All long-duration spacecraft in low-earth-orbit are subject to high speed impacts by meteoroids and orbital debris. As a result, the threat of damage from such high-speed impacts is a major design consideration in the development and construction of long duration earth-orbiting spacecraft. Recent studies have shown that the nature of a spacecraft wall perforation can range from a flat hole with a jagged edge (i.e. a so-called cookie-cutter hole) to a hole accompanied by bulging, cracking, and petaling. If a cracking event were to occur on-orbit, unstable crack growth could develop which could lead to an unzipping of the impacted spacecraft module. It is, therefore, imperative to be able to determine whether or not a spacecraft wall perforation will be accompanied by petaling and cracking. This paper presents the results of a study whose objective was to develop an empirical model that could be used to determine whether a spacecraft wall perforation would be in the form of a petaled hole or a cookie-cutter hole. A petaling limit function was developed to predict the onset of petaling in terms of impact conditions and spacecraft wall system geometry.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Onset of petalling in a thin spacecraft wall perforated by an orbital debris particle


    Beteiligte:

    Kongress:

    Image Intensifiers and Applications; and Characteristics and Consequences of Space Debris and Near-Earth Objects ; 1998 ; San Diego,CA,USA


    Erschienen in:

    Proc. SPIE ; 3434 ; 126


    Erscheinungsdatum :

    18.11.1998





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch