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.


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    Title :

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


    Additional title:

    Kohlenstoff-Phenolharz-Materialien für Hitzeschilde an Wiedereintritts-Raumkapseln: Herstellung und Eigenschaften


    Contributors:
    Pulci, G. (author) / Tirillo, J. (author) / Marra, F. (author) / Fossati, F. (author) / Bartuli, C. (author) / Valente, T. (author)


    Publication date :

    2010


    Size :

    8 Seiten, 9 Bilder, 4 Tabellen, 20 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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