Extreme Thermal Fatigue: Deformation Analysis of TPS Shields

Atmospheric reentry exposes thermal protection systems to unprecedented stress. A new analysis reveals that plasma infiltration into TPS joints generates critical spallation patterns. This phenomenon, documented through high-precision photogrammetry, shows how thermal gaps act as ignition points for material fatigue, compromising the structural integrity of the spacecraft.

Technical Workflow: From Point Cloud to CFD 🔥

The process begins in RealityCapture, where a detailed 3D model of the damaged shield is generated from high-resolution images. This mesh is imported into Catia to reconstruct the joint geometry and define deformation tolerances. Subsequently, Star-CCM+ simulates the fluid dynamics of the infiltrating plasma, modeling heat transfer and dynamic pressures. The results allow correlating high-temperature zones with observed spallation points, establishing a fatigue risk map per thermal cycle.

Space Safety and Predictive Simulation 🛰️

The integrated simulation of these programs not only explains past failures; it allows predicting the service life of new compounds under extreme conditions. By digitally replicating thermal expansion and plasma erosion, engineers can redesign TPS joints to mitigate infiltration. This approach, combining photogrammetry, CAD, and CFD, is today the most effective barrier against catastrophic failures in critical missions.

How does plasma infiltration affect the microstructure of the TPS shield material during extreme thermal fatigue cycles in atmospheric reentry?

(PS: Material fatigue is like yours after 10 hours of simulation.)