Radiative transmission and absorption within the ablative heat shield of hypersonic vehicles

Alexandre Martin; Marco Panesi

doi:10.2514/6.2020-3276

Radiative transmission and absorption within the ablative heat shield of hypersonic vehicles

Alexandre Martin, Marco Panesi

Mechanical and Aerospace Engineering

Research output: Contribution to conference › Paper › peer-review

8 Scopus citations

Abstract

The P₁ approximation to the radiative transfer equation is coupled to a material response code in order to model ablative materials. These types of materials are used as thermal protection systems for atmospheric entry vehicles. Several test cases are presented to verify the implementation and to validate the approach. Representative conditions – mimicking an arc-jet, a radiant heating facility, and a re-entry trajectory – are used to demonstrate the validity of the coupled model. The code is then used to replicate an experiment that studies the effects of the wavelength on the thermal response of charring ablators. Two lasers are used to deliver the heat pulse. The first laser, at a wavelength of 1.07 μm, deposits the energy within the material, as opposed to the 10.6 μm laser, which mostly does it on the surface. The numerical results verify the findings of the experiment, thus confirming the importance of spectrally resolving the radiative heat flux within charring ablators.

Original language	English
DOIs	https://doi.org/10.2514/6.2020-3276
State	Published - Jun 15 2020
Event	AIAA AVIATION 2020 FORUM - Virtual, Online Duration: Jun 15 2020 → Jun 19 2020

Conference

Conference	AIAA AVIATION 2020 FORUM
City	Virtual, Online
Period	6/15/20 → 6/19/20

Bibliographical note

Funding Information:
Support for this work was provided by the NASA SpaceTech–REDDI–2018 – ESI grant 80NSSC19K0218. The authors would like to thank A. Brandis, S. White and R. Jaffe from NASA Ames Research Center, and A. Amar from NASA Johnson Space Center for insightful discussions, as well as K. Tagavi from the University of Kentucky for reviewing the manuscript.

Funding Information:
Support for this work was provided by the NASA SpaceTech?REDDI?2018 ? ESI grant 80NSSC19K0218. The authors would like to thank A. Brandis, S. White and R. Jaffe from NASA Ames Research Center, and A. Amar from NASA Johnson Space Center for insightful discussions, as well as K. Tagavi from the University of Kentucky for reviewing the manuscript.

Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

ASJC Scopus subject areas

Nuclear Energy and Engineering
Aerospace Engineering
Energy Engineering and Power Technology

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abstract = "The P1 approximation to the radiative transfer equation is coupled to a material response code in order to model ablative materials. These types of materials are used as thermal protection systems for atmospheric entry vehicles. Several test cases are presented to verify the implementation and to validate the approach. Representative conditions – mimicking an arc-jet, a radiant heating facility, and a re-entry trajectory – are used to demonstrate the validity of the coupled model. The code is then used to replicate an experiment that studies the effects of the wavelength on the thermal response of charring ablators. Two lasers are used to deliver the heat pulse. The first laser, at a wavelength of 1.07 μm, deposits the energy within the material, as opposed to the 10.6 μm laser, which mostly does it on the surface. The numerical results verify the findings of the experiment, thus confirming the importance of spectrally resolving the radiative heat flux within charring ablators.",

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N2 - The P1 approximation to the radiative transfer equation is coupled to a material response code in order to model ablative materials. These types of materials are used as thermal protection systems for atmospheric entry vehicles. Several test cases are presented to verify the implementation and to validate the approach. Representative conditions – mimicking an arc-jet, a radiant heating facility, and a re-entry trajectory – are used to demonstrate the validity of the coupled model. The code is then used to replicate an experiment that studies the effects of the wavelength on the thermal response of charring ablators. Two lasers are used to deliver the heat pulse. The first laser, at a wavelength of 1.07 μm, deposits the energy within the material, as opposed to the 10.6 μm laser, which mostly does it on the surface. The numerical results verify the findings of the experiment, thus confirming the importance of spectrally resolving the radiative heat flux within charring ablators.

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Radiative transmission and absorption within the ablative heat shield of hypersonic vehicles

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ASJC Scopus subject areas

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