A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses. The spring is coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass. The spring housing is affixed to the first endmass, a first end of the spring being affixed to the spring housing, and tether are affixed to spring at one end and to the second endmass at the other end. A pretensioned loop holds the endmasses abuttingly together, and a burnwire release mechanism cuts the loop to deploy the spring. Upon deployment, the spring extends to its full length to form a cylindrical boom, and the endmasses continue to move outward along the spring centerline until stopped by the tether.


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    Titel :

    Separation system and burn wire release mechanism for tethered spacecraft


    Beteiligte:
    COFFEY SHANNON (Autor:in) / CARROLL JOSEPH A (Autor:in) / OPPENHEIMER PAUL (Autor:in) / SCHLATER JORDAN R (Autor:in) / GALYSH IVAN (Autor:in) / LEVIN EUGENE (Autor:in) / HOGAN CURT (Autor:in) / THURN ADAM (Autor:in)

    Erscheinungsdatum :

    23.04.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / B26F Perforieren , PERFORATING



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