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

Viola Renato; Thomas Scanlon

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

Viola Renato, Thomas Scanlon

Mechanical And Aerospace Engineering

Research output: Contribution to conference › Paper

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Abstract

A new method to simulate ablative Thermal Protection System (TPS) behaviour during an atmospheric entry is presented. The approach consists of the coupling of two reduced order codes: one for the material behaviour prediction and one for the external heat flux estimation. The latter is a reduced order aero-thermodynamic code developed at Strathclyde University while the internal solver is a unidimensional thermo-ablative code. The three-dimensional spacecraft calculations are generated by running the one-dimensional ablative code on every geometrical vertex. This method produces an estimation of the 3D problem solution while avoiding the complexity of a multidimensional thermo-ablative solver. The test case analysed to prove the method efficacy is the entry of the Pathfinder capsule in the Martian atmosphere.

Original language	English
Number of pages	9
Publication status	Published - 25 Sep 2017
Event	68th International Astronautical Congress (IAC) - Adelaide, Australia Duration: 25 Sep 2017 → 29 Sep 2017 Conference number: 68th

Conference

Conference	68th International Astronautical Congress (IAC)
Abbreviated title	IAC-17
Country	Australia
City	Adelaide
Period	25/09/17 → 29/09/17

Keywords

ablation
Thermal Protection
modelling
re-entry
Mars pathfinder
astronautics

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Renato-Scanlon-IAC-2017-Multi-dimensional-ablation-and-thermal-response-program-for-Martian-entry-analysisAccepted author manuscript, 1.18 MB

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Cite this

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title = "Multi-dimensional ablation and thermal response program for Martian entry analysis",

abstract = "A new method to simulate ablative Thermal Protection System (TPS) behaviour during an atmospheric entry is presented. The approach consists of the coupling of two reduced order codes: one for the material behaviour prediction and one for the external heat flux estimation. The latter is a reduced order aero-thermodynamic code developed at Strathclyde University while the internal solver is a unidimensional thermo-ablative code. The three-dimensional spacecraft calculations are generated by running the one-dimensional ablative code on every geometrical vertex. This method produces an estimation of the 3D problem solution while avoiding the complexity of a multidimensional thermo-ablative solver. The test case analysed to prove the method efficacy is the entry of the Pathfinder capsule in the Martian atmosphere.",

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AU - Renato, Viola

AU - Scanlon, Thomas

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N2 - A new method to simulate ablative Thermal Protection System (TPS) behaviour during an atmospheric entry is presented. The approach consists of the coupling of two reduced order codes: one for the material behaviour prediction and one for the external heat flux estimation. The latter is a reduced order aero-thermodynamic code developed at Strathclyde University while the internal solver is a unidimensional thermo-ablative code. The three-dimensional spacecraft calculations are generated by running the one-dimensional ablative code on every geometrical vertex. This method produces an estimation of the 3D problem solution while avoiding the complexity of a multidimensional thermo-ablative solver. The test case analysed to prove the method efficacy is the entry of the Pathfinder capsule in the Martian atmosphere.

AB - A new method to simulate ablative Thermal Protection System (TPS) behaviour during an atmospheric entry is presented. The approach consists of the coupling of two reduced order codes: one for the material behaviour prediction and one for the external heat flux estimation. The latter is a reduced order aero-thermodynamic code developed at Strathclyde University while the internal solver is a unidimensional thermo-ablative code. The three-dimensional spacecraft calculations are generated by running the one-dimensional ablative code on every geometrical vertex. This method produces an estimation of the 3D problem solution while avoiding the complexity of a multidimensional thermo-ablative solver. The test case analysed to prove the method efficacy is the entry of the Pathfinder capsule in the Martian atmosphere.

KW - ablation

KW - Thermal Protection

KW - modelling

KW - re-entry

KW - Mars pathfinder

KW - astronautics

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Y2 - 25 September 2017 through 29 September 2017

ER -