In an effort by the National Aeronautics and Space Administration (NASA), hypervelocity impact tests were performed on thermal protection systems (TPS) applied on the external surfaces of reusable launch vehicles (RLV) to determine the potential damage from orbital debris impacts. Three TPS types were tested, bonded to composite structures representing RLV fuel tank walls. The three heat shield materials tested were Alumina-Enhanced Thermal Barrier-12 (AETB-12), Flexible Reusable Surface Insulation (FRSI), and Advanced Flexible Reusable Surface Insulation (AFRSI). Using this test data, predictor equations were developed for the entry hole diameters in the three TPS materials, with correlation coefficients ranging from 0.69 to 0.86. Possible methods are proposed for approximating damage occurring at expected orbital impact velocities higher than tested, with references to other published work.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Orbital Debris Impact Damage to Reusable Launch Vehicles


    Beteiligte:
    J. H. Robinson (Autor:in)

    Erscheinungsdatum :

    1998


    Format / Umfang :

    12 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





    Orbital Debris Control Provisions Launch Vehicles

    Loftus, J. P. / International Astronautical Federation | British Library Conference Proceedings | 1994



    Reusable launch vehicles

    Osmun, W.G. | Engineering Index Backfile | 1964


    Reusable launch vehicles

    DrDr Ruppe, H.O. | Elsevier | 1985