A thermally initiated variable venting system may comprise a first linear shape charge (LSC) coupled to a first sensor and a second LSC coupled to a second sensor. An upper apex of the second LSC may be disposed within a lower apex of the first LSC. The output of the system may vary depending on whether the event is fast cook-off (FCO) or slow cook-off (SCO).


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    Title :

    Thermally initiated variable venting system for rocket motor


    Contributors:

    Publication date :

    2020-11-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen



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