System between the Titan/Centaur launch vehicle and its aerodynamic shroud is described. The system provides a precise spring constant and is capable of being inactivated during flight. Design requirements, design details, and the test program are discussed. The conventional English system of units was used during this development program for all principal measurements and calculations.


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    Title :

    Forward bearing reactor mechanism for Titan 3-E/Centaur D-1T space launch vehicle


    Contributors:


    Publication date :

    1975-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English