Autonomous slat-cove-filler device for reduction of aeroacoustic noise associated with aircraft systems
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-009/24
B64C-009/22
B64C-003/48
출원번호
US-0277859
(2011-10-20)
등록번호
US-9242720
(2016-01-26)
발명자
/ 주소
Turner, Travis L.
Kidd, Reggie T.
Lockard, David P
Khorrami, Mehdi R.
Streett, Craig L.
Weber, Douglas Leo
출원인 / 주소
The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
대리인 / 주소
Warmbier, Andrea Z.
인용정보
피인용 횟수 :
0인용 특허 :
10
초록▼
A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The
A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.
대표청구항▼
1. A wing structure for aircraft, comprising: a primary wing structure defining a leading edge, a trailing edge, and upper and lower surfaces extending between the leading and trailing edges to define a first airfoil element;a leading-edge slat movably interconnected with the primary wing structure
1. A wing structure for aircraft, comprising: a primary wing structure defining a leading edge, a trailing edge, and upper and lower surfaces extending between the leading and trailing edges to define a first airfoil element;a leading-edge slat movably interconnected with the primary wing structure for movement between a retracted position wherein the leading edge slat is positioned adjacent the leading edge of the primary wing structure to reduce aerodynamic drag, and a deployed position wherein the leading-edge slat is shifted relative to the retracted position to thereby provide a multi-element airfoil, and wherein the leading-edge slat includes a leading surface whereby, in use, airflow splits and flows over an upper surface of the leading-edge slat that extends rearwardly from the leading surface to a trailing edge, and a lower surface extending rearwardly from the leading surface to a cusp;a slat cove filler comprising a flexible material connected to the trailing edge and the cusp, wherein the slat cove filler defines a first shape when the leading edge slat is in its deployed position, and a second shape when the leading edge slat is in its retracted position, and wherein at least a portion of the slat cove filler comprises a superelastic shape memory alloy that transforms from an austenitic phase to a martensite phase when the slat cove filler changes from the first shape to the second shape; anda torsion spring that rotatably biases the slat cove filler about a hinge and causes the slat cove filler to change from the second shape to the first shape as the slat moves from its retracted position to its deployed position;wherein the slat cove filler is connected to the cusp of the slat by the hinge. 2. The wing structure of claim 1, wherein the second shape of the slat cove filler comprises a plurality of concave portions and at least one convex portion facing the leading edge of the primary wing structure, wherein the at least one convex portion is disposed between the plurality of concave portions. 3. A wing structure for aircraft, comprising: a primary wing structure defining a leading edge, a trailing edge, and upper and lower surfaces extending between the leading and trailing edges to define a first airfoil element;a leading-edge slat movably interconnected with the primary wing structure for movement between a retracted position wherein the leading edge slat is positioned adjacent the leading edge of the primary wing structure to reduce aerodynamic drag, and a deployed position wherein the leading-edge slat is shifted relative to the retracted position to thereby provide a multi-element airfoil, and wherein the leading-edge slat includes a leading surface whereby, in use, airflow splits and flows over an upper surface of the leading-edge slat that extends rearwardly from the leading surface to a trailing edge, and a lower surface extending rearwardly from the leading surface to a cusp; anda slat cove filler comprising a flexible material connected to the trailing edge and the cusp, wherein the slat cove filler defines a first shape when the leading edge slat is in its deployed position, and a second shape when the leading edge slat is in its retracted position, and wherein at least a portion of the slat cove filler comprises a superelastic shape memory alloy that transforms from an austenitic phase to a martensite phase when the slat cove filler changes from the first shape to the second shape;wherein the slat cove filler is connected to the cusp of the slat by a hinge; andwherein the second shape of the slat cove filler comprises a first and a second concave portion and a convex portion, wherein said first and second concave portions and convex portion face the leading edge of the primary wing structure, and wherein the convex portion is disposed between the first and second concave portions. 4. The wing structure of claim 3, wherein: at least a portion of the superelastic shape memory alloy experiences at least about 2% strain when the leading edge slat is in its retracted position. 5. The wing structure of claim 3, wherein: a boundary layer is formed at an outer surface of the thin flexible material when air flows along the outer surface;the first shape of the thin flexible material defines an outer surface having a contour that causes the boundary layer to remain attached to the outer surface. 6. The wing structure of claim 5, wherein: the first shape of the thin flexible material includes a smoothly curved convex portion extending rearwardly from the cusp of the slat, and a concave curved portion adjacent the trailing edge of the slat. 7. The wing structure of claim 3, wherein the isobar line comprises a substantially constant pressure line that occur during landing approach of the aircraft. 8. A wing structure for aircraft, comprising: a primary wing structure defining a leading edge, a trailing edge, and upper and lower surfaces extending between the leading and trailing edges to define a first airfoil element;a leading-edge slat movably interconnected with the primary wing structure for movement between a retracted position wherein the leading edge slat is positioned adjacent the leading edge of the primary wing structure to reduce aerodynamic drag, and a deployed position wherein the leading-edge slat is shifted relative to the retracted position to thereby provide a multi-element airfoil, and wherein the leading-edge slat includes a leading surface whereby, in use, airflow splits and flows over an upper surface of the leading-edge slat that extends rearwardly from the leading surface to a trailing edge, and a lower surface extending rearwardly from the leading surface to a cusp; anda slat cove filler comprising a flexible material connected to the trailing edge and the cusp, wherein the slat cove filler defines a first shape when the leading edge slat is in its deployed position, and a second shape when the leading edge slat is in its retracted position, and wherein at least a portion of the slat cove filler comprises a superelastic shape memory alloy that transforms from an austenitic phase to a martensite phase when the slat cove filler changes from the first shape to the second shape, wherein the slat cove filler defines a first area having a first thickness, and a second area having a second thickness that is greater than the first thickness, and wherein the slat cove filler includes a first sheet comprising superelastic shape memory alloy having the first thickness and a second sheet of material disposed on a portion of the first sheet to define the second area having the second thickness;wherein the slat cove filler is connected to the cusp of the slat by a hinge. 9. The wing structure of claim 8, wherein: at least a portion of the superelastic shape memory alloy experiences at least about 2% strain when the leading edge slat is in its retracted position. 10. The wing structure of claim 8, wherein: a boundary layer is formed at an outer surface of the thin flexible material when air flows along the outer surface;the first shape of the thin flexible material defines an outer surface having a contour that causes the boundary layer to remain attached to the outer surface. 11. The wing structure of claim 10, wherein: the first shape of the thin flexible material includes a smoothly curved convex portion extending rearwardly from the cusp of the slat, and a concave curved portion adjacent the trailing edge of the slat. 12. The wing structure of claim 10, wherein the isobar line comprises a substantially constant pressure line that occur during landing approach of the aircraft.
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이 특허에 인용된 특허 (10)
Wolfgang Gleine DE; Knut Mau DE; Udo Carl DE, Aerodynamic noise reducing structure for aircraft wing slats.
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