Effect of carbon fabric type on the mechanical performance of 2D carbon/carbon composites

1998 ◽  
Vol 19 (5) ◽  
pp. 618-625 ◽  
Author(s):  
Tse-Hao Ko ◽  
Wen-Shyong Kuo
2018 ◽  
Vol 40 (S2) ◽  
pp. E1504-E1511 ◽  
Author(s):  
Gibeop Nam ◽  
Jeachul Kim ◽  
Jung‐Il Song

2022 ◽  
Vol 12 (1) ◽  
Author(s):  
Sanjay Mavinkere Rangappa ◽  
Jyotishkumar Parameswaranpillai ◽  
Suchart Siengchin ◽  
Mohammad Jawaid ◽  
Togay Ozbakkaloglu

AbstractIn this work, fillers of waste chicken feather and abundantly available lignocellulose Ceiba Pentandra bark fibers were used as reinforcement with Biopoxy matrix to produce the sustainable composites. The aim of this work was to evaluate the mechanical, thermal, dimensional stability, and morphological performance of waste chicken feather fiber/Ceiba Pentandra bark fiber filler as potential reinforcement in carbon fabric-layered bioepoxy hybrid composites intended for engineering applications. These composites were prepared by a simple, low cost and user-friendly fabrication methods. The mechanical (tensile, flexural, impact, hardness), dimensional stability, thermal stability, and morphological properties of composites were characterized. The Ceiba Pentandra bark fiber filler-reinforced carbon fabric-layered bioepoxy hybrid composites display better mechanical performance compared to chicken feather fiber/Ceiba Pentandra bark fiber reinforced carbon fabrics layered bioepoxy hybrid composites. The Scanning electron micrographs indicated that the composites exhibited good adhesion at the interface of the reinforcement material and matrix system. The thermogravimetric studies revealed that the composites possess multiple degradation steps, however, they are stable up to 300 °C. The thermos-mechanical studies showed good dimensional stability of the composites. Both studied composites display better thermal and mechanical performance compared to neat bioepoxy or non-bioepoxy thermosets and are suitable for semi-structural applications.


Materials ◽  
2020 ◽  
Vol 13 (2) ◽  
pp. 256 ◽  
Author(s):  
Feng Xu ◽  
Shizhen Zhu ◽  
Jingdan Hu ◽  
Zhuang Ma ◽  
Yanbo Liu

Carbon fabric reinforced phenolic composites were widely used as TPSs (thermal protection system) material in the aerospace industry. However, their limited oxidative ablation resistance restricted their further utility in more serious service conditions. In this study, the surface-decorated ZrB2/SiC and its modified carbon fabric reinforced phenolic composites have been successfully prepared. The self-modification mechanism of the surface-decorated ZrB2/SiC particles were characterized. The mechanical performance and ablation behavior of the composites were investigated. Results showed that the ZrB2/SiC particles possessed a good surface-decorated effect, which achieved good compatibility with the phenolic resin. The mechanical performance of the modified phenolic composite was effectively improved. The anti-oxidative ablation performance of the composite was improved. The mass ablation rate of the surface-decorated ZrB2–SiC-modified carbon fabric reinforced phenolic composites was 25% lower than that of the unmodified composites. The formed ZrO2 ceramic layer attached to the surface of the residual chars prevented the heat energy and oxygen from the inner material. Meanwhile, the volatilization of SiO2 and B2O3 effectively increased the heat dissipation. All these results confirmed that the ZrB2–SiC particles can effectively improve the ablation resistance of the composite, which provided a basis for the application of the composites to more serious service environments.


2015 ◽  
Vol 28 (5) ◽  
pp. 285-290
Author(s):  
Hyun-Wook Park ◽  
Mi-Young Park ◽  
Chun-Gon Kim ◽  
Soo-Hyun Kim

Aerospace ◽  
2021 ◽  
Vol 8 (4) ◽  
pp. 105
Author(s):  
Mauricio Torres-Arellano ◽  
Manuel de Jesus Bolom-Martínez ◽  
Edgar Adrian Franco-Urquiza ◽  
Ruben Pérez-Mora ◽  
Omar A. Jiménez-Arévalo ◽  
...  

This research aimed to determine riveted carbon/epoxy composites’ mechanical performance when fabricated by resin transfer molding (RTM). As this manufacturing process is gaining importance in the aeronautics and automotive industries, assembly methods and their reliability must be studied in terms of their airworthiness and transportation implementation. The study case resumes the determination of the bearing strength of RTM-woven carbon composites for different rivet joint diameters (1/8, 5/32 and 3/16 in). The joint shear strength was obtained following the ASTM D5961 instructions, and post-failure analysis was carried out by a computerized tomography scan. A residual strength curve is provided with the results to infer the bearing strength for the riveted composites as a function of the rivet width-to-diameter ratio. A discussion of the fracture mechanism and tensile strength is carried out to assess the understanding of the riveted woven composites.


2016 ◽  
Vol 50 (23) ◽  
pp. 3239-3254
Author(s):  
Biswanath Jana ◽  
KV Rajulapati ◽  
N Eswara Prasad ◽  
RK Jain ◽  
K Bhanu Sankara Rao

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