Detail design studies of critical prop/rotor aircraft components are summarized. The program objective is to determine design criteria and demonstrate the adequacy of technology by designing a full-scale prop/rotor aircraft and by designing, manufacturing and testing scaled models. Thirty percent of the weight empty components of the aircraft consisting of the wing, nacelle support and tilt mechanism, nacelle truss, prop/rotor hub, controls and blades was designed in this phase. The weight empty of the aircraft decreased by one to five percent from the target value established in the Phase I studies. Weight increases in the nacelle and tilting mechanism components were offset by substantial weight decreases in the rotor and hub components. Supporting technology studies in the areas of stability and control and aeroelastic stability requirements are also included. Discussed are the primary control system, rotor feedback system and power management system and aircraft flutter and vibration suppression considerations. (Author)


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    Titel :

    Detail Design of Critical Components for a Prop/Rotor Aircraft


    Beteiligte:
    D. A. Richardson (Autor:in) / J. Liiva (Autor:in) / R. R. Pruyn (Autor:in) / R. W. Sandford (Autor:in) / G. Miliziano (Autor:in)

    Erscheinungsdatum :

    1970


    Format / Umfang :

    390 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Configuration Design Analysis of a Prop/Rotor Aircraft

    D. A. Richardson / J. Liiva | NTIS | 1970



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