Ablation systems are critical components in the design of atmospheric reentry vehicles, providing thermal protection to the underlying structures from the harsh conditions experienced during high-speed descent. These systems work by removing material from the surface of the heat shield through a controlled process of ablation, which dissipates heat and prevents it from penetrating the vehicle's interior. The thermal protection system (TPS) for an atmospheric reentry vehicle represents one of the most challenging components in its overall design, and the choice of ablation material is a critical factor in ensuring the safety and integrity of the payload.

One type of ablation material is the Light-weight Ceramic Ablator (LCA), which has been widely employed in space missions due to its low density and high efficiency. In particular, the Phenolic Impregnated Carbon Ablator (PICA) designed by NASA has been successfully employed as a thermal shield for a range of applications, including the delivery of the Curiosity rover to Mars and the thermal protection of the Dragon Space X manned capsule. However, it is suspected that the physical and chemical characteristics of phenolic materials change with age, which may affect the performance of these materials in applications with extended storage/service lives prior to use.

In this context, our software solution,  K-load, can evaluate the mechanical/thermal, and physical performance loss of LCA composites over time. Our software uses high-fidelity finite element models to simulate the behavior of the material under various aging conditions, taking into account the changes in its physical and chemical properties. By providing a more accurate and comprehensive assessment of the resin's loss of performance, K-load aims to improve the design and reliability of ablation systems for a range of applications.