Thermal protection systems (TPS) are designed to protect re-entry space vehicles from the severe heating encountered during hypersonic flight through a planet's or the earth's atmosphere. A carbon-phenolic ablative TPS was developed, manufactured and tested with the aim of fulfilling the thermal and mechanical requirements corresponding to the actual loads experienced by a vehicle during a moon-earth re-entry. Experimental activities were carried out on two different composite systems (a resole resin coupled with a graphitic felt and a graphitic foam), and were aimed to the optimization of the manufacturing procedure and to the characterization of the mechanical behaviour and of the insulation performance of the fabricated composites. (c) 2010 Elsevier Ltd. All rights reserved.

Carbon-phenolic ablative materials for re-entry space vehicles: Manufacturing and properties / Pulci, Giovanni; Tirillo', Jacopo; Marra, Francesco; F., Fossati; Bartuli, Cecilia; Valente, Teodoro. - In: COMPOSITES. PART A: APPLIED SCIENCE AND MANUFACTURING. - ISSN 1359-835X. - STAMPA. - 41:10(2010), pp. 1483-1490. [10.1016/j.compositesa.2010.06.010]

Carbon-phenolic ablative materials for re-entry space vehicles: Manufacturing and properties

PULCI, Giovanni;TIRILLO', Jacopo;MARRA, FRANCESCO;BARTULI, Cecilia;VALENTE, Teodoro
2010

Abstract

Thermal protection systems (TPS) are designed to protect re-entry space vehicles from the severe heating encountered during hypersonic flight through a planet's or the earth's atmosphere. A carbon-phenolic ablative TPS was developed, manufactured and tested with the aim of fulfilling the thermal and mechanical requirements corresponding to the actual loads experienced by a vehicle during a moon-earth re-entry. Experimental activities were carried out on two different composite systems (a resole resin coupled with a graphitic felt and a graphitic foam), and were aimed to the optimization of the manufacturing procedure and to the characterization of the mechanical behaviour and of the insulation performance of the fabricated composites. (c) 2010 Elsevier Ltd. All rights reserved.
2010
thermal analysis; cure; heat treatment; foams; high temperature properties; e. cure; a. foams; b. high temperature properties; d. thermal analysis
01 Pubblicazione su rivista::01a Articolo in rivista
Carbon-phenolic ablative materials for re-entry space vehicles: Manufacturing and properties / Pulci, Giovanni; Tirillo', Jacopo; Marra, Francesco; F., Fossati; Bartuli, Cecilia; Valente, Teodoro. - In: COMPOSITES. PART A: APPLIED SCIENCE AND MANUFACTURING. - ISSN 1359-835X. - STAMPA. - 41:10(2010), pp. 1483-1490. [10.1016/j.compositesa.2010.06.010]
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/365864
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