A tiltrotor aircraft (10) has a fuselage (12) and a wing (18) having upper and lower surfaces (18a-b) with a plurality of channels (56a-d) extending therebetween, each with a cycloidal rotor (28a-h) mounted therein. At least two pylon assemblies (22a-b) are rotatably coupled to the wing (18) to selectively operate the tiltrotor aircraft (10) between helicopter and airplane flight modes. Each pylon assembly (22a-b) includes a mast (54) and a proprotor assembly (24a-b) operable to rotate with the mast (54) to generate thrust. At least one engine (40) provides torque and rotational energy to the proprotor assemblies (24a-b) and the propulsion assemblies. Each of the cycloidal rotors (28a-h) has a plurality of blades (108) that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor (28a-h) is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.


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    Title :

    TILTROTOR AIRCRAFT HAVING VERTICAL LIFT AND HOVER AUGMENTATION


    Additional title:

    KIPPROTORFLUGZEUG MIT ZUSÄTZLICHEM AUFTRIEB IN SCHWEBEN UND VERTIKALEM FLUGMODUS
    AÉRONEF À ROTORS BASCULANTS PRÉSENTANT UNE AUGMENTATION DE POUSSÉE POUR LE VOL STATIONNAIRE ET VERTICAL



    Publication date :

    2019-07-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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