A capable, supersonic, Short Take-Off, Vertical Landing (STOVL) tactical combat fighter aircraft must have a highly integrated engine and airframe. Vertical landing and short takeoff with powered lift require dividing engine flow between front and rear nozzles for resultant thrust through the aircraft center of gravity. This defines the engine location, nozzles and cycle bypass ratio, which influences aircaft supersonic drag, engine fuel consumption and dry engine thrust. In jet borne flught, the aircraft pitch, roll, yaw and altitude control must be provided by modulation of front and rear exhaust thrust and compressor bleed. This aircraft control in hover dictates engine thrust, control schedules and response. Satisfying these demands is challenging, but good solution are being found in ongoing design studies initiated September 1986 by NASA and DOD. Even though a bypass ratio of about 1.0 is needed for hover thrust balance, emerging engine technologies allow fan pressure ratios of 4 to 5. Resulting high pressures in front ducts and nozzles minimize frontal area, provide high specific thrust and reduct fuel consumption for high combat thrust levels. New materials and structural concepts reduce the weight of aircraft, engines and vectoring STOVL nozzles. Digital electronic controls enable the necessary integration of propulsion flight controls.


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    Titel :

    STOVL engine/airframe integration


    Weitere Titelangaben:

    STOVL Antrieb/Flugzeugintegration


    Beteiligte:
    Bucknell, R.L. (Autor:in)

    Erschienen in:

    AIAA-Papers ; Jul ; 1-5


    Erscheinungsdatum :

    1987


    Format / Umfang :

    5 Seiten, 7 Bilder, 2 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch