초록 ▼

A system and method provides for the manipulation of the aerodynamic characteristics of airfoils and other aerostructures using blowing and/or suction. This system and method uses one or more internal cavities located within an airfoil. An internal cavity is coupled to the exterior surface of the ai

A system and method provides for the manipulation of the aerodynamic characteristics of airfoils and other aerostructures using blowing and/or suction. This system and method uses one or more internal cavities located within an airfoil. An internal cavity is coupled to the exterior surface of the airfoil via one or more slots. A rotary actuator is incorporated into a slot. When the rotary actuator is rotated into a first position, it forms a channel that allows fluid to pass between the internal cavity and the air surrounding the airfoil. When the rotary actuator rotates into a second position, it prevents fluid from passing through the channel between the internal cavity and the air surrounding the airfoil.

대표청구항 ▼

What is claimed is: 1. A system for modulating the aerodynamic characteristics of an airfoil with an external surface, comprising: An internal cavity located within the external surface; A slot located on the external surface, connecting said internal cavity to the external surface; A rotating asse

What is claimed is: 1. A system for modulating the aerodynamic characteristics of an airfoil with an external surface, comprising: An internal cavity located within the external surface; A slot located on the external surface, connecting said internal cavity to the external surface; A rotating assembly inserted into and rotating within said slot with a first orientation and a second orientation; and A channel formed through said rotating assembly with an internal opening to said internal cavity and an external opening to the external surface, wherein said channel allows flow between said internal cavity and the external surface in said first orientation, and said channel substantially prevents flow between said internal cavity and the external surface in said second orientation. 2. A system of claim 1, further comprising a sealing mechanism located within said internal cavity that occludes said channel in part of said first orientation. 3. A system of claim 2, wherein the occlusion of said channel by sealing mechanism creates a third orientation and a fourth orientation, whereby said sealing mechanism blocks said channel in said third orientation preventing flow through said channel between said internal cavity and the external surface of the airfoil, while said channel is not blocked by said sealing mechanism in said fourth orientation thereby allowing flow through said channel between said internal cavity and said external surface of the airfoil. 4. A system of claim 2, whereby a wedge located within said rotating assembly divides said internal opening into two separate inlets. 5. A system of claim 1, wherein said internal cavity is pressurized such that flow through the channel is directed from said internal cavity out to said external surface. 6. A system of claim 1, wherein said slot is located in the leading edge of the airfoil. 7. A system of claim 6, wherein the rotation of said rotating assembly can orient said external opening from −60 degrees to +60 degrees from the centerline of said airfoil. 8. A system of claim 6, further comprising: A second slot located on the surface of the airfoil connecting said internal cavity to the external surface; A second rotating assembly inserted into and rotating within said second slot with an A orientation and a B orientation; and, A second channel formed through said second rotating assembly with an inner opening to said internal cavity and an outer opening to said external surface, wherein said second channel allows flow between said internal cavity and the external surface in said A orientation, and said second channel substantially prevents flow between said internal cavity and the external surface in said B orientation. 9. A system of claim 8, wherein said second rotating assembly is located in the trailing edge of the airfoil. 10. A system of claim 8, wherein said second channel connects a second internal cavity located within the external surface to said external surface. 11. A system of claim 6, further comprising slots located on the upper and lower surfaces of the airfoil, wherein each slot has an open position that allows flow through between said internal cavity and the external surface and a closed position that substantially prevents flow through said internal cavity and the external surface. 12. A system of claim 11, wherein a pair of said slots are located within the first 50% chord of the airfoil. 13. A system of claim 12, wherein said internal cavity is pressurized and said slots are oriented to direct the flow from the internal cavity to the external surface into the relative velocity vector of the freestream air over the external surface. 14. A system of claim 11, wherein said slots are modulated such that flow between said internal cavity and the external surface varies between a minimum in said closed position and a maximum in said open position based on said modulation. 15. A system of claim 11, wherein said slots allows flow between a second internal cavity within the external surface to said external surface. 16. A system of claim 1, further comprising a control means for directing the rotation of said rotating assembly to modulate the aerodynamic characteristics. 17. A helicopter rotor blade control system, comprising: A rotor rotatably mounted to the helicopter; A rotor blade with an exterior, an interior, a leading edge, a trailing edge, and root attached by said root to said rotor; An internal cavity formed in said interior and connected to said rotor such that air can flow between said rotor and said internal cavity; A slot formed in said leading edge creating a channel between said internal cavity through to said exterior; and, A rotary actuator with a first orientation and a second orientation located inside said channel whereby said rotary actuator in said first orientation forms a channel allowing air to flow between said exterior and said internal cavity and when said rotary actuator in said second orientation closes the channel to substantially prevents air from flowing between said exterior and said internal cavity. 18. A system of claim 17, whereby said internal cavity is pressurized with air. 19. A system of claim 17, whereby in said second orientation, said rotary actuator forms a second channel allowing air to flow between said exterior and said internal cavity and said rotary actuator closes said second channel in said first orientation, such that said second channel substantially prevents air from flowing between said exterior and said internal cavity. 20. A system of claim 17, whereby said root is rigidly attached to said rotor. 21. A system of claim 17, whereby said rotary actuator decreases the lift generated by said rotor blade when said rotor blade is in one portion of its rotation around the helicopter and increases lift in the remaining portion of its rotation around the helicopter. 22. A system of claim 17, further comprising slots located on the upper and lower surfaces of the airfoil, wherein each slot has an open position that allows flow through between said internal cavity and the external surface and a closed position that substantially prevents flow through said internal cavity and the external surface.