Roberto SCIGLIANO, Marco MARINI, Sara DI BENEDET TO, Marta ALBANO, Giuliano RANUZZI
DOI Number: 10.60853/htzh-cf74
Conference number: HiSST-2024-00134
In the last decade, international community has shown an increasing interest in civil high-speed aviation. In particular, several studies have been carried out to assess the technical possibility of hypersonic civil flights paying attention at technical, environmental and economic viability in combination with human factors, social acceptance, implementation and operational aspects. In the past years, some innovative high-speed aircraft configurations have been proposed as results of dedicated multi-disciplinary and highly integrated design concept where aerothermodynamic, structural and propulsive issues are evaluated together in the frame of European Commission-supported research projects such as: LAPCAT I/II [1-3], ATLLAS I/II [4], HIKARI, HEXAFLY [5], HEXAFLY-International [6], STRATOFLY [7, 8, 9, 10]. In this context, starting from an in-depth investigation of the status of past and on-going activities, CIRA has launched a national project funded by PRO.R.A. (Aerospace Research Program), aiming at designing, manufacturing and flight-testing a propelled hypersonic demonstrator, namely the Scramjet Hypersonic Experimental Vehicle (SHEV) [11]. The Italian Space Agency (ASI) is also funding the activities for a three-year period. This paper focuses the attention on the preliminary thermal assessment of the experimental flight vehicle mainly from the structure and material point of view.