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.
|Number of pages||6|
|Publication status||Published - 3 Jun 2017|
|Event||31st International Symposium on Space Technology and Science (ISTS) - |
Duration: 3 Jun 2017 → 9 Jun 2017
|Conference||31st International Symposium on Space Technology and Science (ISTS)|
|Period||3/06/17 → 9/06/17|
- thermal protection
- stardust SRC
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), .