Ablative materials represent a widespread solution for shielding space vehicles from overheating during a reentry phase in atmosphere where the high heating fluxes and the consequent high temperatures cannot be compatible with the vehicle structure and with the safety of the payload and/or the crew. In this work, two different kinds of carbon-phenolic ablators with a density of 0.3 g/cm3 were manufactured and their mechanical and thermal properties were experimentally evaluated. The thermal protection performances of the developed ablators were assessed in a hypersonic plasma wind tunnel facility, setting representative enthalpy and heat flux conditions (6 and 13 MW/m2), consistent with atmospheric reentry missions from high energy orbits. Data of the experimental tests were compared with the results obtained by a finite element model built up for these materials with the commercial software SAMCEF Amaryllis. All results enlighten the good performances of the ablators under severe heat flux conditions and outline their operating limits.

Design of new carbon-phenolic ablators. Manufacturing, plasma wind tunnel tests and finite element model rebuilding / Paglia, L.; Genova, V.; Tirillò, J.; Bartuli, C.; Simone, A.; Pulci, G.; Marra, F.. - In: APPLIED COMPOSITE MATERIALS. - ISSN 0929-189X. - 28:5(2021), pp. 1675-1695. [10.1007/s10443-021-09925-8]

Design of new carbon-phenolic ablators. Manufacturing, plasma wind tunnel tests and finite element model rebuilding

Paglia L.
;
Genova V.
Secondo
;
Bartuli C.;Pulci G.
Penultimo
;
Marra F.
Ultimo
2021

Abstract

Ablative materials represent a widespread solution for shielding space vehicles from overheating during a reentry phase in atmosphere where the high heating fluxes and the consequent high temperatures cannot be compatible with the vehicle structure and with the safety of the payload and/or the crew. In this work, two different kinds of carbon-phenolic ablators with a density of 0.3 g/cm3 were manufactured and their mechanical and thermal properties were experimentally evaluated. The thermal protection performances of the developed ablators were assessed in a hypersonic plasma wind tunnel facility, setting representative enthalpy and heat flux conditions (6 and 13 MW/m2), consistent with atmospheric reentry missions from high energy orbits. Data of the experimental tests were compared with the results obtained by a finite element model built up for these materials with the commercial software SAMCEF Amaryllis. All results enlighten the good performances of the ablators under severe heat flux conditions and outline their operating limits.
2021
bending test; carbon-phenolic ablative materials; finite element analysis; plasma wind tunnel test; specific heat
01 Pubblicazione su rivista::01a Articolo in rivista
Design of new carbon-phenolic ablators. Manufacturing, plasma wind tunnel tests and finite element model rebuilding / Paglia, L.; Genova, V.; Tirillò, J.; Bartuli, C.; Simone, A.; Pulci, G.; Marra, F.. - In: APPLIED COMPOSITE MATERIALS. - ISSN 0929-189X. - 28:5(2021), pp. 1675-1695. [10.1007/s10443-021-09925-8]
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1624947
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