Multi-dimensional ablation and thermal response program for re-entry analysis

Viola Renato, Thomas Scanlon, Richard Brown

Research output: Contribution to conferencePaper

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Abstract

The development of a new methodology to estimate the ablative Thermal Protection System (TPS) behaviour and the external flux conditions during the re-entry phase of a space mission is described in this paper. Reduced-order codes are used to investigate both the flux aerodynamics and the ablative material pyrolysis phenomenon. The re-entry of the Stardust sample return capsule is analysed and the results are compared to high-fidelity coupled programs. The aim of the study is to prove that three-dimensional estimations of the external heat flux along the capsule, TPS external temperature and surface recession can be evaluated with reduced-order codes.
Original languageEnglish
Number of pages6
Publication statusPublished - 3 Jun 2017
Event31st International Symposium on Space Technology and Science (ISTS) -
Duration: 3 Jun 20179 Jun 2017
http://www.ists.or.jp/

Conference

Conference31st International Symposium on Space Technology and Science (ISTS)
Period3/06/179/06/17
Internet address

Fingerprint

Reentry
Ablation
Ablative materials
Fluxes
Heat flux
Aerodynamics
Pyrolysis
Temperature
Hot Temperature

Keywords

  • ablation
  • thermal protection
  • modeling
  • stardust SRC
  • astronautics

Cite this

Renato, V., Scanlon, T., & Brown, R. (2017). Multi-dimensional ablation and thermal response program for re-entry analysis. Paper presented at 31st International Symposium on Space Technology and Science (ISTS), .
Renato, Viola ; Scanlon, Thomas ; Brown, Richard. / Multi-dimensional ablation and thermal response program for re-entry analysis. Paper presented at 31st International Symposium on Space Technology and Science (ISTS), .6 p.
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Renato, V, Scanlon, T & Brown, R 2017, 'Multi-dimensional ablation and thermal response program for re-entry analysis' Paper presented at 31st International Symposium on Space Technology and Science (ISTS), 3/06/17 - 9/06/17, .

Multi-dimensional ablation and thermal response program for re-entry analysis. / Renato, Viola; Scanlon, Thomas; Brown, Richard.

2017. Paper presented at 31st International Symposium on Space Technology and Science (ISTS), .

Research output: Contribution to conferencePaper

TY - CONF

T1 - Multi-dimensional ablation and thermal response program for re-entry analysis

AU - Renato, Viola

AU - Scanlon, Thomas

AU - Brown, Richard

PY - 2017/6/3

Y1 - 2017/6/3

N2 - The development of a new methodology to estimate the ablative Thermal Protection System (TPS) behaviour and the external flux conditions during the re-entry phase of a space mission is described in this paper. Reduced-order codes are used to investigate both the flux aerodynamics and the ablative material pyrolysis phenomenon. The re-entry of the Stardust sample return capsule is analysed and the results are compared to high-fidelity coupled programs. The aim of the study is to prove that three-dimensional estimations of the external heat flux along the capsule, TPS external temperature and surface recession can be evaluated with reduced-order codes.

AB - The development of a new methodology to estimate the ablative Thermal Protection System (TPS) behaviour and the external flux conditions during the re-entry phase of a space mission is described in this paper. Reduced-order codes are used to investigate both the flux aerodynamics and the ablative material pyrolysis phenomenon. The re-entry of the Stardust sample return capsule is analysed and the results are compared to high-fidelity coupled programs. The aim of the study is to prove that three-dimensional estimations of the external heat flux along the capsule, TPS external temperature and surface recession can be evaluated with reduced-order codes.

KW - ablation

KW - thermal protection

KW - modeling

KW - stardust SRC

KW - astronautics

M3 - Paper

ER -

Renato V, Scanlon T, Brown R. Multi-dimensional ablation and thermal response program for re-entry analysis. 2017. Paper presented at 31st International Symposium on Space Technology and Science (ISTS), .