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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    Titel :

    Functional design of minuteman flight control system


    Weitere Titelangaben:

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


    Beteiligte:
    Andreosky, E. (Autor:in)

    Kongress:

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



    Erscheinungsdatum :

    1965


    Format / Umfang :

    10 pages


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Functional Design of the Minuteman Flight Control System

    Andreosky, Eugene | SAE Technical Papers | 1965


    Minuteman

    Pike, I. | Engineering Index Backfile | 1963



    Minuteman missile transportation system

    Drakeley, G.T. | Engineering Index Backfile | 1961