초록 ▼

A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the air-craft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift durin

A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the air-craft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash.

대표청구항 ▼

1. A tiltrotor aircraft, comprising: a fuselage;a first wing member attached to the fuselage;a second wing member attached to the fuselage;a first nacelle that is rotatable relative to the first wing member, the first nacelle having: an inboard section coupled to the first wing member; andan outboar

1. A tiltrotor aircraft, comprising: a fuselage;a first wing member attached to the fuselage;a second wing member attached to the fuselage;a first nacelle that is rotatable relative to the first wing member, the first nacelle having: an inboard section coupled to the first wing member; andan outboard section;a second nacelle that is rotatable relative to the second wing member, the second nacelle having: an inboard section coupled to the second wing member; andan outboard section;a first wing extension coupled to the outboard section of the first nacelle, the first wing extension having a flap; anda second wing extension coupled to the outboard section of the second nacelle the second wing extension having a flap;wherein the first wing extension is pivotally coupled to the outboard section of the first nacelle. 2. The tiltrotor aircraft according to claim 1, wherein the first wing extension is coupled to the outboard section of the first nacelle, so as to provide yaw control when the tiltrotor aircraft is in a helicopter mode. 3. The tiltrotor aircraft according to claim 1, wherein the tiltrotor aircraft is a quad-tiltrotor aircraft. 4. The tiltrotor aircraft according to claim 3, wherein the quad-tiltrotor aircraft comprises: four wing extensions in total. 5. A tiltrotor aircraft, comprising: a fuselage;a first nacelle that is rotatable relative to a first wing member, the first nacelle having: an inboard section coupled to the first wing member; andan outboard section;a second nacelle that is rotatable relative to a second wing member, the second nacelle having: an inboard section coupled to the second wing member; andan outboard section;a first rotor assembly supported by the first nacelle;a second rotor assembly supported by the second nacelle;a first wing extension coupled to the outboard section of the first nacelle the first wing extension having a flap; anda second wing extension coupled to the outboard section of the second nacelle the second wing extension having a flap;wherein the first wing extension is pivotally coupled to the outboard section of the first nacelle. 6. The tiltrotor aircraft according to claim 5, wherein the tiltrotor aircraft is a quad-tiltrotor aircraft. 7. The tiltrotor aircraft according to claim 6, wherein the quad-tiltrotor aircraft comprises: four wing extensions in total. 8. A method for controlling yaw movement of an aircraft, comprising: providing the tiltrotor aircraft of claim 5;rotating the first and second rotor assemblies such that rotorwash is created;pivotally rotating the first and second wing extensions in the rotorwash, thereby at least partially controlling yaw movement of the aircraft during helicopter mode; andproviding a pivot joint coupled to the first nacelle and first wing extension. 9. The method according to claim 8, wherein the helicopter mode is achieved by positioning the nacelle in a position for vertical take-off and landing. 10. The method according to claim 8, wherein pivotally rotating the first wing extension is achieved by rotating the first wing extension about the pivot joint, such that the first wing extension chord is positioned at an angle relative to the rotor axis of rotation.