TY - GEN
T1 - Radiative transmission and absorption within the ablative heat shield of hypersonic vehicles
AU - Martin, Alexandre
AU - Panesi, Marco
N1 - Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
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.
AB - 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.
UR - http://www.scopus.com/inward/record.url?scp=85092648418&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85092648418&partnerID=8YFLogxK
U2 - 10.2514/6.2020-3276
DO - 10.2514/6.2020-3276
M3 - Conference contribution
AN - SCOPUS:85092648418
SN - 9781624105982
T3 - AIAA AVIATION 2020 FORUM
BT - AIAA AVIATION 2020 FORUM
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2020 FORUM
Y2 - 15 June 2020 through 19 June 2020
ER -