Investigation of carbon fiber composite stiffened skin with vacuum assisted resin infusion/prepreg co-curing process

Ma, Xiaofeng; Gu, Yi; Li, Min; Li, Yanxia; Zhang, Zuoguang

doi:10.1007/s11431-014-5660-8

Cited by 11 publications

(7 citation statements)

References 16 publications

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“…It is noted that value of reduced modulus of resin matrix is far smaller than that of carbon fiber. 15,18 Moreover, the absolute reduced modulus of resin matrix is susceptible to the local roughness of sample surface for different locations. Therefore, the reduced modulus value of injection resin is selected as benchmark and the ratios of reduced modulus for other indentions are listed in Table 1.…”

Section: Resultsmentioning

confidence: 99%

“…stringer stiffened panel and spars, have been successfully fabricated by co-LCM processes with significant cost reduction. [7][8][9][10][11][12][13][14][15] Fratta et al 11 investigated the co-VARI process, applying out-of-autoclave (OoA) prepreg stack and dry fiber preform with various processing conditions. The results showed that co-VARI process was a potential alternative to sole prepreg process and VARI process due to the satisfactory mechanical properties and cost-effective saving.…”

Section: Introductionmentioning

confidence: 99%

“…stringer stiffened panel and spars, have been successfully fabricated by co-LCM processes with significant cost reduction. 7–15 Fratta et al. 11 investigated the co-VARI process, applying out-of-autoclave (OoA) prepreg stack and dry fiber preform with various processing conditions.…”

Section: Introductionmentioning

confidence: 99%

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Interlaminar properties of carbon fiber composite laminates with resin transfer molding/prepreg co-curing process

et al. 2014

Journal of Reinforced Plastics and Composites

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Co-cured resin transfer molding (co-RTM) process, which combined resin transfer molding (RTM) process with prepreg process, was adopted to fabricate carbon fiber/epoxy resin laminates. The compatibility between prepreg resin and injection resin was investigated by nano-indention test and glass transition temperature with different resin mixture ratios. Processing quality of co-RTM laminates was evaluated by optical micrographs and thickness dimension. Mode I (G IC ) and mode II (G IIC ) interlaminar fracture toughness tests were measured to characterize the mechanical properties of co-cured interface. Moreover, prepreg resin impregnation into fiber fabric was studied by fluorescent micrographs and its influences on processing quality and interlaminar property were analyzed. The results show that good resin compatibility can be obtained between two resin systems. There are no obvious defects except for some resin rich region at co-cured interface for co-RTM laminates. The G IC and G IIC test values of co-RTM laminates locate between those of prepreg laminates and RTM laminates, which exhibit no weak effect occurs at co-cured interface. In addition, increasing holding temperature and prolonging holding time promote prepreg resin impregnation effect, improving the fiber compaction and interlaminar performances at co-cured interface. Therefore, co-RTM process is a hopeful technique for manufacturing composite structure with effective cost saving.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Interlaminar properties of carbon fiber composite laminates with resin transfer molding/prepreg co-curing process

et al. 2014

Journal of Reinforced Plastics and Composites

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“…So far, a variety of composite manufacturing techniques such as autoclave prepreg molding, 6–12 resin transfer molding (RTM), 13,14 resin film infusion, 15,16 vacuum assisted resin transfer molding (VARTM), 17–19 or the combination of thereof (combined wet winding/prepreg, 20 combined prepreg/RTM, 21 combined out-of-autoclave prepreg/VARTM 22,23 ) have been employed to integrally cure structures. Amongst the various methods, VARTM is the most cost-effective technique that requires neither autoclave nor prepreg and offers a great advantage to fabricate very large parts using inexpensive tooling.…”

Section: Introductionmentioning

confidence: 99%

Co-cured manufacturing of multi-cell composite box beam using vacuum assisted resin transfer molding

Akin

Oztan

Akin

et al. 2021

Journal of Composite Materials

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Co-curing holds great promise to minimize assembly weight, time, and cost for stiffened aerospace structures, which are conventionally fabricated separately and then integrated either through mechanical fastening or adhesive bonding—also known as secondary bonding. This study presented a low-cost co-curing process using VARTM to fabricate stiffened shells, particularly composite box beams. The experimental investigation was performed and the co-curing process was improved by scrutinizing the critical process parameters, such as foam strength and coating, and curing cycle. This work was also intended to present the demonstration of the proposed co-curing method and its comparison with the conventional secondary bonding technique for three-cell carbon fiber-reinforced polymer (CFRP) composite box beams. Fiber volume fraction measurements were carried out to the specimens extracted from the various section of the co-cured part, namely top skin, web, and bottom skin and as a result, around 60% of fiber volume fraction was measured, which was in good agreement with the results obtained from optical microscopy-based image analysis. Structural-level four-point bending test results showed that the weight normalized maximum and the ultimate load of the part increased by 44% and 45% with the use of the co-curing process, respectively. The improved mechanical properties indicated that stronger structural integration can be achieved by integrally curing structures. SEM micrographs revealed a favorable fiber-matrix interface, bolstering the superior integration of the co-cured part. These findings suggest that the low-cost co-curing process can be a potential candidate for the fabrication of stiffened aerospace structures, such as composite box beams.

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“…1 As one of the typical integrated assemblies, the T-stiffened skin assembly has attracted much attention. 2–6…”

Section: Introductionmentioning

confidence: 99%

Size sensitivity of residual stress and deformation in co-curing process of T-stiffened composite skin assembly

Zhongli

Wang

et al. 2019

Journal of Reinforced Plastics and Composites

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The stiffener plays an important role in the overall performance of T-stiffened skin assembly which is a primary structure of aircraft. In this paper, a thermo-viscoelastic finite element model that has been verified by experimental results was established to investigate the effect of the stiffener on stress concentration, stress redistribution, and deformation of T-stiffened skin assembly during curing. The size dependence of residual stress and deformation was analyzed by establishing a series of integrated assemblies with different sizes and stacking sequences of the stiffener. The sensitivity of residual stress and deformation to the stiffener size and stacking sequence was investigated. The results reveal that the overall residual stress of T-stiffened skin assembly is mainly sensitive to the fillet radius and the stacking sequence, whereas the residual stress of skin is almost not sensitive to the stiffener size. The maximum deformation of T-stiffened skin assembly is located in the skin, and the evolution of the maximum deformation is significantly affected by the flange length and stacking sequence.

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Investigation of carbon fiber composite stiffened skin with vacuum assisted resin infusion/prepreg co-curing process

Cited by 11 publications

References 16 publications

Interlaminar properties of carbon fiber composite laminates with resin transfer molding/prepreg co-curing process

Interlaminar properties of carbon fiber composite laminates with resin transfer molding/prepreg co-curing process

Co-cured manufacturing of multi-cell composite box beam using vacuum assisted resin transfer molding

Size sensitivity of residual stress and deformation in co-curing process of T-stiffened composite skin assembly

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