Use of auxiliary rudders for yaw control at low speed
First Claim
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 the cabin portion away therefrom,a first vertical stabilizer mounted to the empennage,a first rudder secured to pivot with respect to the first vertical stabilizer, anda horizontal stabilizer connected to the empennage;
a rotor rotatably mounted to the tower to rotate about an axis of rotation offset from the first vertical stabilizer and the horizontal stabilizer;
a propulsion source mounted to the airframe and directing air flow across the vertical stabilizer;
a first auxiliary rudder mounted to the horizontal stabilizer and spaced from the first vertical stabilizer; and
a controller receiving yaw control inputs from a pilot and selectively actuating the first auxiliary rudder in response to the yaw control inputs exclusively at airspeeds of the rotorcraft below an airspeed threshold and actuating the first rudder without actuating the first auxiliary rudder in response to the yaw control inputs at airspeeds of the rotorcraft above the airspeed threshold.
12 Assignments
0 Petitions
Accused Products
Abstract
Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.
-
Citations
20 Claims
-
1. A rotorcraft comprising:
-
an airframe including a 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 the cabin portion away therefrom, a first vertical stabilizer mounted to the empennage, a first rudder secured to pivot with respect to the first vertical stabilizer, and a horizontal stabilizer connected to the empennage; a rotor rotatably mounted to the tower to rotate about an axis of rotation offset from the first vertical stabilizer and the horizontal stabilizer; a propulsion source mounted to the airframe and directing air flow across the vertical stabilizer; a first auxiliary rudder mounted to the horizontal stabilizer and spaced from the first vertical stabilizer; and a controller receiving yaw control inputs from a pilot and selectively actuating the first auxiliary rudder in response to the yaw control inputs exclusively at airspeeds of the rotorcraft below an airspeed threshold and actuating the first rudder without actuating the first auxiliary rudder in response to the yaw control inputs at airspeeds of the rotorcraft above the airspeed threshold. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
-
-
11. A rotorcraft comprising:
-
an airframe including first and second vertical stabilizers mounted to the airframe, each of the first and second horizontal stabilizers having a rudder mounted thereto, and a horizontal stabilizer mounted to the airframe between the first and second vertical stabilizers; a rotor rotatably mounted to the airframe and rotatable about an axis of rotation, the axis of rotation offset from the horizontal stabilizer and first and second vertical stabilizers; a propulsion system mounted to the airframe and oriented to direct air flow over the vertical stabilizer, the propulsion system defining a stream tube; an auxiliary rudder mounted to the horizontal stabilizer positioned between the first and second vertical stabilizers; and a controller programmed to receive yaw control inputs from a pilot and to actuate the auxiliary rudder in response to the yaw control inputs only for airspeeds of the rotorcraft below an airspeed threshold. - View Dependent Claims (12, 13, 14, 15)
-
-
16. A rotorcraft comprising:
-
an airframe including a cabin portion supporting flight controls and a seat to receive a pilot, a tower portion fixed to the cabin portion and extending upward therefrom, first and second empennages extending from proximate the cabin portion away therefrom, first and second vertical stabilizers mounted to the first and second empennages, respectively, first and second rudders secured to pivot with respect to the first and second vertical stabilizers, respectively, and a horizontal stabilizer connected to extend between the first and second empennages; a rotor, rotatably mounted to the tower to rotate about an axis of rotation offset from the horizontal stabilizer and the first and second vertical stabilizers; a propulsion source mounted to the airframe and directing air flow across the horizontal stabilizer; a first auxiliary rudder mounted to the horizontal stabilizer and spaced from the first and second vertical stabilizers; and a controller receiving yaw control inputs from the pilot and selectively actuating the first auxiliary rudder in response to the yaw control inputs exclusively at airspeeds of the rotorcraft below an airspeed. - View Dependent Claims (17, 18, 19, 20)
-
Specification