A separation mechanism (100) for passive separation of a first spacecraft component (200) from a second spacecraft component (300) comprises a first structural element (10), a second structural element (20) and joining means (30) for mechanically joining the first and second structural elements (10, 20). The first structural element (10) has a receiving hole with an inner first connecting surface (11) and is adapted to be mounted to the first spacecraft component (200). The second structural element (20) is adapted to be at least in part received within the receiving hole of the first structural element (10) and has an outer second connecting surface (21) facing the inner first connecting surface (11) when the second structural element (20) is at least in part received within the receiving hole of the first structural element (10). The second structural element (20) is adapted to be mounted to the second spacecraft component. The joining means (30) is adapted to mechanically join the first and second structural elements (10, 20) together via their first and second connecting surfaces (11, 21). The joining means (30), in a joint state of the passive separation mechanism (100), is sandwiched between and connects the inner first connecting surface (11) and the outer second connecting surface (21) together when the second structural element (20) is at least in part received within the receiving hole of the first structural element (10). The joining means (30) is solder meltable at a temperature in the range of 100°C to 300°C so as to separate the first and second structural elements (10, 20) when a melting temperature, i.e., a temperature in the range of 100°C to 300°C, is experienced by the separation mechanism (100).


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    Title :

    TWO-PART PASSIVE SEPARATION MECHANISM FOR SEPARATION OF TWO SPACECRAFT COMPONENTS DURING THE ATMOSPHERIC RE-ENTRY OF THE SPACECRAFT


    Additional title:

    ZWEITEILIGER PASSIVER TRENNMECHANISMUS ZUR TRENNUNG VON ZWEI RAUMFAHRZEUGKOMPONENTEN WÄHREND DES ATMOSPHÄRISCHEN WIEDEREINTRITTS DES RAUMFAHRZEUGS
    MÉCANISME DE SÉPARATION PASSIF EN DEUX PARTIES POUR SÉPARER DEUX COMPOSANTS D'ENGINS SPATIAUX PENDANT LA RENTRÉE ATMOSPHÉRIQUE DE L'ENGIN SPATIAL


    Contributors:

    Publication date :

    2024-12-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS




    Spacecraft Disintegration During Uncontrolled Atmospheric Re-Entry

    Fritsche, B. / Roberts, T. / Romay, M. et al. | British Library Online Contents | 1997



    Spacecraft disintegration during uncontrolled atmospheric re-entry

    Fritsche, B. / Klinkrad, H. / Kashkovsky, A. et al. | British Library Conference Proceedings | 2000


    SPACECRAFT SEPARATION SYSTEM

    VORONIN EVGENIJ ALEKSANDROVICH / GREBNEV NIKOLAJ EGOROVICH / KRUGLOV GENRIKH EVGEN EVICH et al. | European Patent Office | 2015

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