A lightweight carbon-phenolic ablator, with a density of 0.5 g/cm3, designed to be used as a thermal protection system for a re-entry space vehicle, was manufactured by infiltration of a carbon felt with a phenolic resin. A sample of this ablative material was tested in a Plasma Wind Tunnel (PWT) facility, simulating erosion and heat flux conditions consistent with an orbital reentry. The surface temperature of the test article was monitored during the PWT test. Microstructural and microtomographic analyses were carried out on the tested sample to investigate the effect of the high heat flux exposure on the composite material, by measuring the amount of ablation and the depth of pyrolyzation. Moreover a finite element model was implemented in order to rebuild the PWT test. Very encouraging results were obtained in terms of surface insulation capacity and surface recession. The pyrolysis and erosion of the ablator was simulated by implementing a complex finite element model, with results in very good agreement with experimental evidences.

Carbon-phenolic ablative materials for re-entry space vehicles: Plasma wind tunnel test and finite element modeling / Paglia, Laura; Tirillo', Jacopo; Marra, Francesco; Bartuli, Cecilia; Simone, A.; Valente, Teodoro; Pulci, Giovanni. - In: MATERIALS & DESIGN. - ISSN 0264-1275. - STAMPA. - 90:(2016), pp. 1170-1180. [10.1016/j.matdes.2015.11.066]

Carbon-phenolic ablative materials for re-entry space vehicles: Plasma wind tunnel test and finite element modeling

PAGLIA, LAURA;TIRILLO', Jacopo;MARRA, FRANCESCO;BARTULI, Cecilia;VALENTE, Teodoro;PULCI, Giovanni
2016

Abstract

A lightweight carbon-phenolic ablator, with a density of 0.5 g/cm3, designed to be used as a thermal protection system for a re-entry space vehicle, was manufactured by infiltration of a carbon felt with a phenolic resin. A sample of this ablative material was tested in a Plasma Wind Tunnel (PWT) facility, simulating erosion and heat flux conditions consistent with an orbital reentry. The surface temperature of the test article was monitored during the PWT test. Microstructural and microtomographic analyses were carried out on the tested sample to investigate the effect of the high heat flux exposure on the composite material, by measuring the amount of ablation and the depth of pyrolyzation. Moreover a finite element model was implemented in order to rebuild the PWT test. Very encouraging results were obtained in terms of surface insulation capacity and surface recession. The pyrolysis and erosion of the ablator was simulated by implementing a complex finite element model, with results in very good agreement with experimental evidences.
2016
Lightweight ablative materials, Plasma Wind Tunnel test, Ablation, Pyrolysis, FE modeling
01 Pubblicazione su rivista::01a Articolo in rivista
Carbon-phenolic ablative materials for re-entry space vehicles: Plasma wind tunnel test and finite element modeling / Paglia, Laura; Tirillo', Jacopo; Marra, Francesco; Bartuli, Cecilia; Simone, A.; Valente, Teodoro; Pulci, Giovanni. - In: MATERIALS & DESIGN. - ISSN 0264-1275. - STAMPA. - 90:(2016), pp. 1170-1180. [10.1016/j.matdes.2015.11.066]
File allegati a questo prodotto
File Dimensione Formato  
Mat&Des 2016 Carbon Pheolic.pdf

solo gestori archivio

Note: paper
Tipologia: Documento in Post-print (versione successiva alla peer review e accettata per la pubblicazione)
Licenza: Tutti i diritti riservati (All rights reserved)
Dimensione 3.03 MB
Formato Adobe PDF
3.03 MB Adobe PDF   Contatta l'autore

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/837697
Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 59
  • ???jsp.display-item.citation.isi??? 44
social impact