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Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes an airfoil having an external flow surface with an upper portion and a lower portion, and with the airfoil

Link mechanisms, including Stephenson II link mechanisms for multi-position flaps and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes an airfoil having an external flow surface with an upper portion and a lower portion, and with the airfoil forming a base link. The system further includes a six-bar linkage coupled to the airfoil and having a Stephenson II configuration, including a binary second link pivotably connected to the airfoil, a ternary third link pivotably connected to the second link, a binary fourth link pivotably connected to the third link, a ternary fifth link pivotably connected to the airfoil and the fourth link, and a binary sixth link pivotably connected to the third link and the fifth link. The system can further include a deployable leading edge panel carried by the linkage, with the leading edge panel being movable via the linkage between a stowed position and at least one deployed position.

대표청구항 ▼

1. An aircraft system, comprising: an airfoil having an external flow surface, the external flow surface comprising an upper portion and a lower portion, the airfoil forming a base link;a six-bar linkage coupled to the airfoil and having a configuration that includes: a binary second link pivotably

1. An aircraft system, comprising: an airfoil having an external flow surface, the external flow surface comprising an upper portion and a lower portion, the airfoil forming a base link;a six-bar linkage coupled to the airfoil and having a configuration that includes: a binary second link pivotably connected to the airfoil at a first location;a ternary third link pivotably connected to the second link;a binary fourth link pivotably connected to the third link;a ternary fifth link pivotably connected to the fourth link and pivotably connected to the airfoil at a second location, the first and second locations being fixed relative to each other; anda binary sixth link pivotably connected to the third link and the fifth link; anda deployable leading edge panel carried by the linkage, the leading edge panel being movable via the linkage between a stowed position and at least one deployed position. 2. The system of claim 1 wherein the fifth link is pivotably connected to the airfoil at the second location forward of the first location, and wherein the system further comprises an ice protection airflow duct positioned between the first and second locations. 3. The system of claim 1 wherein the fifth link is pivotably connected to the airfoil at the second location forward of the first location, and wherein the system further comprises an ice protection airflow duct positioned forward of the second location. 4. The system of claim 1 wherein the leading edge panel forms a part of the lower portion when in the stowed position. 5. The system of claim 1 wherein the at least one deployed position includes a landing position and a take-off position, and wherein the leading edge panel (a) forms a part of the lower portion when in the stowed position, (b) has a trailing edge that is spaced apart from the upper portion to form a gap when in the landing position, and (c) seals the gap when in the take-off position. 6. The aircraft system of claim 1, further comprising: an actuator coupled to the linkage;a controller coupled to the actuator; anda selector coupled to the controller and changeable among multiple selectable positions to which the leading edge panel can be deployed, wherein the controller controls the actuator to move the leading edge panel to a selected position based on input from the selector. 7. The system of claim 1 wherein the leading edge panel is fixedly carried by the fourth link. 8. The system of claim 1 wherein the leading edge panel is pivotable relative to the fourth link. 9. The system of claim 8 wherein the leading edge panel is carried by a panel support member, and wherein the panel support member is pivotably connected to the third link. 10. The system of claim 9, further comprising a bullnose pivotably coupled to the leading edge panel, and wherein: the leading edge panel is flexible and changes shape as the leading edge panel moves from the stowed position to the at least one deployed position; andthe panel support member is pivotably coupled to the bullnose. 11. The system of claim 9, further comprising: a bullnose pivotably coupled to the leading edge panela support panel pivotably coupled to the leading edge panel, the bullnose, and the third link; anda seventh link pivotably connected between the support panel and the fifth link; wherein: the at least one deployed position includes a landing position and a take-off position;the leading edge panel (a) forms a part of the lower portion when in the stowed position, (b) has a trailing edge that is spaced apart from the upper portion to form a gap when in the landing position, and (c) at least partially seals the gap when in the take-off position; andthe leading edge panel is flexible and changes shape as the leading edge panel moves from the stowed position to at least one of the landing position and the take-off position. 12. An aircraft system comprising: a fuselage;a wing attached to the fuselage, the wing having an external flow surface, the external flow surface comprising an upper portion and a lower portion, the airfoil forming a base link;a six-bar linkage coupled to the airfoil and having a configuration that includes: a binary second link pivotably connected to the airfoil at a first location;a ternary third link pivotably connected to the second link;a binary fourth link pivotably connected to the third link;a ternary fifth link pivotably connected to the fourth link and pivotably connected to the airfoil at a second location, the first and second locations being fixed relative to each other; anda binary sixth link pivotably connected to the third link and the fifth link; anda deployable leading edge panel carried by the linkage, the leading edge panel being movable via the linkage among a stowed position, a landing position, and a take-off position, and wherein the leading edge panel (a) forms a part of the lower portion when in the stowed position, (b) has a trailing edge that is spaced apart from the upper portion to form a gap when in the landing position, and (c) at least partially seals the gap when in the take-off position, further wherein the leading edge panel maintains a generally fixed shape as it is moved among the stowed position, the landing position and the take-off position, and wherein fourth link includes a generally rigid support panel that carries the leading edge panel. 13. The system of claim 12, further comprising a bullnose pivotably connected to the leading edge panel and to a seventh link that is in turn pivotably connected to the third link. 14. The system of claim 12 wherein the fifth link is pivotably connected to the airfoil at the second location forward of the first location, and wherein the system further comprises an ice protection airflow duct positioned between the first and second locations. 15. The system of claim 12 wherein the leading edge panel is one of multiple leading edge panels positioned in a spanwise direction along the wing, with the thickness of the wing being different at different spanwise locations, and wherein individual leading edge panels are connected to the wing with corresponding individual six-bar linkages having Stephenson II configurations. 16. The aircraft system of claim 12, further comprising: an actuator coupled to the linkage;a controller coupled to the actuator; anda selector coupled to the controller and changeable among multiple selectable positions to which the leading edge panel can be deployed, wherein the controller controls the actuator to move the leading edge panel to a selected position based on input from the selector. 17. An aircraft system comprising: a fuselage;a wing attached to the fuselage, the wing having an external flow surface, the external flow surface comprising an upper portion and a lower portion, the airfoil forming a base link;a six-bar linkage having a configuration that includes: a binary second link pivotably connected to the airfoil at a first location;a ternary third link pivotably connected to the second link;a binary fourth link pivotably connected to the third link;a ternary fifth link pivotably connected to the fourth link and pivotably connected to the airfoil at a second location, the first and second locations being fixed relative to each other; anda binary sixth link pivotably connected to the third link and the fifth link; anda deployable leading edge panel carried by the linkage, the leading edge panel being movable via the linkage among a stowed position, a landing position, and a take-off position;a bullnose pivotably coupled to the leading edge panel;a support panel pivotably coupled to the leading edge panel, the bullnose, and the third link; anda seventh link pivotably connected between the support panel and the fifth link; wherein: the leading edge panel (a) forms a part of the lower portion when in the stowed position, (b) has a trailing edge that is spaced apart from the upper portion to form a gap when in the landing position, and (c) at least partially seals the gap when in the take-off position; andthe leading edge panel is flexible and changes shape as the leading edge panel moves from the stowed position to at least one of the landing position and the take-off position. 18. The system of claim 17 wherein the fifth link is pivotably connected to the airfoil at the second location forward of the first location, and wherein the system further comprises an ice protection airflow duct positioned forward of the second location. 19. The system of claim 17 wherein the leading edge panel forms a part of the lower portion when in the stowed position. 20. The aircraft system of claim 17, further comprising: an actuator coupled to the linkage;a controller coupled to the actuator; anda selector coupled to the controller and changeable among multiple selectable positions to which the leading edge panel can be deployed, wherein the controller controls the actuator to move the leading edge panel to a selected position based on input from the selector. 21. A method for operating an aircraft wing system, comprising: deploying a leading edge panel relative to an airfoil having an external flow surface, the airfoil forming a base link, the leading edge panel having a configuration that includes: a binary second link pivotably connected to the airfoil at a first location;a ternary third link pivotably connected to the second link;a binary fourth link pivotably connected to the third link;a ternary fifth link pivotably connected to the fourth link and pivotably connected to the airfoil at a second location, the first and second locations being fixed relative to each other; anda binary sixth link pivotably connected to the third link and the fifth link, wherein the leading edge panel is carried by the linkage;stowing the leading edge panel after take-off; anddeploying the leading edge panel to be spaced apart from a leading edge of the wing during at least one of approach and landing. 22. The method of claim 21 wherein stowing the leading edge panel includes stowing the leading edge panel in an opening at a lower surface of the airfoil. 23. The method of claim 21 wherein the leading edge panel has a generally fixed, rigid shape, and wherein deploying and stowing the leading edge panel are completed while the leading edge panel has a generally fixed, rigid shape. 24. The method of claim 21 wherein the leading edge panel has a flexible shape wherein at least one of stowing the leading edge panel and deploying the leading edge panel includes changing a shape of the leading edge panel. 25. The method of claim 21, further comprising shielding the airfoil with the leading edge panel during take-off to at least restrict debris from attaching to the external flow surface. 26. An aircraft system, comprising: an airfoil having an external flow surface, the external flow surface comprising an upper portion and a lower portion, the airfoil forming a base link;a six-bar linkage coupled to the airfoil and having a configuration that includes: a second link pivotably connected to the airfoil at a first pivot point having a first location;a third link pivotably connected to the second link at a second pivot point offset from the first pivot point;a fourth link pivotably connected to the third link at a third pivot point;a fifth link pivotably connected to the airfoil at a seventh pivot point having a second location fixed relative to the first location, the fifth link being pivotably connected to the fourth link at a sixth pivot point; anda sixth link pivotably connected to the third link at a fourth pivot point, and pivotably connected to the fifth link at a fifth pivot point, the second, third and fourth pivot points being offset from each other, the fifth, sixth and seventh pivot points being offset from each other; anda deployable leading edge panel carried by the linkage, the leading edge panel being movable via the linkage between a stowed position and at least one deployed position.