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.
Carbon-phenolic ablative materials for re-entry space vehicles: Manufacturing and properties
Kohlenstoff-Phenolharz-Materialien für Hitzeschilde an Wiedereintritts-Raumkapseln: Herstellung und Eigenschaften
Composites, Part A: Applied Science and Manufacturing ; 41 , 10 ; 1483-1490
2010
8 Seiten, 9 Bilder, 4 Tabellen, 20 Quellen
Article (Journal)
English
Low Temperature Ablative Heat Shield for Re-Entry Vehicles
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