Pyrolysis gas energy transport in ablative material

The use of Thermal Protection Systems (TPS) for spacecraft entering the atmosphere is critical in protecting vehicles from extreme heat. Ablative materials offer an effective solution to mitigating this heat by absorbing and diverting thermal energy by releasing pyrolysis gas to the material surface. However, due to the uncertainties surrounding the behavior of pyrolysis gas, existing numerical models require validation. The Kentucky Aerothermodynamics and Thermal Response System (KATS) is used to simulate material response of TPS, including charring and non-charring ablators. This study conducts multiple test cases that aim to validate the multi-material and multi-dimensional numerical framework within KATS material response modeling, specifically focusing on characterizing pyrolysis gas energy transport.