Abstract
The initial configuration of a reentry capsule composed of thermal protection system (TPS) and substructure was designed. The temperature requirement of the substructure was set below 333 K, considering the operating temperature of electronic equipment such as batteries and GPS antennas during reentry. A maximum heat flux of 12.4 MW/m2 was applied as a boundary condition. Furthermore, the overall temperature distribution of the reentry capsule and the pyrolysis and ablation behavior of the TPS were analyzed. The surface temperature increased up to 3,227 K, and the surface recession of 7.412 mm occurred due to thermochemical ablation, but the substructure met the temperature requirements. These results imply that the thickness margin of the TPS can be reduced in the preliminary design phase, enabling further lightweighting. In conclusion, the analysis procedures were established to apply various ablative materials and design the reliable reentry capsule.
| Translated title of the contribution | Analysis of Pyrolysis and Ablation Behavior in TPS for Reentry Capsule |
|---|---|
| Original language | Korean |
| Pages (from-to) | 175-182 |
| Number of pages | 8 |
| Journal | Journal of the Korean Society for Aeronautical and Space Sciences |
| Volume | 52 |
| Issue number | 3 |
| DOIs | |
| State | Published - 2024.03 |
Keywords
- Ablation
- Charring Ablative Materials
- Pyrolysis
- Reentry Capsule
- Thermal Protection System
Quacquarelli Symonds(QS) Subject Topics
- Engineering - Mechanical
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