炭化アブレ一夕のスポレーションモデル

摘要

When a space vehicle enters a planet at high velocity, the vehicle encounters severe aerodynamic heating environments.An ablation heat protection system has been the most reliable and has been successfully applied to the reentry problem.Mechanical spallation is expected to play one of the most important roles for the char removal of the charring ablators inhigh heat flux environments. The spallation appears to be caused by stresses due to surface pressure, thermal stresses, andstresses due to internal pressure of the pyrolysis gases. In order to update the understanding and to provide the newinsights of the spallation, a study of the thermal response of ablators is performed. Objective of this study is to model thespallation, which plays an important role for the char removal of the charring ablators in high heat flux environments, andpresent numerical results of the thermal response of ablators.