Investigation of the dynamics of the movement of space descent vehicles in the atmosphere of the planet using modern means of mathematical modeling

For reentry in Mars atmosphere, inflatable braking devices are interesting as they do not use rigid heat shields, parachutes, or retrorockets which limits the mass to send into space. This paper focuses on one MetNet probe, to validate the use of inflatable braking device geometry. This study shows the results on aerodynamic coefficients determined using different solvers from OpenFOAM [9] software in distinct configurations exposing the effect of small deformations of the braking device in the stages of the probe’s reentry. Finally, this study shows final velocity determined using a Python program and compared with expected values on different locations on Mars’s surface.