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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

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


    Weitere Titelangaben:

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


    Beteiligte:
    Pulci, G. (Autor:in) / Tirillo, J. (Autor:in) / Marra, F. (Autor:in) / Fossati, F. (Autor:in) / Bartuli, C. (Autor:in) / Valente, T. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2010


    Format / Umfang :

    8 Seiten, 9 Bilder, 4 Tabellen, 20 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




    Ablative heat shields for planetary entry vehicles.

    Sparhawk, H. E. / Strauss, E. L. | NTRS | 1968


    Low Temperature Ablative Heat Shield for Re-Entry Vehicles

    Nathan, R. P. / Bindu, S. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2005



    Defining Ablative Thermal Protection System Margins for Planetary Entry Vehicles

    Wright, Michael / Cozmuta, Ioana / Laub, Bernard et al. | AIAA | 2011