초록 ▼

Micro-electro-mechanical (MEM) translational tabs are introduced for enhancing and controlling aerodynamic loading of lifting surfaces. These microtabs are mounted at or near the trailing edge of lifting surfaces, deploy approximately normal to the surface, and have a maximum deployment height on th

Micro-electro-mechanical (MEM) translational tabs are introduced for enhancing and controlling aerodynamic loading of lifting surfaces. These microtabs are mounted at or near the trailing edge of lifting surfaces, deploy approximately normal to the surface, and have a maximum deployment height on the order of the boundary layer thickness. Deployment of this type of device effectively changes the camber, thereby affecting the lift generated by the surface. The effect of these microtabs on lift is as powerful as conventional control surfaces such as ailerons. Application of this simple yet innovative lift enhancement and control device will permit the elimination of some of the bulky conventional high-lift and control systems and result in an overall reduction in system weight, complexity and cost.

대표청구항 ▼

What is claimed is: 1. An apparatus for controlling aerodynamic loading of an airfoil surface, comprising: a base member; and a plurality of translational elements; said translational elements slidably coupled to said base member; said base member configured for installation in a trailing edge regi

What is claimed is: 1. An apparatus for controlling aerodynamic loading of an airfoil surface, comprising: a base member; and a plurality of translational elements; said translational elements slidably coupled to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said translational elements are extendable and retractable in relation to said airfoil; wherein said translational elements have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length; wherein said translational elements are configured to control aerodynamic loading on said airfoil as a result of the orientation of said translational elements in the absence of a flap-type control surface on said airfoil. 2. An apparatus as recited in claim 1, wherein said translational element comprises a microfabricated tab. 3. An apparatus for controlling aerodynamic loading of an airfoil surface, comprising: a base member; and a translational element; said translational element slidably coupled to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said translational element is extendable and retractable in relation to said airfoil; wherein said translational element is coupled to said base member with a dovetail joint. 4. An apparatus as recited in claim 3, wherein said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to sold sliding member. 5. An apparatus as recited in claim 4, wherein said extension member comprises a microfabricated tab. 6. An apparatus for controlling aerodynamic loading of an airfoil surface, comprising: a base member; and a translational element; said translational element slidably coupled to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said translational element is extendable and retractable in relation to said airfoil; wherein said translational element comprises (i) an extension member, and (ii) a sliding member, (iii) said sliding member slidably coupled to said base member, (iv) said extension member fixedly coupled to said sliding member; wherein said translational element is coupled to said base member with a dovetail joint. 7. An apparatus as recited in claim 6, wherein said translational element is extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 8. An apparatus for controlling aerodynamic loading, comprising: a base member; a plurality of sliding members; and said base member configured for installation in a trailing edge surface of an airfoil; said airfoil being without a flap-type control surface; wherein said sliding members are extendable and retractable from within said airfoil surface; wherein said sliding members have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length; wherein said sliding members are configured to control aerodynamic loading on said airfoil as a result of the orientation of said translational elements. 9. An apparatus as recited in claim 8, wherein said sliding members are adapted to increase or decrease lift as a result of a fully extended orientation of said sliding members. 10. An apparatus for controlling aerodynamic loading, comprising: a base member; a sliding member; and an extension member; said extension member bonded to said sliding member; said sliding member slidably coupled to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said extension member is extendable and retractable in relation to said airfoil; wherein said extension member is coupled to said base member with a dovetail joint. 11. An apparatus as recited in claim 10, wherein said extension member is extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 12. An apparatus for controlling aerodynamic loading, comprising: a microfabricated base member; a microfabricated sliding member; and a microfabricated extension member; said extension member bonded to said sliding member; said sliding member slidably coupled to said base member using a dovetail joint; said base member configured for installation in a trailing edge region of an airfoil wherein said extension member is extendable and retractable in relation to said airfoil. 13. An apparatus as recited in claim 12, wherein said extension member is extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 14. An apparatus for controlling aerodynamic loading, comprising: a base member; a plurality of translational elements; and means for slidably coupling said elements to said base member; said base member configured for installation in a trailing edge surface of an airfoil wherein said elements are extendable and retractable in relation to said airfoil; wherein said translational elements have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length; wherein said translational elements are configured to control aerodynamic loading on said airfoil as a result of the orientation of said translational elements in the absence of a flap-type control surface on said airfoil. 15. An apparatus as recited in claim 14, wherein said translational elements are configured to extend and retract linearly outward from said airfoil surface. 16. An apparatus for controlling aerodynamic loading, comprising: a base member; a translational element; and means for slidably coupling said translational element to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said translational element is extendable and retractable in relation to said airfoil; wherein said means for slidably coupling said translational element to said base member comprises a dovetail joint. 17. An apparatus as recited in claim 16, wherein said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to said sliding member. 18. An apparatus as recited in claim 17, wherein said extension member comprises a microfabricated tab. 19. An apparatus for controlling aerodynamic loading, comprising: a base member; a translational element; and means for slidably coupling said translational element to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said translational element is extendable and retractable in relation to said airfoil; wherein said translational element comprises (i) an extension member, and (ii) a sliding member, (iii) said sliding member slidably coupled to said base member, (iv) said extension member fixedly coupled to said sliding member; wherein said means for slidably coupling said translational element to said base member comprises a dovetail joint. 20. An apparatus as recited in claim 19, wherein said translational element is extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 21. An apparatus for controlling aerodynamic loading, comprising: a base member; a sliding member; an extension member; said extension member bonded to said sliding member; and means for slidably coupling said sliding member to said base member; said base member configured for installation in a trailing edge region of an airfoil wherein said extension member is extendable and retractable in relation to said airfoil; wherein said means for slidably coupling said sliding member to said base member comprises a dovetail joint. 22. An apparatus as recited in claim 21, wherein said extension member is extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 23. In an airfoil having a surface and a trailing-edge region, the improvement comprising: a plurality of translational elements embedded in the trailing-edge region of the airfoil; wherein said translational elements are extendable and retractable in relation to said airfoil; wherein said translational elements have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length; wherein said translational elements are configured to control aerodynamic loading on said airfoil surface as a result of the orientation of said translational elements in the absence of a flap-type control surface on said airfoil. 24. An improved airfoil as recited in claim 23: wherein said translational elements are slidably coupled to a base member. 25. An improved airfoil as recited in claim 24, wherein said a trailing-edge region terminates at a trailing edge of said airfoil; and wherein said translational elements are positioned a distance from said trailing edge; said distance being no greater than ten percent of the chord length of said airfoil. 26. In an airfoil having a surface and a trailing-edge region, the improvement comprising: a translational element embedded in the trailing-edge region of the airfoil; wherein said translational element is extendable and retractable in relation to said airfoil; wherein said translational element is slidably coupled to a base member; wherein said translational element is coupled to said base member with a dovetail joint. 27. An improved airfoil as recited in claim 26, wherein said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to said sliding member. 28. An improved airfoil as recited in claim 27, wherein said extension member comprises a microfabricated tab. 29. In an airfoil having a surface and a trailing-edge region, the improvement comprising: a translational element embedded in the trailing-edge region of the airfoil; wherein said translational element is extendable and retractable in relation to said airfoil, wherein said translational element is slidably coupled to a base member; wherein said translational element comprises (i) an extension member, and (ii) a sliding member, (iii) said sliding member slidably coupled to said base member, (iv) said extension member fixedly coupled to said sliding member; wherein said translational element is coupled to said base member with a dovetail joint. 30. An apparatus as recited in claim 29, wherein said translational element is extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 31. In an airfoil having a surface and a trailing-edge region, the improvement comprising: a plurality of spaced-apart translational elements embedded in the trailing-edge region of the airfoil; said translational elements having a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length wherein said translational elements are extendible and retractable in relation to said airfoil; wherein said translational elements are configured to control aerodynamic loading on said airfoil as a result of the orientation of said translational elements in the absence of a flap-type control surface on said airfoil. 32. An improved airfoil as recited in claim 31: wherein said translational elements are configured to slidably extend and retract linearly outward from said airfoil surface. 33. An improved airfoil as recited in claim 32, wherein said translational elements span in a line across a majority of said airfoil in said trailing edge region. 34. In an airfoil having a surface and a trailing-edge region, the improvement comprising: a plurality of spaced-apart translational elements embedded in the trailing-edge region of the airfoil; wherein said translational elements are extendible and retractable in relation to said airfoil; wherein said translational elements are slidably coupled to a base member; wherein said translational elements are coupled to said base member with dovetail joints. 35. An improved airfoil as recited in claim 34, wherein each said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to said sliding member. 36. An improved airfoil as recited in claim 35, wherein said extension member comprises a microfabricated tab. 37. In an airfoil having a surface and a trailing-edge region, the improvement comprising: a plurality of spaced-apart translational elements embedded in the trailing-edge region of the airfoil; wherein said translational elements are extendible and retractable in relation to said airfoil; wherein each said translational element comprises (i) an extension member, and (ii) a sliding member, (iii) said sliding member slidably coupled to said base member, (iv) said extension member fixedly coupled to said sliding member; wherein each said sliding member is coupled to said base member with a dovetail joint. 38. An apparatus as recited in claim 37, wherein said translational elements are extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 39. An airfoil having a surface and a trailing-edge region, and comprising a plurality of spaced-apart translational elements embedded in said trailing-edge region of said airfoil wherein said translational elements are extendible and retractable in relation to said airfoil, wherein said translational elements are have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length, and configured to control aerodynamic loading on said airfoil as a result of the orientation of said translational elements in the absence of a flap on said airfoil. 40. An airfoil as recited in claim 39: wherein said translational elements are slidably coupled to a base member. 41. An airfoil as recited in claim 40, wherein said translational elements are deployed independently of any other control surface on said airfoil. 42. An airfoil having a surface and a trailing-edge region, and comprising a plurality of spaced-apart translational elements embedded in said trailing-edge region of said airfoil wherein said translational elements are extendible and retractable in relation to said airfoil; wherein said translational elements are slidably coupled to a base member; wherein said translational elements are coupled to said base member with dovetail joints. 43. An airfoil as recited in claim 42, wherein each said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to said sliding member. 44. An airfoil as recited in claim 43, wherein said extension member comprises a microfabricated tab. 45. An airfoil having a surface and a trailing-edge region, and comprising a plurality of spaced-apart translational elements embedded in said trailing-edge region of said airfoil wherein said translational elements are extendible and retractable in relation to said airfoil; wherein each said translational element comprises (i) an extension member, and (ii) a sliding member, (iii) said sliding member slidably coupled to said base member, (iv) said extension member fixedly coupled to said sliding member; wherein each said sliding member is coupled to said base member with a dovetail joint. 46. An airfoil as recited in claim 45, wherein said translational elements are extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 47. An airfoil having a trailing-edge region and a chord length, and comprising: a plurality of spaced apart translational elements embedded in the trailing edge region of the airfoil; each said translational element configured for deployment outward from said trailing-edge region of said airfoil; each said translational element having a maximum height of approximately two percent of the chord length of the airfoil when said translational element is fully deployed; wherein said translational elements have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length; wherein said translational elements are configured to control aerodynamic loading on said airfoil as a result of the orientation of said translational element in the absence of a flap-type control surface on said airfoil. 48. An airfoil as recited in claim 47: wherein said translational elements are slidably coupled to a base member. 49. An airfoil as recited in claim 48, wherein said a trailing-edge region terminates at the trailing edge of said airfoil; and wherein said translational element is positioned a distance from said trailing edge; said distance being no greater than ten percent of the chord length of said airfoil. 50. An airfoil having a trailing-edge region and a chord length, and comprising: a plurality of spaced apart translational elements embedded in the trailing edge region of the airfoil; each said translational element configured for deployment outward from said trailing-edge region of said airfoil; each said translational element having a maximum height of approximately two percent of the chord length of the airfoil when said translational element is deployed; wherein said translational elements are slidably coupled to a base member; wherein said translational elements are coupled to said base member with dovetail joints. 51. An airfoil as recited in claim 50, wherein each said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to said sliding member. 52. An airfoil as recited in claim 51, wherein said extension member comprises a microfabricated tab. 53. An airfoil having a trailing-edge region and a chord length, and comprising: a plurality of spaced apart translational elements embedded in the trailing edge region of the airfoil; each said translational element configured for deployment outward from said trailing-edge region of said airfoil; each said translational element having a maximum height of approximately two percent of the chord length of the airfoil when said translational element is deployed; wherein each said translational element comprises (i) an extension member, and (ii) a sliding member, (iii) said sliding member slidably coupled to said base member, (iv) said extension member fixedly coupled to said sliding member; wherein each said sliding member is coupled to said base member with a dovetail joint. 54. An airfoil as recited in claim 53, wherein said translational elements are extendable and retractable in a direction substantially perpendicular to the surface of said airfoil. 55. A method of controlling aerodynamic loading on an airfoil having a chord length, trailing edge and a trailing-edge region, the airfoil generating a point of airflow separation when the airfoil is employed in an airflow, the method comprising: slidably deploying a translational element linearly outward from said trailing-edge region of said airfoil; wherein said translational element is embedded at a distance no further than ten percent of the chord length from the trailing edge in the trailing-edge region of the airfoil; and shifting the point of airflow separation for a substantial portion of the airfoil from the trailing edge to a location on the translational element to control the lift of said airfoil. 56. A method as recited in claim 55, wherein said translational element is deployed in a direction substantially perpendicular to the surface of said airfoil. 57. A method of controlling aerodynamic loading on an airfoil having a chord length, trailing edge and a trailing-edge region, the airfoil generating a point of airflow separation when the airfoil is employed in an airflow, comprising: slidably deploying a plurality of spaced-apart translational elements linearly outward from said trailing-edge region of said airfoil; wherein said translational elements are embedded at a distance no further than ten percent of the chord length from the trailing edge in the trailing-edge region of the airfoil; and shifting the point of airflow separation for a substantial portion of the airfoil from the trailing edge to a location on the translational elements to control the lift of said airfoil. 58. A method as recited in claim 57, wherein said translational elements are deployed in a direction substantially perpendicular to the chord of said airfoil. 59. A method as recited in claim 57, wherein said airfoil has an upper surface and a lower surface, and wherein deploying a plurality of spaced-apart translational elements comprises deploying the translational elements downward from the lower surface of the airfoil to increase the lift of the airfoil. 60. A method as recited in claim 57, wherein said airfoil has an upper surface and a lower surface, and wherein deploying a plurality of spaced-apart translational elements comprises deploying the translational elements upward from the upper surface of the airfoil to decrease the lift of the airfoil. 61. A method as recited in claim 57, wherein each translational element is capable of variably extending to at least a portion of the translation element's extendable length. 62. A method as recited in claim 57, wherein each translational element is capable of independently extending and retracting in relation to said airfoil and each other. 63. An apparatus for controlling aerodynamic loading of an airfoil, said airfoil having a chord length and an upper and lower surface converging at a trailing edge, comprising: a base member; and a translational element; said translational element slidably coupled to said base member; said base member configured to be embedded at a distance no further than ten percent of the chord length from the trailing edge in a trailing edge region of an airfoil; wherein said translational element is extendable and retractable said airfoil; wherein said translational element is configured to shift the point of airflow separation for a substantial portion of the airfoil from the trailing edge to a location on the translational elements to control the aerodynamic loading of said airfoil. 64. An apparatus as recited in claim 63, wherein the translation element is configured such that downward extension of said translational element outward from the lower surface increases the lift on said airfoil. 65. An apparatus as recited in claim 63, wherein the translation element is configured such that upward extension of said translational element outward from the upper surface decreases the lift on said airfoil. 66. An airfoil having upper and lower surfaces and a trailing-edge region, comprising: a plurality of spaced-apart translational elements embedded in said trailing-edge region of said airfoil; wherein said translational elements have a length running substantially parallel to a trailing edge of said airfoil and are spaced apart from each other at a distance less than said length; wherein said translational elements am independently extendible and retractable in relation to said airfoil and each other to control aerodynamic loading on said airfoil in the absence of a flap-type control surface on said airfoil. 67. An airfoil as recited in claim 66, wherein said translational elements may be deployed in a serrated pattern to produce a variable trailing-edge geometry. 68. An airfoil as recited in claim 66, wherein said translational elements may be extended downward from said lower surface to increase lift on the airfoil. 69. An airfoil as recited in claim 66, wherein said translational elements may be extended upward from said upper surface to decrease lift on the airfoil. 70. An airfoil having a chord length, trailing-edge and a trailing-edge region, the airfoil generating a point of airflow separation when the airfoil is employed in an airflow, comprising: a translational element embedded in said airfoil less than ten percent of the chord length from the trailing edge; wherein said translational element is extendible and retractable linearly outward in relation to said airfoil; wherein said translational element is positioned in said trailing-edge region of said airfoil such that extension of the translational element shifts the point of airflow separation for a substantial portion of the airfoil from the trailing edge to a location on the translational element; wherein aerodynamic loading on said airfoil is controlled by said shift in the point of airflow separation. 71. An airfoil as recited in claim 70, wherein said translational element embedded in said airfoil at a distance ranging from two percent to six percent of the chord length from the trailing edge. 72. An airfoil having a trailing-edge and a trailing-edge region, the airfoil generating a point of airflow separation when the airfoil is employed in an airflow, comprising: a translational element embedded in said airfoil; wherein said translational element is extendible and retractable outward in relation to said airfoil; wherein said translational element is positioned in said trailing-edge region of said airfoil such that extension of the translational element shifts the point of airflow separation from the trailing edge to a location on the translational element; wherein lift on said airfoil is controlled by said shift in the point of airflow separation; and a base member configured for installation in the trailing-edge region of the airfoil; wherein said translational element comprises: an extension member; and a sliding member; said sliding member slidably coupled to said base member; said extension member fixedly coupled to said sliding member. 73. An airfoil as recited in claim 70, wherein: said airfoil has an upper surface and a lower surface; and wherein the translational element is configured to be deployed downward from the lower surface of the airfoil to increase the lift on the airfoil. 74. An airfoil as recited in claim 70, wherein: said airfoil has an upper surface and a lower surface; and wherein the translational element is configured to be deployed upward from the upper surface of the airfoil to decrease the lift on the airfoil. 75. An airfoil as recited in claim 70, wherein: said airfoil has an upper surface and a lower surface; and wherein the translational element is configured to be deployed upward from the upper surface of the airfoil and downward from the lower surface of the airfoil to control the lift on the airfoil. 76. An airfoil as recited in claim 70, further comprising: a second translational element embedded in said airfoil; wherein said second translational element is independently extendible and retractable in relation to said airfoil and said first translational element. 77. An airfoil as recited in claim 70, wherein the translation element comprises a plurality of translational elements configured such that extension of the translational element shifts the point of airflow separation across substantially all of the airfoil. 78. An airfoil as recited in claim 70, wherein the translational element is configured to operate independently from any other control surface on said airfoil. 79. An airfoil as recited in claim 70, wherein the translational element is configured to operate in the absence of a flap-type control surface on said airfoil. 80. An airfoil as recited in claim 70, wherein the translational element is configured to operate in the absence of an aileron on said airfoil. 81. An airfoil as recited in claim 70, wherein the translational element is configured to operate in the absence of a flap on said airfoil. 82. An airfoil as recited in claim 70, wherein the translational element has a maximum height of approximately two percent of the chord length of the airfoil when said translational element is deployed.