Evaluation System for Ablative Material in a High-Temperature Torch

Lee, Sanghoon; Park, Gisu; Kim, Jae Gang; Paik, Jong Gyu

doi:10.1007/s42405-019-00185-2

Cited by 21 publications

(3 citation statements)

References 74 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…These factors are extrinsic elements impacting ablation mechanisms. Numerical simulation and evaluation system can also be established for diagnosing the flame during ablation [ 33 ].…”

Section: Preparation Of C/si-based Compositesmentioning

confidence: 99%

Advances in Ablation or Oxidation Mechanisms and Behaviors of Carbon Fiber-Reinforced Si-Based Composites

et al. 2023

View full text Add to dashboard Cite

Composites with excellent thermomechanical and thermochemical properties are urgently needed in the aerospace field, especially for structural applications under high-temperature conditions. Carbon fiber-reinforced Si-based composites are considered the most promising potential high-temperature materials due to their excellent oxidation resistance and ablative behaviors, good structural designability, and excellent mechanical properties. The reinforcement of the relevant composites mainly involves carbon fiber, which possesses good mechanical and temperature resistance abilities. In this paper, the ablation behaviors and mechanisms of related composites are reviewed. For carbon fiber-reinforced pure Si-based composites (C/SiM composites), the anti-ablation mechanism is mainly attributed to the continuous glassy SiO2, which inhibits the damage of the substrate. For C/SiM composite doping with refractory metal compounds, the oxides of Si and refractory metal together protect the main substrate from ablation and oxidation. Moreover, in addition to thermochemical damage, thermophysical and thermomechanical behavior severely destroy the surface coating of the substrate.

show abstract

“…These factors are extrinsic elements impacting ablation mechanisms. Numerical simulation and evaluation system can also be established for diagnosing the flame during ablation [ 33 ].…”

Section: Preparation Of C/si-based Compositesmentioning

confidence: 99%

Advances in Ablation or Oxidation Mechanisms and Behaviors of Carbon Fiber-Reinforced Si-Based Composites

et al. 2023

View full text Add to dashboard Cite

show abstract

“…Due to the heterogeneous nature of the CCCM oxidation process, one of the main parameters determining its rate is the value boundary of the phase interface through which mass transfer proceeds (Kamyar et al, 2019;Lee et al, 2019). The complex influence of phase boundary consists of the fact that its only active part, the proportion of which varies with time, is involved in the process of low-temperature oxidation.…”

Section: Despitementioning

confidence: 99%

CCCM Specific Surface Estimation in Process of Low-Temperature Oxidation

Pogodin¹,

Астапов²,

Rabinskiy³

2020

PTQ

View full text Add to dashboard Cite

The low-temperature oxidation process of carbon-carbon composite materials (CCCM) with a pyrocarbon matrix has been examined. Oxidation at temperatures of 450 to 700 °C is characterized by internal burnout of the carbon phase without a noticeable change in the experimental samples external volume. Oxidation resistance analysis of CCCM structural components was performed. CCCM and carbon fibers specific surface area were estimated by the low-temperature adsorption of nitrogen and krypton using the Brunauer-Emmett-Teller model and the theory of density functional model. Pore size distribution was calculated by the semi-empirical Horvath-Kawazoe method. A significant increase (about 10-15 times) in specific surface area of the composite material, together with a rise in free volume ~5%, was accompanied by total weight loss of about 5%. Specific surface area changes occur as a result of anisotropic etching of carbon fibers surface with the formation of micropores with 0.5–2.0 nm diameter range. Although macropores are formed mainly due to the oxidation of thermosetting binder pyrolysis residue, they do not contribute to the specific surface increase but solely provide access to micropores. Microporosity evolution leads to an increase of structural discontinuity degree and, ultimately, to the loss of matrix-filler contact boundary. As a result, an overall weakening of material mechanical characteristics is to be noted. Thus, oxidative degradation is closely related to the increase in void space. A follow-up study is on-going. In fact, an open question remains, namely whether the oxidative process occurs differently in the micropores of diameter less than 2 nm and how it may contribute to the oxidative stress resistance behavior of CCCM.

show abstract

“…Thermal protection system is one of the most critical technologies for guaranteeing the safe service of aerospace vehicles in extreme environments (Chen et al, 2017;Qian et al, 2016;Meng et al, 2016). The ablative composites have been used for a variety of aerospace applications as thermal protection materials (Lee et al, 2019;Li et al, 2019). When heat flux is imposed on the ablative composites' surfaces, they undergo physicochemical changes such as decomposition, melting and sublimation, which will take away a large amount of heat, the purpose of preventing excessive heat flux from entering the internal structure of aircraft to ensure safety is achieved (Chen et al, 2017;Li and Huang, 2015;Rivier et al, 2019;Stern et al, 2019).…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of ablative behavior of silicone resin coated carbon fabric

Zheng

Zhi

Mao

et al. 2020

PRT

View full text Add to dashboard Cite

Purpose The purpose of this paper is to study the ablative behavior of the silicone resin-coated carbon fabric (coated fabric) that will swell significantly during ablation. Design/methodology/approach The ablation experiments of three coated fabrics were conducted by quartz lamp radiant. Based on the experimental analysis, a numerical model was proposed for the coated fabrics to study the ablative process in term of the energy balance, mass conservation and thermal decomposition equations. Findings Results showed that the average relative errors between the simulated temperatures and experimental values of back surfaces of coated fabric 1, 2 and 3 were 10.01, 7.53 and 7.32%, respectively. The average density of silicone resin of coated fabric 1 was reduced by 47.96%, and the closer the distance from the heated surface was, the more the density decreased. The thermal conductivity and specific heat capacity of silicone resin of coated fabric 1 increased with time. Before 50 s, each decomposition rate curve showed an inflection point, at which the silicone resin decomposed most intensely. Research limitations/implications Based on experimental observations, the ablative behavior of the material with fixed expansion layer was simulated. In the further research, the moving expansion layer could be considered. Originality/value This paper provides the theoretical basis to evaluate the effectiveness of thermal protection materials that will swell during ablation.

show abstract

Evaluation System for Ablative Material in a High-Temperature Torch

Cited by 21 publications

References 74 publications

Advances in Ablation or Oxidation Mechanisms and Behaviors of Carbon Fiber-Reinforced Si-Based Composites

Advances in Ablation or Oxidation Mechanisms and Behaviors of Carbon Fiber-Reinforced Si-Based Composites

CCCM Specific Surface Estimation in Process of Low-Temperature Oxidation

Numerical analysis of ablative behavior of silicone resin coated carbon fabric

Contact Info

Product

Resources

About