A propulsion system for a supersonic aircraft. The propulsion system includes a main gas turbine engine adapted for generating propulsive thrust during subsonic and supersonic flight operations of the aircraft and a supplementary propulsion unit adapted for generating additional propulsive thrust. The supplementary propulsion unit has an air intake and an exhaust for gas accelerated by the supplementary propulsion unit to provide the additional propulsive thrust and is adapted to generate the additional propulsive thrust during a limited range of subsonic flight operations, and to be dormant during other flight operations. The propulsion system also has a housing for the supplementary propulsion unit. The housing includes an intake cover and an exhaust cover which are controllably moveable between deployed and stowed configurations. During the limited range of subsonic flight operations the intake cover and the exhaust cover are moved to the deployed configuration to open the intake and the exhaust. During the other flight operations the intake cover and the exhaust cover are moved to the stowed configuration to close the intake and the exhaust.


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    Title :

    Supersonic aircraft propulsion installation


    Publication date :

    2018-08-29


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English



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