Flight control system is rate plus position multirate sampled-data control system; missile can be launched on moment's notice; control of Minuteman I is achieved by vectoring four nozzles on each of three stages; Minuteman II is controlled by vectoring four nozzles on each of stages one and three and by injecting liquid into exhaust stream of stage two; to control thrust vector throughout boost, control system uses digital computer angular accelerometer, three thrust vector control units, and three digital resolvers. SAE -- Paper 650598.


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    Title :

    Functional design of minuteman flight control system


    Additional title:

    SAE-NASA -- Aerospace Vehicle Flight Control Conference -- Proc


    Contributors:

    Conference:

    Proceedings of the SAE-NASA -- Aerospace Vehicle Flight Control Conference ; 1965 Control



    Publication date :

    1965


    Size :

    10 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Functional Design of the Minuteman Flight Control System

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