A method has been developed to design a propellant stress relief groove (SRG) for solid rocket motors. The method considers a time-dependent pressure distribution in both burn-back and 'burn-forward' analyses and allows a desired bondline stress condition to be incorporated into the SRG design. Application of the method to obtain an improved propellant SRG for the Titan IV Solid Rocket Motor Upgrade (SRMU) is illustrated in this report. The improved propellant SRG obtained from this method for the Titan IV SRMU provides significant enhancement in the propellant structural margin of safety throughout motor firing. Titan IV solid rocket motor, Propellant, Stress analysis.


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    Titel :

    Propellant Stress Relief Groove for the Titan IV SRMU


    Beteiligte:
    I. S. Chang (Autor:in)

    Erscheinungsdatum :

    1993


    Format / Umfang :

    32 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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