Numerical investigation of RCS jet interaction and plume impingement for Mars precision landing

Mars exploration represents one of the most appealing research focus within robotic space exploration plans of Europe. Indeed, the possibility to operate on ground, collect rocks and dust samples, and transfer them to Earth would be extremely important since more complex analysis are allowed in laboratory. To this aim, the need of precision landing on Mars is mandatory. In this framework, the present research effort deals with the aerodynamic and aerothermodynamic analysis of the interactions between the flowfield past the entry capsule and the plumes of the thruster of the reaction control system. This interaction has been simulated in the trajectory points of Mars entry corresponding to the foreseen bank reverse manoeuvres of capsule, at hypersonic and supersonic flight conditions where the maximum jet interaction and plume impingement is expected. The CFD analyses have been focused on global aerodynamic coefficients and on the flow field structure in the region affected by thruster jets. In particular, in the hypersonic conditions the effect of the thermal non-equilibrium on the main parameters has been evaluated, while in the supersonic case the influence of laminar and turbulent assumption has been assessed.