Verification and Application of the Sam Re-Entry Model

The objective of the Spacecraft Aerothermal Model (SAM) destructive re-entry code is to provide a tool for the early stages of satellite design which delivers an improved balance between fidelity and performance over existing object and spacecraft oriented algorithms. With an evaluation time measured in minutes for Monte Carlo studies it is rapid enough to use in interactive design studies; whilst the inclusion of a six-degree-of-freedom predictive fragmentation model represents a significant advance over existing object oriented algorithms. This paper outlines the capabilities in SAM, and demonstrates them using a Delta II re-entry test case, providing both a verification against other established re-entry codes and an indication of how SAM can enable improved understanding of the differences between the re-entry codes. This in turn delivers improved understanding of the sensitivities of casualty risk aiding design for demise.