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USE OF AUXILIARY RUDDERS FOR YAW CONTROL AT LOW SPEED

  • US 20120104156A1
  • Filed: 10/27/2011
  • Published: 05/03/2012
  • Est. Priority Date: 11/02/2010
  • Status: Active Grant
First Claim
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1. A rotorcraft comprising:

  • an airframe includinga cabin portion supporting flight controls and a seat to receive a pilot,a tower portion fixed to the cabin portion and extending upward therefrom,an empennage extending from proximate the cabin portion away therefrom,a first horizontal stabilizer mounted to the empennage, a first rudder secured to pivot with respect to the first horizontal stabilizer, anda vertical stabilizer connected to the empennage;

    a rotor rotatably mounted to the tower to rotate about an axis of rotation offset from the vertical stabilizer and first horizontal stabilizer;

    a propulsion source mounted to the airframe and directing air flow across the vertical stabilizer;

    a first auxiliary rudder mounted to the vertical stabilizer and spaced from the first horizontal stabilizer; and

    a controller receiving yaw control inputs from a pilot and selectively actuating the auxiliary rudders in response to the yaw control inputs exclusively at airspeeds of the rotorcraft below an airspeed threshold.

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