of composite laminates by examining a single-step joint configuration with a bondline incorporating core-shell rubber (CSR) nanoparticles and thermoplastic micro-fiber polyphenylene sulfide (PPS) veils. Three types of bondlines for the single-step joint configuration are produced by resin infusion process: untoughened (i.e. Baseline), single-material toughened (i.e. 10 wt% CSR nanoparticles or 20 g/m<sup>2</sup> PPS veils) and hybrid toughened (i.e. 10 wt% CSR particles and 20 g/m<sup>2</sup> PPS veils). High-cycle tension fatigue tests with zero load ratio (i.e. <i>R</i> = 0) are conducted. Backface strain measurements and two-dimensional digital image correlation (2D DIC) are employed to evaluate the initiation and propagation of the crack developed at the untoughened and toughened bondlines. The results show that the hybrid interface toughening method increases the fatigue life (i.e. by ∼49% at low load level and ∼278% at high load level) and reduces crack growth rate, outperforming the untoughened as well as non-hybrid toughened fracture resistance.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"355 - 372"},"PeriodicalIF":2.3,"publicationDate":"2024-12-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s10443-024-10292-3.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778049","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Influence of Fibre Stacking Sequence on Impact Resistance and Residual Strength in Flax/Basalt Hybrid Laminates

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-11 DOI: 10.1007/s10443-024-10294-1

Muhammad Mughees Abbas Dogar, Aamir Mubashar, Manzar Masud, Usman Ayub, Saqib Anwar, Xianwei Wang

{"title":"Influence of Fibre Stacking Sequence on Impact Resistance and Residual Strength in Flax/Basalt Hybrid Laminates","authors":"Muhammad Mughees Abbas Dogar, Aamir Mubashar, Manzar Masud, Usman Ayub, Saqib Anwar, Xianwei Wang","doi":"10.1007/s10443-024-10294-1","DOIUrl":"10.1007/s10443-024-10294-1","url":null,"abstract":"<div><p>This study investigates the effects of different fibre stacking configurations on the low-velocity impact (LVI) resistance and compression after impact (CAI) behaviour of hybrid laminates reinforced with flax and basalt fibres. Five types of laminates with different stacking sequences were manufactured using twill weave basalt and flax fibre fabrics, resulting in laminates with 15 layers each. The configurations included symmetric, asymmetric, and sandwich-type laminates with varying the distribution of flax and basalt fibre layers. The laminates were subjected to drop-weight impact tests at energy levels of 30 J, 45 J, and 60 J to evaluate their impact resistance. Post-impact, CAI tests were conducted according to ASTM standards to assess the residual compressive strength. Furthermore, both quantitative and qualitative analysis of results were conducted to investigate the effect of variations in stacking sequences. The experimental results showed that the placement of flax fibre layers significantly influences both the impact performance and residual strength of the hybrid laminates. The results revealed that the symmetric laminate having an alternating arrangement of flax and basalt fibres through its thickness, exhibited superior impact resistance and the highest residual compressive strength across all energy levels. Furthermore, different types of damage mechanisms were also observed depending on the variation in stacking sequences and impact energies, which include the damage the permanent indentation, matrix cracking, fibre pull-out, and delamination. At lower impact energies, all laminates primarily exhibited surface indentations and matrix cracking without perforation.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"681 - 702"},"PeriodicalIF":2.3,"publicationDate":"2024-12-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778081","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Design Optimization for Hydrostatic Pressure in Hybrid Composite Cylinders

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-10 DOI: 10.1007/s10443-024-10293-2

Akongnwi Nfor Ngwa, Birendra Chaudhary, Helio Matos, Arun Shukla

{"title":"Design Optimization for Hydrostatic Pressure in Hybrid Composite Cylinders","authors":"Akongnwi Nfor Ngwa, Birendra Chaudhary, Helio Matos, Arun Shukla","doi":"10.1007/s10443-024-10293-2","DOIUrl":"10.1007/s10443-024-10293-2","url":null,"abstract":"<div><p>This study explores an optimization system to achieve the highest collapse pressure on glass-carbon hybrid composite cylinders under hydrostatic loading conditions. This work evaluates and validates previously established composite buckling solutions for cylindrical composite structures under hydrostatic pressure with experimental results of hybrid composite shells. It utilizes the validated analytical solution to optimize the buckling pressure by varying layup configuration, optimum layup angle, material content, and thickness of each lamina. The optimization is performed on asymmetric and symmetric layup cases to evaluate the influence of the hybrid layup construction on the buckling performance of the structure. Results show that the thicker glass fiber plies are preferred for inner layers and the stiffer carbon fiber plies for the outermost layers to achieve maximum buckling collapse pressure for all the optimization cases, as this configuration provides superior flexural rigidity. For hybrid composite structures with asymmetric configurations, the collapse pressure can be higher when most layers are made of glass fiber if the glass layers are at least twice as thick as the carbon layers. Similarly, axial-load-resistant layers (0°) should be located around the geometric center of the laminate with the hoop-load-resistant layers (90°) on or near the outermost layers and shear-resistant layers (45°) between these layers for both symmetric and asymmetric hybrid structures. Moreover, long tubes with small diameters (L/D > 10) favor hoop bending stiffnesses (90°) for all layers in the laminate due to less influence of boundary conditions at endcap locations.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"373 - 394"},"PeriodicalIF":2.3,"publicationDate":"2024-12-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s10443-024-10293-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778002","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

The Influence of Trigger Angle Structure on the Energy Absorption Capabilities of Aluminum Alloy/Thermoplastic Reinforced Polypropylene Hybrid Tubes 扳机角度结构对铝合金/热塑性增强聚丙烯混合管能量吸收能力的影响

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-06 DOI: 10.1007/s10443-024-10289-y

Xiang Siyi, Li Huaguan, Sun Xianglong, Zhou Rui, Liu Wenyi, Lin Yanyan

{"title":"The Influence of Trigger Angle Structure on the Energy Absorption Capabilities of Aluminum Alloy/Thermoplastic Reinforced Polypropylene Hybrid Tubes","authors":"Xiang Siyi, Li Huaguan, Sun Xianglong, Zhou Rui, Liu Wenyi, Lin Yanyan","doi":"10.1007/s10443-024-10289-y","DOIUrl":"10.1007/s10443-024-10289-y","url":null,"abstract":"<div><p>Fiber/metal hybrid tubes are significantly lighter and offer better energy absorption properties than traditional pure metal or fiber tubes, they are prone to instability and local buckling under multi-angle extrusion. The article describes the development of aluminum alloy (Al)/thermoplastic reinforced polypropylene (CFPP) hybrid tubes with different trigger angles through the finite element simulation and test combined research method. For various trigger angle configurations, the effects of axial and multi-angle loading on damage and energy absorption properties are examined. The introduction of a trigger angle enables progressive load distribution, with the inner aluminum alloy layer and CFPP layer making initial contact and being quickly destroyed, effectively reducing the initial peak load. A well-designed trigger angle length facilitates the gradual failure of the entire structure. When the trigger angle is 45°, load distribution is more even, resulting in better energy absorption performance. Under multi-angle conditions, composite tubes, whether with or without a trigger angle, tend to become unstable. However, the 45° trigger angle helps mitigate the instability, promoting progressive failure and ensuring stable energy absorption performance.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"625 - 637"},"PeriodicalIF":2.3,"publicationDate":"2024-12-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778077","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Advances and Future Prospects of Adhesive Bonding and Co-Consolidation Technologies for Aviation Carbon Fiber Thermoplastic Composites 航空碳纤维热塑性复合材料粘合剂粘接和共固化技术的进展与未来展望

IF 2.3 4区材料科学

Applied Composite Materials Pub Date : 2024-12-05 DOI: 10.1007/s10443-024-10291-4

Jiaming Liu, Dong Quan, Xi Yang, Chuanjian Zhou, Guoqun Zhao

{"title":"Advances and Future Prospects of Adhesive Bonding and Co-Consolidation Technologies for Aviation Carbon Fiber Thermoplastic Composites","authors":"Jiaming Liu, Dong Quan, Xi Yang, Chuanjian Zhou, Guoqun Zhao","doi":"10.1007/s10443-024-10291-4","DOIUrl":"10.1007/s10443-024-10291-4","url":null,"abstract":"<div><p>Driven by the growing demand for light-weight and high-strength structures, the application of thermoplastic composites (TPCs) has significantly increased in the last several decades, benefiting from their excellent specific strength and stiffness, damage resistance and thermal stability, etc. With the rapidly increased demand of TPC components in aviation fields, develop advanced light-weight joining technologies for TPCs becomes critical. In the present study, the light-weight adhesive bonding and co-consolidation techniques for TPCs are particularly focused on and comprehensively reviewed. Nevertheless, there are still severe challenges for high-quality adhesive and co-consolidated TPC joints. In this paper, the types of surface treatment, adhesive bonding and co-consolidation technologies for TPCs were charactered systematically. In addition to that, the TPC joining strength for various joining technologies has been summarized and analyzed. Furthermore, the future development trends for adhesive bonding and co-consolidation technologies of TPCs were also proposed.</p></div>","PeriodicalId":468,"journal":{"name":"Applied Composite Materials","volume":"32 2","pages":"415 - 430"},"PeriodicalIF":2.3,"publicationDate":"2024-12-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143778004","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"材料科学","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0