Abstract
The thermal behavior of thermal protection systems of the (re)entry vehicles subjected to aerodynamic heating is essential for flight missions. The behavior of a honeycomb-reinforced lightweight ablator is investigated in this paper using experimental and numerical methods. The inductively coupled plasma wind-tunnel facility is used to simulate the heating process, and the internal temperature of the honeycomb-reinforced lightweight ablator is monitored by sensors. The multiphysics coupling mechanisms of the honeycomb-reinforced lightweight ablator are analyzed based on the experimental results, and the multiphysics coupling model is presented mathematically. The multiphysics coupling model is validated by comparison of predicted surface and in-depth temperature profiles as well as the charring zones with the experimental results because they have good consistency. The multiphysical behavior in the charring honeycomb-reinforced lightweight ablator is analyzed using the multiphysics coupling model, including the gas pressure, the pyrolysis rate, and the mass flow rate. This study will help on the thermal protection system design for flight missions.
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