This invention pertains to a solid rocket propellant grain which contains hydroxyl terminated polybutadiene and is bonded to a rocket motor liner which contains carboxy terminated polybutadiene. This is done by carrying out the following sequence of steps: First, the liner is cast and cured; then the liner is coated with a solution of a bromine terminated phenol-formaldehyde copolymer which uses normal hexane as the solvent; next, the coat is allowed to dry for from about 15 to about 30 minutes; finally, the propellant grain is cast and cured.


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    Titel :

    Method for Bonding a Rocket Motor Liner to a Solid Rocket Propellant Grain


    Beteiligte:
    G. F. Sieg (Autor:in) / H. W. Gerrish (Autor:in) / J. D. Braun (Autor:in) / M. F. Pickett (Autor:in)

    Erscheinungsdatum :

    1971


    Format / Umfang :

    3 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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