According to the present invention, a device for a variable and adaptable diverterless bump inlet is presented. The diverterless bump inlet is an engine inlet typically used in high speed aircraft to generate a shock in order to compress the airflow and to divert the low-energy forebody boundary layer, thus preventing most of this forebody boundary layer from being ingested into the engine air intake. Due to the absence of conventional boundary layer diverters radar visibility of the aircraft is considerably reduced. The fixed-geometry diverterless bump inlet presents a disadvantage of being inefficient at off-design operating conditions. The presented engine inlet of an aircraft comprises a flexible inlet, a mechanism to change the shape of the flexible inlet, and a processing unit to control the mechanism. The flexible inlet of the device includes plurality of edges attached partly to a fuselage skin and partly to an engine inlet duct. With this device, the shape of the flexible inlet can be controlled according to the flight conditions, and hence the engine air intake will perform more efficient at all speeds while fulfilling the requirements for less radar visibility.


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    Title :

    VARIABLE AND ADAPTABLE DIVERTERLESS BUMP INLET


    Additional title:

    VARIABLER UND ANPASSBARER UMLENKUNGSLOSER HÖCKEREINLASS
    ENTRÉE DE BOSSE SANS INVERSEUR ADAPTABLE ET VARIABLE


    Contributors:

    Publication date :

    2022-11-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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