An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.

    L'invention concerne un aéronef comprenant une cellule, une queue qui s'étend, et un ensemble rotor principal coaxial contrarotatif comprenant un ensemble rotor supérieur composé d'une pluralité de pales et un ensemble rotor inférieur composé d'une pluralité de pales. Un système de poussée de translation est positionné au niveau de la queue qui s'étend, le système de poussée de translation fournissant une poussée de translation à la cellule. Un système de pilotage permet de commander l'ensemble rotor supérieur et l'ensemble rotor inférieur, lequel système de pilotage est conçu pour commander le décalage de portance de l'ensemble rotor supérieur et de l'ensemble rotor inférieur.


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    Title :

    LIFT OFFSET CONTROL OF A ROTARY WING AIRCRAFT


    Additional title:

    COMMANDE DE DÉCALAGE DE PORTANCE D'UN AÉRONEF À VOILURE TOURNANTE


    Contributors:

    Publication date :

    2016-08-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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