  A high fidelity multi-physics Eulerian computational framework is presented
for the simulation of supersonic parachute inflation during Mars landing.
Unlike previous investigations in this area, the framework takes into account
an initial folding pattern of the parachute, the flow compressibility effect on
the fabric material porosity, and the interactions between supersonic fluid
flows and the suspension lines. Several adaptive mesh refinement (AMR)-enabled,
large edge simulation (LES)-based, simulations of a full-size disk-gap-band
(DGB) parachute inflating in the low-density, low-pressure, carbon dioxide
(CO2) Martian atmosphere are reported. The comparison of the drag histories and
the first peak forces between the simulation results and experimental data
collected during the NASA Curiosity Rover's Mars atmospheric entry shows
reasonable agreements. Furthermore, a rudimentary material failure analysis is
performed to provide an estimate of the safety factor for the parachute
decelerator system. The proposed framework demonstrates the potential of using
Computational Fluid Dynamics (CFD) and Fluid-Structure Interaction (FSI)-based
simulation tools for future supersonic parachute design.
