Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling

Paglia, Laura; Tirillò, Jacopo; Marra, Francesco; Bartuli, Cecilia; Simone, Antonia; Valente, Teodoro; Pulci, Giovanni

doi:10.1016/j.matdes.2015.11.066

Cited by 60 publications

(39 citation statements)

References 18 publications

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“…This review does not include rigid heat shielding materials, which is a special area of study involving other types of materials particularly suited for low orbit and space vehicles, such phenolic resin, silicon oxides, and ceramics [30,31].…”

Section: Polymeric Insulators For Solid Propellant Rocket Motorsmentioning

confidence: 99%

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

et al. 2020

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This review addresses a comparison, based on the literature, among nitrile rubber (NBR), ethylene-propylene-diene-monomer rubber (EPDM), and polyurethane (PU) elastomeric heat shielding materials (EHSM). Currently, these are utilized for the insulation of rocket engines to prevent catastrophic breakdown if combustion gases from propellant reaches the motor case. The objective of this review is to evaluate the performance of PU–EHSM, NBR–EHSM, and EPDM–EHSM as insulators, the latter being the current state of the art in solid rocket motor (SRM) internal insulation. From our review, PU–EHSM emerged as an alternative to EPDM–EHSM because of their easier processability and compatibility with composite propellant. With the appropriate reinforcement and concentration in the rubber, they could replace EPDM in certain applications such as rocket motors filled with composite propellant. A critical assessment and future trends are included. Rubber composites novelties as EHSM employs specialty fillers, such as carbon nanotubes, graphene, polyhedral oligosilsesquioxane (POSS), nanofibers, nanoparticles, and high-performance engineering polymers such as polyetherimide and polyphosphazenes.

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Section: Polymeric Insulators For Solid Propellant Rocket Motorsmentioning

confidence: 99%

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

et al. 2020

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“…As a suitable reinforcement, carbon fibers are preferred over other fibers like glass fiber, kevlar fiber, nylon fiber, and so on due to their excellent mechanical strength and modulus, creep resistance, very high electrical and thermal conductivity, thermal‐shock resistance, very low coefficient of thermal expansion, inertness to chemicals, and so on . Therefore, the CPCs possess the excellent mechanical strength, ablation resistance, self‐lubricating nature, anti‐seizure characteristics, high thermal stability and low coefficient of thermal expansion, which make it one of the most suitable material for various thermo‐structural applications such as in rocket engines parts and thermal protection systems for reentry vehicles , automotive bearings, rotors, and pistons . However, various other parameters such as types of carbon fiber and fillers, sizing, coupling agent, processing conditions, types of fillers, and so on play crucial roles to obtain desired thermo‐mechanical and other properties .…”

Section: Introductionmentioning

confidence: 99%

Fabrication and characterization of eco‐friendly human‐hair derived porous carbon‐filled carbon fabric‐reinforced polymer composites

et al. 2018

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The effects of human hair‐derived porous carbon (HHC) as an eco‐friendly reinforcing filler in the carbon fabric‐reinforced phenolic matrix composites (CPCs) are evaluated through micro‐structural characterization studies, tensile, and flexural tests, dynamic mechanical analysis, density and electrical conductivity measurements. Various interfacial interaction parameters like reinforcement efficiency, C‐factor, adhesion factor, and so on are also calculated and compared for understanding the effects of HHC in composites. Conventional hand‐layup technique is used for impregnation of slurry made of phenolic resin and 0–50 wt% HHC on carbon fabric followed by stacking and curing through hot pressing to get laminates of CPCs. Significant improvement in mechanical, viscoelastic and electrical properties are observed over unfilled composite for all investigated HHC loadings. However, 30–40 wt% filler loading gives the optimum balance of properties. The results show ∼15, 93, 50, 85, and 132% increase in tensile strength, Young's modulus, flexural strength, flexural modulus, and storage modulus, respectively. Moreover drastic gain (1,500%) in electrical conductivity and substantial enhancement in thermal stability of CPCs make HHC as a cheap alternative reinforcing filler for structural composite applications working under thermo‐mechanical loads. POLYM. COMPOS., 40:E1573–E1587, 2019. © 2018 Society of Plastics Engineers

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“…Fang et al [18] simulated the velocity field, temperature field, and pressure field around ablation pit to demonstrate the formation mechanism of "skeleton structure." Paglia et al [19] simulated the pyrolysis and erosion of the ablator by implementing a complex finite element model, which results in very good agreement with experimental evidences. Very encouraging results were especially obtained in terms of surface insulation capacity and surface recession.…”

Section: Introductionmentioning

confidence: 70%

Experimental and Numerical Evaluation of the Ablation Process of Carbon/Carbon Composites Using High Velocity Oxygen Fuel System

Fan

Jiang

et al. 2017

Advances in Materials Science and Engineering

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The ablation process of carbon/carbon (C/C) composites was tested under hypersonic flowing propane flame. The microstructures of C/C composites were characterized and the numerical analysis was performed. Two typical ablation morphologies of the carbon fibers, which are drum-like and needle-like shapes, were observed depending on the alignments of fibers to the flame directions. Temperature fields in the composites were analyzed using finite element method, and the mechanisms that govern the formation of different ablation behaviors were elucidated. For paralleled fiber bundles, the highest temperature situates in the middle parts underlying the ablation pits, where the drum-like shape is formed. For perpendicular fiber bundles, the highest temperature appears at the turning point between the transverse section and the surface of fiber, which leads to the gradual ablation from the fiber surface toward the axis, and eventually the formation of the needle-like shape.

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Carbon-phenolic ablative materials for re-entry space vehicles: plasma wind tunnel test and finite element modeling

Cited by 60 publications

References 18 publications

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

Evaluation of elastomeric heat shielding materials as insulators for solid propellant rocket motors: A short review

Fabrication and characterization of eco‐friendly human‐hair derived porous carbon‐filled carbon fabric‐reinforced polymer composites

Experimental and Numerical Evaluation of the Ablation Process of Carbon/Carbon Composites Using High Velocity Oxygen Fuel System

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