Technical emphasis was placed on characterization of a scaled-up batch of the improved propellant formulation and determination of the effects of dry heat sterilization on propellant integrity and structural response. The grain stress analysis was directed toward tailoring a fully-bonded grain to the calculated propellant allowable stresses and investigating various bond release concepts to relieve stresses incurred in thermal shrinkage following sterilization.


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    Titel :

    Demonstration of a sterilizable solid rocket motor system, addendum


    Beteiligte:
    Depree, D. O. (Autor:in) / Lambert, W. L. (Autor:in)

    Erscheinungsdatum :

    1971-12-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :