AERODYNAMIC AND AEROTHERMODYNAMIC INVESTIGATION FOR AEROSHAPE AND FLYING QUALITIES OF THE ICARUS RE-ENTRY SYSTEM

ICARUS is a project funded by the European Union’s HORIZON EUROPE (HE) program under the grant agreement No 101134997.It targets to bring up to TRL6 the maturation of enabling technologies in the field of re-usable space transportation systems, addressing the innovative re-entry solution based on Inflatable Heat Shields (IHS), deemed applicable for recovery of Launch Vehicles stages.This paper presents the system design of the Aerodemonstrator solution with a particular focus on aeroshape investigation and definition, aerodynamic and aerothermodynamic characterization, flying qualities and static stability assessment. 2D-axisymmetric and 3D CFD simulations have been performed with the ONERA code CEDRE/CHARME on the various aeroshape designs under study, for various flight conditions extracted along referenced flight trajectories and IHS attitude. Low supersonic to hypersonic flows, from Mach 1.41 up to Mach 6.5 (entry velocity), have been yet simulated, assuming turbulent boundary layer. The Aerodynamic Database (AEDB) composed of aerodynamic force and moment coefficients and associated uncertainties from EFESTO-2 HE project legacy, as well as the location of the pressure center have been used to assess the flying qualities analysis.The convective-diffusive heat flux calculated assuming both radiative equilibrium at the wall and/or cold isothermal wall condition are used to size the flexible Thermal Protection System, and guide the choice and positions of sensors (Health Monitoring System Work Package). The obtained results and consecutive analysis, which led our design choices, are discussed in perspective of the IHS aero-demonstrator.