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    STP674

    Advanced Material Applications on the Trident I Missile

    Published: 0


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    Abstract

    An in-depth materials study was conducted to improve cost and reliability of the Trident I Missile. This study resulted in the application of composite materials in approximately 65 percent of the vehicle's primary and secondary structures. The materials utilized ranged from laminated sitka spruce, through filament wound motor cases to graphite epoxy woven cloth and injection molded polyphenylene sulfide. In all applications, significant weight savings were achieved over materials used on previous Polaris and Poseidon Missiles.

    Keywords:

    composite materials, advanced composites, filament wound motor cases, pyrolytic graphite carbon nozzles, injection molded materials, weight optimization, reliability, expenses, graphite epoxy


    Author Information:

    Wong, DG
    Manager, Loads, Structures, and Dynamics Department, Missile Systems Division, and supervisor, Vehicle Shell System Section, Missile Structures Department, Lockheed Missiles and Space Company, Inc., Sunnyvale, Calif.

    Vollersen, CA
    Manager, Loads, Structures, and Dynamics Department, Missile Systems Division, and supervisor, Vehicle Shell System Section, Missile Structures Department, Lockheed Missiles and Space Company, Inc., Sunnyvale, Calif.


    Committee/Subcommittee: D30.07

    DOI: 10.1520/STP36899S