Thermal shield materials (TSMs) are critical components in aircraft and aerospace systems, operating under extreme thermal, mechanical, and chemical loads. These materials are subjected simultaneously to high temperatures, mechanical stresses, chemical aggression, intense radiation, and abrasive erosion, making their behavior under service conditions complex and multifaceted. The thermal load experienced by TSMs is strongly influenced by variations in both the velocity and temperature of the incoming flow, particularly during spacecraft re-entry, where rapid changes in flow parameters induce significant thermal and mechanical stresses. During heating, TSMs undergo physical and chemical transformations that substantially alter their microstructure, composition, and density, directly affecting their thermal deformation characteristics. Understanding the influence of different heat supply techniques on these transformations is essential for predicting material performance and ensuring the reliability and safety of aerospace vehicles. This study investigates the relationship between heat application methods and the resulting thermal deformation in composite shield materials, providing insights into optimizing material design and thermal protection strategies for aerospace applications.