Speaker
Description
This paper presents recent developments implemented in the High Fidelity Branch of Pampero spacecraft demise assessment tool, aimed at improving the physical realism and predictive capability of re-entry survivability analyses.
The first major enhancement concerns the aerodynamic and aerothermal modeling framework. Previous implementations relied primarily on engineering correlations to estimate aerodynamic loads and convective heating during atmospheric re-entry. In the updated version of Pampero, these simplified approaches are supplemented by Computational Fluid Dynamics (CFD)-based methodologies, enabling higher-fidelity characterization of flow-field interactions, localized heating phenomena, and shape-dependent effects across a wider flight regime. The integration of CFD-derived data significantly improves the representation of complex geometries and transitional flow conditions.
A second area of improvement involves the mechanical response modeling of spacecraft components during fragmentation and structural failure. The upgraded framework introduces refined thermo-mechanical coupling. These developments provide a more realistic prediction of fragmentation sequences and surviving debris characteristics.
In addition, a thermite reaction model has been implemented to assess the influence of energetic material interactions on spacecraft demise behavior. The model enables simulation of exothermic reactions between selected metallic materials and oxidizers under re-entry conditions, allowing investigation of their potential to accelerate component destruction and reduce ground casualty risk.
The combined improvements substantially increase the fidelity of the Pampero tool while maintaining practical applicability for spacecraft design and certification activities. Preliminary validation and comparative analyses demonstrate improved agreement with high-fidelity reference cases and enhanced capability to evaluate advanced demise-oriented design concepts for future space systems.