This study is dedicated to an innovative heatshield aeroshape intended to be the AEROFAST martian aerocapture demonstrator. The analysis of three representative Mars aerocapture trajectory points (maximum heat flux, maximum dynamic pressure and exit point) results in building a partial AeroThermo-DataBase including both convective and radiative heat flux evaluations carried out assuming CO2 chemical non equilibrium.

Volume Subject Area:
Aerospace Heat Transfer
Topics:
Carbon dioxide, Databases, Equilibrium (Physics), Heat flux, Pressure, Trajectories (Physics), Vehicles
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