Analytical modeling and experimental verification of the performance of a low temperature ablative material

A description is presented of the development and verification of a computer model of the ablation of Thermo-lag T-230, a low temperature ablator. The model is constructed utilizing a basic understanding of the decomposition behavior of the material in a thermal environment. An existing and readily available general numerical analysis computer program is used, and the modeling serves as input to that program. The model adequately predicts both the temperature and mass loss histories of T-230 heatshields exposed to various aerothermodynamic environments including radiant heating and arc heated convective exposures, and the ascent heating environment of a suborbital, exoatmospheric flight vehicle.