A solid rocket motor comprises a pressure vessel, a solid propellant structure within the pressure vessel, and a flight termination system overlying the pressure vessel. The flight termination system comprises a shaped charge configured and positioned to effectuate ignition of an inner portion of the solid propellant structure and a reduction in an ability of the pressure vessel to withstand a change in internal pressure. Another solid rocket motor, a multi-stage rocket motor assembly, and a method of destroying a launch vehicle in flight are also described.


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    Titel :

    Solid rocket motors including flight termination systems, and related multi-stage solid rocket motor assemblies and methods


    Beteiligte:

    Erscheinungsdatum :

    2020-09-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS




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    BROWNE, T. P. / DAY, E. E. / TABACK, H. J. | AIAA | 1965


    HYBRID METAL COMPOSITE STRUCTURES, ROCKET MOTORS AND MULTI-STAGE ROCKET MOTOR ASSEMBLIES INCLUDING HYBRID METAL COMPOSITE STRUCTURES, AND RELATED METHODS

    GARCIA BENJAMIN W C / CHRISTENSEN BRIAN / NELSON DAVID R et al. | Europäisches Patentamt | 2018

    Freier Zugriff

    Solid rocket motors

    Carpenter, Ronn L. | NTRS | 1993