A yaw control system (24; 102; 202, 250; 302; 402; 502; 602) for a helicopter (10; 100; 200, 264; 300; 400; 500; 600) having a tailboom includes one or more tail rotors rotatably coupled to the tailboom (20; 106; 206, 268; 306; 406; 506; 606) and a quiet mode controller (68; 240; 336). The quiet mode controller (68; 240; 336) includes a noise monitoring module (68a; 338) configured to monitor one or more flight parameters of the helicopter (10; 100; 200, 264; 300; 400; 500; 600) and a quiet mode command module (68b; 340) configured to selectively switch the one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) to a quiet mode based on the one or more flight parameters. The quiet mode command module (68b; 340) is also configured to modify one or more operating parameters of the one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) in the quiet mode to reduce noise emitted by the helicopter (10; 100; 200, 264; 300; 400; 500; 600).


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    Title :

    ROTORCRAFT QUIET MODES


    Additional title:

    LEISE BETRIEBSARTEN FÜR DREHFLÜGLER
    MODES SILENCIEUX DE GIRAVION


    Contributors:

    Publication date :

    2023-05-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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