초록 ▼

A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an unders

A retractable chine assembly includes at least one chine which is hingebly mountable to a surface such as of an aircraft having a wing. The chine is preferably configured to be movable between stowed and deployed positions. The aircraft may include an engine nacelle which may be mounted on an underside of the wing. The nacelle may generate a nacelle wake that passes over the wing upper surface at high angles of attack and induces flow separation. The chine is preferably configured such that a vortex generated thereby interacts which the nacelle wake to delay flow separation and stall.

대표청구항 ▼

1. A retractable chine assembly for an aircraft including an engine nacelle and a wing having a wing upper surface, the chine assembly comprising: at least one chine hingedly mounted on an inboard side of the engine nacelle;wherein:the chine is configured to be movable between stowed and deployed po

1. A retractable chine assembly for an aircraft including an engine nacelle and a wing having a wing upper surface, the chine assembly comprising: at least one chine hingedly mounted on an inboard side of the engine nacelle;wherein:the chine is configured to be movable between stowed and deployed positions;the chine generating a vortex passing over the wing upper surface and interacting with a wake generated by the nacelle in a manner increasing wing lift. 2. The retractable chine assembly of claim 1 wherein: the chine is disposable against the engine nacelle when in the stowed position. 3. The retractable chine assembly of claim 1 wherein: the chine is sized and positioned such that the vortex delays wing flow separation. 4. The retractable chine assembly of claim 1 wherein: the engine nacelle has a side surface defining a contour;the chine being contoured to substantially match the contour of the side surface when the chine is in the stowed position. 5. The retractable chine assembly of claim 1 wherein: the aircraft wing defines an angle of attack;the chine being configured to be moved to the deployed position when the angle of attack reaches a predetermined level. 6. The retractable chine assembly of claim 1 further comprising: an actuating mechanism for moving the chine between the stowed and deployed positions;the actuating mechanism including at least one of the following: hydraulic actuator, pneumatic actuator, electromechanical actuator, shape memory alloy device. 7. An aircraft having a wing and an engine nacelle, comprising: a retractable chine assembly, including: at least one chine hingedly mounted on an inboard or outboard side of the engine nacelle;wherein:the chine is configured to be movable between stowed and deployed positions;the chine generating a vortex passing over the wing upper surface and interacting with a wake generated by the nacelle in a manner increasing wing lift. 8. The aircraft of claim 7 wherein: the chine is disposable against the engine nacelle when in the stowed position. 9. The aircraft of claim 7 wherein: the wing is swept in at least one of rearwardly and forwardly swept directions. 10. The aircraft of claim 7 wherein: the chine is sized and positioned such that the vortex delays wing flow separation. 11. The aircraft of claim 7 wherein: the engine nacelle has a side surface defining a contour;the chine being contoured to substantially match the contour of the side surface when the chine is in the stowed position. 12. The aircraft of claim 7 wherein: the wing defines an angle of attack;the chine being configured to be moved to the deployed position when the angle of attack reaches a predetermined level. 13. The aircraft of claim 7 wherein: the aircraft has at least one leading edge device mounted adjacent the wing leading edge and being outwardly extendable therefrom;the leading edge device being disposable against the wing;the chine being configured to be movable from the stowed position to the deployed position when the leading edge device is extended outwardly from the wing by a predetermined amount. 14. The aircraft of claim 13 wherein: the leading edge device being configured as an extendable slat;the slat and wing collectively defining a slot therebetween when the slat is extended;the chine being configured to be movable from the stowed position to the deployed position when the slat is extended. 15. The aircraft of claim 13 further comprising: an actuating mechanism for moving the chine between the stowed and deployed positions;the actuating mechanism including at least one of the following: hydraulic actuator, pneumatic actuator, electromechanical actuator, shape memory alloy device. 16. A method of operating a chine hingedly mounted to an engine nacelle of an aircraft having an a wing upper surface, comprising the steps of: moving the chine between a deployed position and a stowed position;generating a vortex using the chine; andpassing the vortex over the wing upper surface and interacting with a wake generated by the engine nacelle in a manner increasing wing lift. 17. The method of claim 16 wherein the aircraft has a wing defining an angle of attack, the method further comprising the step of: detecting the angle of attack; andmoving the chine from the stowed position to the deployed position when the angle of attack reaches a predetermined level. 18. The method of claim 16 further comprising the step of: biasing the chine toward the deployed position;deploying the chine;locking the chine in the deployed position; andresetting the chine in the stowed position.