An attempt was made to construct a model launch vehicle for geostationary satellites. A synthetic procedure and techniques of designing the flight control system for the boost stage of this class of vehicles, and the characteristics of the prototype of the model SS-3, are given. Data cover: (1) the derivation of relating equations, (2) the system characterization with the aid of trajectory simulations, (3) the computing methods for flexible vehicle stabilization, and (4) the methods for calculating loads on the vehicle by the effects of the wind. The computer programs for drawing Nyquist plot, Bode plot, and root locus of a high order system with multiple feedback loops were worked out and used for vehicle stabilization (Author)


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    Title :

    Flight Control System Design for Launch Vehicles with Liquid Propellant


    Contributors:
    H. Mori (author) / H. Koshiishi (author)

    Publication date :

    1972


    Size :

    41 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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