Ablation behavior of SiC fiber/carbon matrix composites under simulated atmospheric reentry conditions

Ogasawara, Toshio; Aoki, Toru; Hassan, Mohamed Sayed Aly; Mizokami, Yosuke; Watanabe, Naoyuki

doi:10.1016/j.compositesa.2010.10.015

Cited by 35 publications

(9 citation statements)

References 24 publications

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“…9A and 9B). Similar microtextures of protruding phases exposed in the matrix were produced by direct evaporation phenomenon in arc jet ablation experiments on heterogeneous surfaces (Vignoles et al 2009;Ogasawara et al 2011). When patches of microtexture formed by evaporation cross contraction cracks uninterrupted, this indicates that the primary quenching episode preceded ablation (Fig.…”

Section: Variations Of Aerodynamic Ablation Featuresmentioning

confidence: 63%

Constraints on the origins of iron silicide spherules in ultrahigh‐temperature distal impact ejecta

Batovrin¹,

Lipovsky²,

Gulbin

et al. 2021

Meteorit & Planetary Scien

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Terrestrially occurring iron silicide spherules, described in the geological literature for 160 years as cosmogenic and approved as "extraterrestrial" minerals by IMA CNMMN in 1984, so far have escaped any serious examination by meteoriticists. Our isotopic and REE data, obtained for silicide spherules for the first time, disagree with the meteoritic origin of gupeiite (Fe 3 Si) and xifengite (Fe 5 Si 3 ) spherules from two continents. Despite departures from terrestrial norms ( 87 Rb/ 86 Sr-0.0174; 87 Sr/ 86 Sr-0.700181; 3 He/ 4 He-7.57 × 10 −6 ; 40 Ar/ 36 Ar-325.9), the compositions of 143 Nd/ 144 Nd (0.512034) and 147 Sm/ 144 Nd (0.06357), as well as REE abundances, clarify provenance from upper crust sediments for samples with U/Pb age of 121-314 ka from the Ala-Tau range in the Urals. However, the morphology of flanged button shapes, ring waves, and eccentro-radiating ridges reliably constrains the origin of silicide spherules to distal meteoritic impact ejecta. Arc jet ablation experiments have previously demonstrated that similar morphologies, observed on australite tektites, reflect aerodynamic ablation rates corresponding to flight velocities well into orbital range. These features are generally accepted as conclusive evidence for hypervelocity atmospheric entry from space. Internal structure, consistent with accretion through the coalescence of 3-5 µm droplets, and composition, closely corresponding to 1893-1154 K span of C-type condensation sequences, indicate a high probability of processing through recondensation of ejecta vapor.

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Section: Variations Of Aerodynamic Ablation Featuresmentioning

confidence: 63%

Constraints on the origins of iron silicide spherules in ultrahigh‐temperature distal impact ejecta

Batovrin¹,

Lipovsky²,

Gulbin

et al. 2021

Meteorit & Planetary Scien

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“…6 Independently from the production method, the CMC matrix shows not negligible residual porosity that makes the material sensitive wind tunnel. 3,10 The main drawback of the CMCs is the porosity of their SiC ceramic matrix, that prevents the formation of a continuous passivating layer and thus allows the oxygen to penetrate within the composite and to react with the matrix itself, the ceramic fibers and the interlayer put at the matrix/fiber interface. Oxidation reactions result in material degradation and greatly limits the re-usability of TPS for several space missions.…”

Section: Introductionmentioning

confidence: 99%

“…Oxidation reactions result in material degradation and greatly limits the re-usability of TPS for several space missions. 10,11 The re-usability can be improved by depositing a CVD notporous SiC coating on the CMC surface, 1 but cracks can grow within the coating, owing to the thermal mismatch between coating and CMC, and then the material degradation is only delayed.…”

Section: Introductionmentioning

confidence: 99%

Self passivating behavior of multilayer SiC under simulated atmospheric re-entry conditions

Badini

Liedtke

Euchberger

et al. 2012

Journal of the European Ceramic Society

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“…In order to obtain carbon-phenolic ablators with improved performances the manufacturing strategy, the choice of the solvent employed, the ratio between resin and solvent, the structure of the carbon felt and the nature of the phenolic resin have to be selected very carefully [14]. The characteristics of a thermal protection system (TPS) need to be well described in order to select the right system for a specific mission, and significant ground tests can be carried out in plasma wind tunnel (PWT) facilities, where the heat flux conditions encountered during a real reentry trajectory can be reproduced [28][29][30][31]. Data collected during a PWT test can be implemented in a FE model, in order to rebuild the performances of the tested ablative materials and create a numerical tool for the TPS design able to reduce the number of the required experimental tests performed in plasma wind tunnel facilities [32,33].…”

Section: Introductionmentioning

confidence: 99%

Design of New Carbon-Phenolic Ablators: Manufacturing, Plasma Wind Tunnel Tests and Finite Element Model Rebuilding

et al. 2021

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Ablative materials represent a widespread solution for shielding space vehicles from overheating during a reentry phase in atmosphere where the high heating fluxes and the consequent high temperatures cannot be compatible with the vehicle structure and with the safety of the payload and/or the crew. In this work, two different kinds of carbon-phenolic ablators with a density of 0.3 g/cm3 were manufactured and their mechanical and thermal properties were experimentally evaluated. The thermal protection performances of the developed ablators were assessed in a hypersonic plasma wind tunnel facility, setting representative enthalpy and heat flux conditions (6 and 13 MW/m2), consistent with atmospheric reentry missions from high energy orbits. Data of the experimental tests were compared with the results obtained by a finite element model built up for these materials with the commercial software SAMCEF Amaryllis. All results enlighten the good performances of the ablators under severe heat flux conditions and outline their operating limits.

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Ablation behavior of SiC fiber/carbon matrix composites under simulated atmospheric reentry conditions

Cited by 35 publications

References 24 publications

Constraints on the origins of iron silicide spherules in ultrahigh‐temperature distal impact ejecta

Constraints on the origins of iron silicide spherules in ultrahigh‐temperature distal impact ejecta

Self passivating behavior of multilayer SiC under simulated atmospheric re-entry conditions

Design of New Carbon-Phenolic Ablators: Manufacturing, Plasma Wind Tunnel Tests and Finite Element Model Rebuilding

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