Roberto Fauci, Marco Marini, Francesco Di Caprio, Mario De Stefano Fumo, Pietro Catalano, Giovanni Andreutti, Antonio Schettino

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-0272

The present paper summarizes the results of a feasibility study aimed at identifying a possible reference configuration of an unmanned space re-entry vehicle, class 2500 Kg (i.e. IXV, SPACE RIDER like), equipped with a deployable wing Sub-system. The activities have been performed in the framework of CIRA USV3 Deployable Wing System project. The scope of the project is the development of key technologies for future re-entry space vehicle configurations, enabling civil in-orbit experimentation, demonstration and scientific missions, with subsequent return from orbit, and finally safely landing for following refurbishment, and re-use. The main outcomes are discussed and in particular they refer to the aerodynamic and aerothermodynamic performance, concept design for deployable wing subsystem and thermal protection subsystems are presented.

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In Categories: High-Speed Missions and Vehicles, HiSST 2022
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