The Paper describes the activities funded by the Italian Space Agency (ASI) and European Space Agency (ESA) in the IRENE (Italian Re-Entry NacellE) program, an innovative deployable (umbrella-like) heat shield concept developed by ALI S.c.a.r.l.., CIRA and University of Naples. IRENE is a capsule with a variable geometry, “umbrella-like” deployable heat shield that reduces the capsule ballistic coefficient, leading to acceptable heat fluxes, mechanical loads and final descent velocity. The feasibility study of the IRENE has been carried out in 2011. The Thermal Protection System (TPS) materials have been tested in the SPES hypersonic wind tunnel at the University of Naples, and in the SCIROCCO Plasma Wind Tunnel at CIRA in 2011 and in 2018. Thanks to the Italian participation, ESA, ASI, through the funding of the ESA GSTP, is now funding the current phase of the program called MIFE “MINI-IRENE Flight Experiment”. MINI IRENE, the Demonstrator of IRENE, has been designed and manufactured to demonstrate, with a suborbital flight and with a Plasma Wind Tunnel (PWT) test campaign, the functionality of the deployable heat shield. The Flight Demonstrator shall be included as a secondary payload in the interstage adapter of a VSB-30 Sounding Rocket that should be launched from the ESRANGE, Sweden, launch base, then ejected during the ascent phase of the payload section, perform a 15-minutes ballistic flight, re-enter the atmosphere and hit the ground. As an application of IRENE technology, ALI has proposed the “Small Mission to Mars” (SMS) project. SMS is a low-cost system suitable for the entrance in the atmosphere and the operations on the ground of Mars. The SMS feasibility study was funded by the European Space Agency (ESA) in 2016. In the paper are also illustrated the results of the feasibility study of SMS, including a description of the mission profile, launch and escape phases, interplanetary trajectory, Mars approach, entry, descent and landing (EDL), and payload deployment and operations.

Irene technology for thermal protection system / Punzo, F.; Aurigemma, R.; Dell'Aversana, P.; Gramiccia, L.; Spagnulo, M.; Vernillo, P.; Gardi, R.; Fedele, A.; Savino, R.; Grassi, M.; Albano, M.; Iannelli, S.; Ferracina, L.; Roma, I.. - 2020:(2020), pp. 1-14. (Intervento presentato al convegno 71st International Astronautical Congress, IAC 2020 tenutosi a The CyberSpace Edition).

Irene technology for thermal protection system

Gramiccia L.;Spagnulo M.;Fedele A.;Grassi M.;Albano M.;Roma I.
2020

Abstract

The Paper describes the activities funded by the Italian Space Agency (ASI) and European Space Agency (ESA) in the IRENE (Italian Re-Entry NacellE) program, an innovative deployable (umbrella-like) heat shield concept developed by ALI S.c.a.r.l.., CIRA and University of Naples. IRENE is a capsule with a variable geometry, “umbrella-like” deployable heat shield that reduces the capsule ballistic coefficient, leading to acceptable heat fluxes, mechanical loads and final descent velocity. The feasibility study of the IRENE has been carried out in 2011. The Thermal Protection System (TPS) materials have been tested in the SPES hypersonic wind tunnel at the University of Naples, and in the SCIROCCO Plasma Wind Tunnel at CIRA in 2011 and in 2018. Thanks to the Italian participation, ESA, ASI, through the funding of the ESA GSTP, is now funding the current phase of the program called MIFE “MINI-IRENE Flight Experiment”. MINI IRENE, the Demonstrator of IRENE, has been designed and manufactured to demonstrate, with a suborbital flight and with a Plasma Wind Tunnel (PWT) test campaign, the functionality of the deployable heat shield. The Flight Demonstrator shall be included as a secondary payload in the interstage adapter of a VSB-30 Sounding Rocket that should be launched from the ESRANGE, Sweden, launch base, then ejected during the ascent phase of the payload section, perform a 15-minutes ballistic flight, re-enter the atmosphere and hit the ground. As an application of IRENE technology, ALI has proposed the “Small Mission to Mars” (SMS) project. SMS is a low-cost system suitable for the entrance in the atmosphere and the operations on the ground of Mars. The SMS feasibility study was funded by the European Space Agency (ESA) in 2016. In the paper are also illustrated the results of the feasibility study of SMS, including a description of the mission profile, launch and escape phases, interplanetary trajectory, Mars approach, entry, descent and landing (EDL), and payload deployment and operations.
2020
71st International Astronautical Congress, IAC 2020
advanced materials; aerothermodynamics; deployable; re-entry system
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Irene technology for thermal protection system / Punzo, F.; Aurigemma, R.; Dell'Aversana, P.; Gramiccia, L.; Spagnulo, M.; Vernillo, P.; Gardi, R.; Fedele, A.; Savino, R.; Grassi, M.; Albano, M.; Iannelli, S.; Ferracina, L.; Roma, I.. - 2020:(2020), pp. 1-14. (Intervento presentato al convegno 71st International Astronautical Congress, IAC 2020 tenutosi a The CyberSpace Edition).
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1525963
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