Aircraft attitude controller 150 controls the attitude of an aircraft by controlling winglet or wingtip 120 at distal end 112 of wing portion 110 of a wing of an aircraft. The controller obtains information representative of an attitude of an aircraft and, on the basis of the information, actively controls a position of the winglet or wingtip to control an angle of incidence of the winglet. The attitude of the aircraft may comprise a pitch and/or an angle of attack of the aircraft. The winglet may rotate about axis of rotation 123 relative to the wing portion, the axis oriented at a non-zero toe angle to a vertical plane that includes a longitudinal axis of the aircraft. The information may comprise a pitch, angle of attack, speed, drag, mass, mass distribution, centre of gravity, amount of fuel, fuel consumption, or efficiency of the aircraft. The information may be obtained via sensor system 160 including fuel sensors.


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    Title :

    Aircraft attitude controller and wing system


    Contributors:

    Publication date :

    2024-03-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge



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