Giuseppe GUIDOTTI, Federico TOSO, Alessandro PRINCI, Jaime BRICENO-GUTIERREZ, Giuseppe GOVERNALE, Nicole VIOLA, Ingrid DIETLEIN, S. Callsen, K. Bergmann, Junnai ZHAI, Thomas GAWEHN, Roberto GARDI, Barbara TISEO, Ysolde PREVEREAUD, Yann DAUVOIS, C. Julien, Giovanni GAMBACCIANI, Giada DAMMACCO, L.Garcia-Basabe
DOI Number: 10.60853/zsmd-9c42
Conference number: HiSST-2024-00217
Inflatable Heat Shields (IHS) are attracting an increased interest in the field of some hypersonic applications as the one of re-entry. In Europe the “ram’s head” project EFESTO, funded by the European Commission through the Horizon 2020 program and run form 2109 and 2021, allowed the scientific community to carry out an early exploration of the potential use of this technology to recover space systems re-entering from LEO (e.g.: launch vehicle stages, satellites, space station elements). ([1] to [3]) In the track-lay of EFESTO, the project EFESTO-2, funded by the EU program Horizon Europe, aims to further increase the European know-how in the field of Inflatable Heat Shields (HIS) and seeks to improve further the Technology Readiness Level (TRL) of IHS. ([4] to [6]) The EFESTO-2 project is built on four pillars: (1) consolidation of use-case applicability through a business case analysis for a meaningful space application; (2) extension of investigation spectrum of the father project EFESTO; (3) increase of confidence-level and robustness of tools/models; (4) consolidation of European leadership among the scientific and industrial community in this specific field. This paper presents the project’s work and achievements up to completion going across its main work items of execution of a mission and system design loop for a reference application in a baseline use-case scenario; implementation of a sound testing effort covering the key aspects of structural characterization of the inflatable structure as well as deformable shape investigation from the aerodynamic standpoint including stability; verification and improvement of numerical models both at structure (FEM) and aero-shape (CFD) levels; identification of the roadmap and near-future effort toward maturation of the IHS technology for a systematic use on real re-entry missions. This project has received funding from the European Union’s Horizon Europe research and innovation program under grant agreement No 1010811041.