Carbon–phenolic ablative materials for re-entry space vehicles: Manufacturing and properties

Pulci, Giovanni; Tirillò, Jacopo; Marra, Francesco; Fossati, F.; Bartuli, Cecilia; Valente, Teodoro

doi:10.1016/j.compositesa.2010.06.010

Cited by 205 publications

(115 citation statements)

References 9 publications

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“…It begins to gel around 120°C, and its final density is 1.22 g/cm 3 . An advantage of using resole type phenolic resin is its ability to crosslink by means of heat without incorporation of a curing agent 28 . The char yield of this resin is 55-60%/mass yield at 1000°C heat treatment in inert atmosphere.…”

Section: Methodsmentioning

confidence: 99%

Electrical Behavior of Carbon Fiber/Phenolic Composite during Pyrolysis

et al. 2015

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Carbon fiber reinforced carbon (CFRC) composites, also called carbon/carbon (C/C) composites are materials with superior characteristics such as low density, good thermal shock resistance, high strength and low ablation under severe environments. Due to their properties, CFRC composites are ideal candidate in the high temperature fields. By pyrolysis process, carbon fiber phenolic resin composites are converted in C/C composites. The phenolic resin is a non-conductor (electrical resistivity of 1012 Ω.m) and during heat treatment of carbon fiber phenolic resin composite, it is converted to a carbon matrix (a conductor). This conversion was accomplished by electrical resistivity measurements using four-probe method according to ASTM C611-98 with final electrical resistivity of 0.04 mΩ.m. Microstructure of carbon fiber phenolic resin composite was assessed by using optical microscopy and image analysis. Pore volume was evaluated and the results were compared with thermal gravimetric analyses. The values of activation energy (Ea) during pyrolysis were 1.153kJ.mol -1 and 10.860kJ.mol -1.

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Section: Methodsmentioning

confidence: 99%

Electrical Behavior of Carbon Fiber/Phenolic Composite during Pyrolysis

et al. 2015

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“…The fiber degrades to cone shape fiber during ablation in high fiber density area. In the low fiber density area, the fibers get weakened during ablation and peel off from the matrix due to aerodynamic stresses [71].…”

Section: Thermal Decompositionmentioning

confidence: 99%

Hybrid Carbon-Carbon Ablative Composites for Thermal Protection in Aerospace

Sanoj

Kandasubramanian

2014

Journal of Composites

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Composite materials have been steadily substituting metals and alloys due to their better thermomechanical properties. The successful application of composite materials for high temperature zones in aerospace applications has resulted in extensive exploration of cost effective ablative materials. High temperature heat shielding to body, be it external or internal, has become essential in the space vehicles. The heat shielding primarily protects the substrate material from external kinetic heating and the internal insulation protects the subsystems and helps to keep coefficient of thermal expansion low. The external temperature due to kinetic heating may increase to about maximum of 500 ∘ C for hypersonic reentry space vehicles while the combustion chamber temperatures in case of rocket and missile engines range between 2000 ∘ C and 3000 ∘ C. Composite materials of which carbon-carbon composites or the carbon allotropes are the most preferred material for heat shielding applications due to their exceptional chemical and thermal resistance.

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“…Finally, the finite elements in the original micromechanical mesh are eliminated using extracted element numbers. In this paper, the cross-sectional photographs for image-based models are obtained from experimental data of carbon-phenolic ablative materials [21]. Fig.…”

Section: Image-based Fe Modelsmentioning

confidence: 99%

Quantitative Assessment of Variation in Poroelastic Properties of Composite Materials Using Micromechanical RVE Models

Han¹,

Kim²,

Shin³

2016

International Journal of Aeronautical and Space Sciences

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A poroelastic composite material, containing different material phases and filled with fluids, serves as a model to formulate the overall ablative behaviors of such materials. This article deals with the assessment of variation in nondeterministic poroelastic properties of two-phase composite materials using micromechanical representative volume element (RVE) models. Considering the configuration and arrangement of pores in a matrix phase, various RVEs are modeled and analyzed according to their porosity. In order to quantitatively investigate the effects of microstructure, changes in effective elastic moduli and poroelastic parameters are measured via finite element (FE) analysis. The poroelastic parameters are calculated from the effective elastic moduli and the pore-pressure-induced strains. The reliability of the numerical results is verified through image-based FE models with the actual shape of pores in carbon-phenolic ablative materials. Additionally, the variation of strain energy density is measured, which can possibly be used to evaluate microstress concentrations.

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Carbon–phenolic ablative materials for re-entry space vehicles: Manufacturing and properties

Cited by 205 publications

References 9 publications

Electrical Behavior of Carbon Fiber/Phenolic Composite during Pyrolysis

Electrical Behavior of Carbon Fiber/Phenolic Composite during Pyrolysis

Hybrid Carbon-Carbon Ablative Composites for Thermal Protection in Aerospace

Quantitative Assessment of Variation in Poroelastic Properties of Composite Materials Using Micromechanical RVE Models

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