Application of integral methods to ablation charring erosion - A review

Potts, Robert L.

doi:10.2514/3.26597

Cited by 107 publications

(81 citation statements)

References 35 publications

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“…We also assume that the pyrolysis gases are chemically inert with respect to the boundary layer gases. 13) Thus the surface boundary condition is obtained and is shown below 13) …”

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

“…In the calculation, �� is obtained considering oxidation (reaction controlled or diffusion controlled oxidation) and sublimation of the surface char. 12,13) � � is obtained by the relation of � � � �� . Cpg and hpyro are assumed to be constant values of 1674.6 J/(kg K) and 3.313�10 5 J/kg, respectively.…”

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

“…blowis the blowing correction factor, which means the ratio of heat transfer coefficient with and without ablation mass injection into the boundary layer from the ablator surface.he factor blowalso means the correction (reduction) factor of heat flux due to the mass injection into the boundary layer. 13,14) As for the back surface boundary condition, radiation heat exchange between the back surface and the back environment is assumed.…”

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

“…[10][11][12][13][14][15][16] The in-depth governing equations for onedimensional charring ablator response are energy, mass continuity, and decomposition equations, and are expressed by…”

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

“…In such a low heating level, the surface temperature is well below 3000K and the surface ablation is mainly in the diffusion controlled oxidation region. 12,13) If q is on the level of about 10MW/m 2 , the ablator surface temperature is on the level of about 3000K, which means that the surface ablation is in the sublimation region and the surface recession would become much larger than that in the diffusion controlled oxidation region or reaction controlled oxidation region. This behavior would influence the thermal protection performance of the ablator.…”

Section: Introductionmentioning

confidence: 99%

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Study of the Effects of Heat Load, Ablator Density and Backup Structure upon the Thermal Protection Performance of Heat Shield Systems Consisting of Phenolic Carbon Ablators

Kato

Matsuda

Okuyama

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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The effects of heat load, ablator density, and backup structure, etc. upon the heat shield performance of the lightweight phenolic carbon ablators named LATS were investigated using a one-dimensional ablation analysis code. The ablator density was assumed to be from about 260 to 1000kg/m 3 . Heat flux time histories of a rectangular pattern were assumed, where cases of constant heating duration time and constant accumulated heat load (up to 600MJ/m 2 ) were considered. The heating level was assumed to be from 1 to 10MW/m 2 , which means that the ablator surface is in the region of diffusion control oxidation/sublimation. The materials of the backup wall are assumed to be aluminum, stainless steel and high density CFRP. Main findings are: (1) For a low heat flux q with the same heating duration time tq, the necessary thickness, with which the maximum back surface temperature equals to the pre-determined allowable temperature, is nearly constant as the density v changes. On the other hand, the necessary thickness increases largely when q is larger and v is smaller. The ablator necessary mass increases with the increase of v and q for the same tq.

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“…We also assume that the pyrolysis gases are chemically inert with respect to the boundary layer gases. 13) Thus the surface boundary condition is obtained and is shown below 13) …”

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

“…[10][11][12][13][14][15][16] The in-depth governing equations for onedimensional charring ablator response are energy, mass continuity, and decomposition equations, and are expressed by…”

Section: Mathematical Model Of Ablationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Study of the Effects of Heat Load, Ablator Density and Backup Structure upon the Thermal Protection Performance of Heat Shield Systems Consisting of Phenolic Carbon Ablators

Kato

Matsuda

Okuyama

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Nonlinear pyrolysis layer model for thermal behavior of nonhomogeneous charring materials

Huang

et al. 2015

J of Applied Polymer Sci

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To improve the performance of charring materials as the thermal protection system in supersonic vehicles subjected to aerodynamic heating, we develop a nonlinear pyrolysis layer model of nonhomogeneous charring composites, propose a scheme of variable density in which the resin distribution of charring materials is taken as a piecewise linear function, and then simulate the thermal behavior of the design by means of the written calculation codes. This model reveals that the thermal behavior of charring materials depends not only upon several key parameters such as heat flux, moving interfaces, moving boundary and temperaturedependent thermal properties, but also upon variable density. Further numerical investigations point out that the pyrolysis layer plays a very important role in the thermal protection performance. This study will be useful for the optimization of the thermal protection system in supersonic vehicles.

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Effects of gradient density on thermal protection performance of AVCOAT composites under varied heat flux

Huang

Zhang

et al. 2014

Polymer Composites

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Effective heat capacity is a key index to estimate the performance of the thermal protection system of reentry vehicles subjected to aerodynamic heating. To explore the effect of gradient density on the effective heat capacity in this paper, considering variable density we develop the one-dimensional pyrolysis interface model with surface ablation, and design two kinds of the gradient density of AVCOAT composites. The computer codes are written to simulate the thermal behavior of a homogeneous AVCOAT composites and that of two types of gradient AVCOAT composites under aerodynamic heat flux during Apollo capsule reentry. Numerical results indicate that gradient density can improve the thermal protection performance of homogeneous AVCOAT composites, e.g. the piecewise linear and the parabola designs have larger effective heat capacity than homogeneous AVCOAT composites, which owe to exceptional thermal response of gradient density. This study will be helpful for the design of the thermal protection system in re-entry vehicles. POLYM. COMPOS.,

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Application of integral methods to ablation charring erosion - A review

Cited by 107 publications

References 35 publications

Study of the Effects of Heat Load, Ablator Density and Backup Structure upon the Thermal Protection Performance of Heat Shield Systems Consisting of Phenolic Carbon Ablators

Study of the Effects of Heat Load, Ablator Density and Backup Structure upon the Thermal Protection Performance of Heat Shield Systems Consisting of Phenolic Carbon Ablators

Nonlinear pyrolysis layer model for thermal behavior of nonhomogeneous charring materials

Effects of gradient density on thermal protection performance of AVCOAT composites under varied heat flux

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