Heat transfer in a multi-layered thermal protection system under aerodynamic heating

Ferraiuolo, Michele; Manca, Oronzio

doi:10.1016/j.ijthermalsci.2011.10.019

Cited by 57 publications

(17 citation statements)

References 14 publications

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“…When reentry vehicle enters the earth's atmosphere, the vehicle encounters severe aerodynamic heating and thermal protection system (TPS) is necessary . Charring composite materials are typically used as TPS material . While charring materials encounter aerodynamic heating, charring materials pyrolyze, and release gases such as methane, carbon monoxide, carbon dioxide, and hydrogen .…”

Section: Introductionmentioning

confidence: 99%

“…1 Charring composite materials are typically used as TPS material. [2][3][4] While charring materials encounter aerodynamic heating, charring materials pyrolyze, and release gases such as methane, carbon monoxide, carbon dioxide, and hydrogen. [5][6][7] There are solid phase, gas phase, chemical reaction, and heat transfer in the pyrolysis layer which is unsteady and complex [8][9][10][11][12] ; therefore, prediction of the thermal conductivity of the pyrolysis layer has always been difficult.…”

Section: Introductionmentioning

confidence: 99%

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Prediction of thermal conductivity of pyrolysis layer by thermogravimetry data

Guo

Huang

2019

J of Applied Polymer Sci

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Thermal conductivity of the pyrolysis layer in the charring material is of great importance for the optimal design of thermal protection system (TPS) in reentry vehicles. A method based on the thermogravimetry data of the charring material is presented to predict the thermal conductivity of the pyrolysis layer and the distribution of thermal conductivity of the pyrolysis layer is estimated. In addition, in order to validate the accuracy of this method, thermal response of the charring material is calculated with the predicted thermal conductivity and compared with the experimental data. The simulation results agree with the measured data and the numerical results indicate that taking this method to calculate the thermal conductivity of the pyrolysis layer is more compatible with the actual situation. This study is helpful to the optimization of the TPS. © 2019 Wiley Periodicals, Inc. J. Appl. Polym. Sci. 2020, 137, 48346.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Prediction of thermal conductivity of pyrolysis layer by thermogravimetry data

Guo

Huang

2019

J of Applied Polymer Sci

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“…The projects in the gradient TPC and materials at NASA Glenn Research Laboratory and NASA [6][7][8] demonstrated the possibility of manufacturing these materials to enable the required thermal mode of the spacecraft. The TPC in question were based on CCCM or ceramic matrix composite material with the silicon carbide fiber frame, modified with the high-melt zirconium-based carbide systems.…”

Section: Introductionmentioning

confidence: 99%

Modeling the heat and mass transfer in the pores of the thermal protection carbon-carbon frame during the gas-phase deposition of silicon carbide

2016

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Abstract. This paper is dedicated to the numerical simulation of the gasphase deposition into the porous carbon-carbon frame for the gradient thermal protection of reentry vehicles. The paper presents the specifics of creating the representative volume elements of the porous carbon-carbon frames based on the microstructure data from the computed tomography scanner, electronic scanning microscope and porosimetry results. The finite-element models of the representative volume elements are created in order to obtain the net independent solution, including the special finite elements at the phase interfaces. The finite-element and finite-volume method was used for calculation, implemented in MSC.Digimat and ANSYS software packages. The effect of the reagent parameters on the gas-phase deposition process, uniformity and rate of silicon carbide deposition was simulated parametrically, and the results are presented.

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“…And the forced transpiration cooling is a technique in which a coolant fluid (such as water or air) is sent through a porous medium in order to protect that surface from heat, but it is too complex and uncertain to be used in aerospace [3]. Ferraiuolo and Manca [5] developed analytical and semi-analytical procedures to solve thermal problems. Gori et al [4] evaluated the effective thermal conductivity of an ablative composite material in the state of virgin material and in three paths of degradation.…”

Section: Introductionmentioning

confidence: 99%

The inverse problem in zero linear ablation of aluminizing carbon composites under high heat flux

Huang

et al. 2013

THERM SCI

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The concept of zero linear ablation is introduced to describe the mass ablation without shape change, and it is employed to design thermal protection materials under an extreme thermal environment. Aluminizing carbon composites are used as a sample to study numerically the heat response. As indicated in the numerical results, the shape of the composites did not change under a high heat flux because the phase transition (melt or evaporation) of aluminum can absorb a lot of energy before the ablation of carbon, and the zero linear ablation depends on not only the volume fraction of aluminum, but also the heating period and the heat flux.

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Heat transfer in a multi-layered thermal protection system under aerodynamic heating

Cited by 57 publications

References 14 publications

Prediction of thermal conductivity of pyrolysis layer by thermogravimetry data

Prediction of thermal conductivity of pyrolysis layer by thermogravimetry data

Modeling the heat and mass transfer in the pores of the thermal protection carbon-carbon frame during the gas-phase deposition of silicon carbide

The inverse problem in zero linear ablation of aluminizing carbon composites under high heat flux

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