Carbon Fiber/Phenolic Composites with High Thermal Conductivity Reinforced by a Three-Dimensional Carbon Fiber Felt Network Structure

Shi, Shanshan; Wang, Ying; Jiang, Tao; Wu, Xinfeng; Zhong, Ning; Sun, Kai; Zhao, Yuantao; Li, Wenge; Yu, Jinhong

doi:10.1021/acsomega.2c03848

Cited by 17 publications

(4 citation statements)

References 64 publications

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“…In addition, some CFs boast a high axial TC of up to 1100 W/(mK) along the axial direction, and their TC is <10 W/(mK) along the radial direction. 28,29 TCPCs with randomly filled CFs do not show promising TC values. It has been reported that the TC of randomly CF-filled (20 wt%) polydimethylsiloxane (PDMS) composites was only 1.3 W/(mK).…”

Section: Introductionmentioning

confidence: 90%

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Modeling thermal conductivity of polymer/carbon fiber composites prepared by SCFNA method

He,

et al. 2023

Polymer Composites

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The spatial confining forced network assembly (SCFNA) has proven to be a promising method for greatly improving the thermal conductivity (TC) of polymer composites via transforming self‐assembled networks into force‐assembled networks in polymer matrices. Most of the models currently in use were derived to predict the TC of polymer composites with self‐assembled networks; however, these are not suitable for predicting the TC of polymer composites with force‐assembled networks. To address this issue, a TC prediction model for polymer/carbon fiber (CF) composites obtained using the SCFNA method was developed. First, a literature TC prediction model, built by abstracting a representative volume element (RVE) from a CF self‐assembled network, was utilized to determine the key parameters related to the CF distance. Thereafter, a modified RVE model was constructed based on the morphological characteristics of the force‐assembled network of CFs. In conjunction with the thermal resistance method, the TC values of the polymer composites were calculated and successfully validated using experimental data obtained by the SCFNA method. In this model, the compression ratio (ε) and a fitting coefficient f were applied to describe the relationship between self‐assembled and force‐assembled networks, and furthermore, the actual filler content in the force‐assembled network was calculated. It was found that as the ε value and filler content increased, f accordingly decreased; however, the calculated actual filler volume content in the force‐assembled network increased. These results possibly reflect the evolution of the CF microstructure obtained by the SCFNA method.Highlights Filler gaps in self‐assembled networks were studied using a literature model. The relationship between self‐assembled and force‐assembled networks was established. A thermal conductivity model of the force‐assembled network was established. The actual filler volume content in the force‐assembled network was calculated.

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Section: Introductionmentioning

confidence: 90%

“…However, CFs have anisotropic TCs. In addition, some CFs boast a high axial TC of up to 1100 W/(mK) along the axial direction, and their TC is <10 W/(mK) along the radial direction 28,29 . TCPCs with randomly filled CFs do not show promising TC values.…”

Section: Introductionmentioning

confidence: 98%

Modeling thermal conductivity of polymer/carbon fiber composites prepared by SCFNA method

He,

et al. 2023

Polymer Composites

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“…Carbon–phenolic materials are not good thermal insulators but act as excellent ablators [ 11 ]. The poor thermal insulation, which is characterized by high thermal conductivity, makes carbon–phenolic materials ideal for improving heat dissipation in electronic components [ 12 ]. On the contrary, for the spacecraft heat shield applications, the thermal insulation provided by carbon–phenolic materials needs to be improved to protect the metallic frame of the spacecraft, as the commonly used high-temperature resistant aluminum alloys begin to lose their strength above 473.15 K (i.e., 200 °C) [ 13 ].…”

Section: Introductionmentioning

confidence: 99%

Arc-Jet Tests of Carbon–Phenolic-Based Ablative Materials for Spacecraft Heat Shield Applications

2023

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We developed and tested two carbon–phenolic-based ablators for future Korean spacecraft heat shield applications. The ablators are developed with two layers: an outer recession layer, fabricated from carbon–phenolic material, and an inner insulating layer, fabricated either from cork or silica–phenolic material. The ablator specimens were tested in a 0.4 MW supersonic arc-jet plasma wind tunnel at heat flux conditions ranging from 6.25 MW/m2 to 9.4 MW/m2, with either specimen being stationary or transient. Stationary tests were conducted for 50 s each as a preliminary investigation, and the transient tests were conducted for ~110 s each to stimulate a spacecraft’s atmospheric re-entry heat flux trajectory. During the tests, each specimen’s internal temperatures were measured at three locations: 25 mm, 35 mm, and 45 mm from the specimen stagnation point. During the stationary tests, a two-color pyrometer was used to measure specimen stagnation-point temperatures. During the preliminary stationary tests, the silica–phenolic-insulated specimen’s reaction was normal compared to the cork-insulated specimen; hence, only the silica–phenolic-insulated specimens were further subjected to the transient tests. During the transient tests, the silica–phenolic-insulated specimens were stable, and the internal temperatures were lower than 450 K (~180 °C), achieving the main objective of this study.

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“…Despite being excellent ablators, carbon-phenolic materials are considered poor thermal insulators [1]. The poor thermal insulation, which is a result of high thermal conductivity, makes carbon-phenolic materials favorable for enhancing heat dissipation in electronic components [16]. However, for spacecraft heat shield applications, the poor thermal insulation of carbon-phenolic materials is unfavorable.…”

Section: Introductionmentioning

confidence: 99%

Thermal Behavior of Carbon-Phenolic/Silica Phenolic Dual-Layer Ablator Specimens through Arc-Jet Tests

Chinnaraj,

Kim,

Choi

2023

Materials

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We studied the behavioral characteristics of a newly developed dual-layer ablator, which uses carbon-phenolic as a recession layer and silica-phenolic as an insulating layer. The ablator specimens were tested in a 0.4 MW supersonic arc-jet plasma wind tunnel, employing two different shapes (flat-faced and hemispherical-faced) and varying thicknesses of the carbon-phenolic recession layer. The specimens underwent two test conditions, namely, stationary tests (7.5 MW/m2, ~40 s) and transient tests simulating an interplanetary spacecraft re-entry heat flux trajectory (6.25↔9.4 MW/m2, ~108 s). During the stationary tests, stagnation point temperatures of the specimens were measured. Additionally, internal temperatures of the specimens were measured at three locations for both stationary and transient tests: inside the carbon-phenolic recession layer, inside the silica-phenolic insulating layer, and at the recession layer–insulating layer intersection. The hemispherical-faced specimen surface temperatures were about 3000 K, which is about 350 K higher than those of flat-faced specimens, resulting in higher internal temperatures. The recession layer internal temperatures rose more exponentially when moved closer to the specimen stagnation point. Layer interaction and insulating layer internal temperatures were found to be dependent on both the recession layer thickness and the exposed surface shape. The change in exposed surface shape increased mass loss and recession, with hemispherical-faced specimens showing ~1.4-fold higher values than the flat-faced specimens.

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Carbon Fiber/Phenolic Composites with High Thermal Conductivity Reinforced by a Three-Dimensional Carbon Fiber Felt Network Structure

Cited by 17 publications

References 64 publications

Modeling thermal conductivity of polymer/carbon fiber composites prepared by SCFNA method

Modeling thermal conductivity of polymer/carbon fiber composites prepared by SCFNA method

Arc-Jet Tests of Carbon–Phenolic-Based Ablative Materials for Spacecraft Heat Shield Applications

Thermal Behavior of Carbon-Phenolic/Silica Phenolic Dual-Layer Ablator Specimens through Arc-Jet Tests

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