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.
|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||68th International Astronautical Congress (IAC)|
|Period||25/09/17 → 29/09/17|
- Thermal Protection
- Mars pathfinder
Renato, V., & Scanlon, T. (2017). Multi-dimensional ablation and thermal response program for Martian entry analysis. Paper presented at 68th International Astronautical Congress (IAC), Adelaide, Australia.