An aircraft wing includes a leading element; a trailing element positioned behind the leading element relative to a direction of movement of the aircraft and an actuation system for moving one of the elements between a retracted position and an extended position in which there is an air gap between
An aircraft wing includes a leading element; a trailing element positioned behind the leading element relative to a direction of movement of the aircraft and an actuation system for moving one of the elements between a retracted position and an extended position in which there is an air gap between a lower surface of the leading element and a surface of the trailing element. Two or more elongate stiffening ridges extend downwards from the lower surface of the leading element, and each adjacent pair of ridges is separated by a channel. The leading element is shaped to provide an improved air gap, preferably one which is parallel or convergent in all positions. Typically the volume of at least one of the ridges is less than the 50% of the volume of a channel defined by that ridge.
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1. An aircraft wing comprising: a main wing element;a moveable element, wherein the moveable element comprises at least one of: a leading element in front of the main wing element; ora trailing element behind the main wing element relative toa direction of flight of the aircraft,wherein a front elem
1. An aircraft wing comprising: a main wing element;a moveable element, wherein the moveable element comprises at least one of: a leading element in front of the main wing element; ora trailing element behind the main wing element relative toa direction of flight of the aircraft,wherein a front element is a forward one of the main wing element and the moveable element in the direction of flight, and a rear element is a rearward one of the main wing element and the moveable element;an actuation system configured to move the moveable element between a retracted position and an extended position in which there is an air gap between a lower surface of the front element and the rear element, wherein the air gap has a length in the direction of flight and a width defined by a shortest dimension between the lower surface of the front element and a surface of the rear element adjacent the air gap and overlapped by the lower surface of the front element, at each point along the length of the air gap; andtwo or more elongate stiffening ridges extending downwards from the lower surface of the front element, wherein the two or more elongate stiffening ridges overlap the rear element while the actuated system is in the retracted position,wherein each adjacent pair of stiffening ridges is separated by a channel, and the volume of at least one of the ridges is less than the 50% of the volume of the channel adjacent the at least one of the ridges,wherein the actuation system is configured to orient the moveable element so that in at least one intermediate position of the actuation system the width of the air gap is constant or convergent along the length of the air gap and the width of the air gap is at a minimum at an outlet of the air gap. 2. The wing of claim 1, wherein the thickness of the front element at a point along the direction of flight less than the depth of a channel at the same point. 3. The wing of claim 1 wherein each channel has an open rear end which is positioned substantially at a trailing edge of the front element. 4. The wing of claim 1 wherein tangents to the lower surface relative to the upper surface of the front element transverse to the trailing edge of the front element make an angle of less than 5 degrees with each other at the trailing edge. 5. The wing of claim 1 wherein tangents to the lower surface relative to the upper surface of the front element transverse to a trailing edge of the front element make an angle of less than 2 degrees with each other at the trailing edge. 6. The wing of claim 1 wherein a volume of at least one of the ridges is less than 25% of a volume of a channel defined by that ridge. 7. The wing of claim 1 wherein the thickness of the front element at one or more points is less than 50% of the depth of a channel at the same point. 8. The wing of claim 1 wherein each of the two or more elongate stiffening ridge tapers towards a rear end of the stiffening ridge. 9. The wing of claim 1 wherein the surface of the front element extends to either side of the outermost pair of the two or more elongate ridges. 10. The wing of claim 1 wherein at least some of the two or more elongate stiffening ridges extend at an angle greater than 0° to a direction of flow of air through the air gap. 11. The wing of claim 1 wherein the actuation system is configured to orient the moveable element so that, at each of all of the intermediate positions of the actuation system, the width of the air gap is either constant or convergent. 12. The wing of claim 1, wherein the font element is the main wing element which is a fixed wing and the rear element is the moveable element which is a moveable flap, and said actuation system is connected to move said flap between the retracted and the extended positions. 13. The wing of claim 1, wherein said front element is the moveable element which is a moveable slat and the rear element is the main wing element which is a fixed wing, and said actuation system is connected to move said moveable slat between the retracted and the extended positions. 14. An aircraft wing comprising: a main wing element; anda moveable element, wherein the moveable element comprises at least one of: a leading element forward of the main wing element relative to a direction of the aircraft; ora trailing element behind the main wing element relative tothe direction of flight of the aircraft;wherein a front element is a forward one of the main wing element and the moveable element in the direction of flight, and a rear element is a rearward one of the main wing element and the moveable element;an actuation system configured to move the moveable element between a retracted position and an extended position in which there is an air gap between a lower surface front element and the rear element, wherein the air gap has a length in the direction of flight and a width defined by a shortest dimension between the lower surface of the front element and a surface of the rear element adjacent the air gap and overlapped by the lower surface, at each point along the length of the air gap; andtwo or more elongate stiffening ridges extending downwards from the lower surface of the front element, wherein the two or more elongate stiffening ridges overlap the surface of the rear element while the actuated system is in the retracted position;wherein each adjacent pair of stiffening ridges is separated by a channel, and wherein the thickness of the front element at a point along the direction of flight is less than the depth of the channel at the same point,wherein the actuation system is configured to orient the moveable element so that in at least one intermediate position of the actuation system the width of the air gap is constant or convergent along a length of the air gap in the direction of flight, such that the width of the air gap is at least as great as the width of the air gap at the rear outlet. 15. The wing of claim 14, wherein the front element is the main wing element which is a fixed wing and the rear element is the moveable element which is a moveable flap, and said actuation system is connected to move said moveable flap between the retracted and the extended positions. 16. The wing of claim 14, wherein said front element is the moveable element which is a moveable slat and the rear element is the main wing element which is a fixed wing, and said actuation system is connected to move said moveable slat between the retracted and the extended positions. 17. An aircraft wing comprising: a main wing element;a moveable element including at least one of: a leading element ahead of the main wing element relative to a direction of flight of the aircraft; ora trailing element behind the leading element relative to a direction of flight of the aircraft;wherein a forward element is the most forward of the main wing element and the moveable element, and a rear element is the most rearward of the main wing element and the moveable element;an actuation system configured to move the movable element between a retracted position and an extended position in which there is an air gap between a lower surface of the front element and the rear element, wherein the air gap has a length in the direction of flight and a width defined by a shortest dimension between the lower surface of the front element and an upper surface of the rear element adjacent the air gap and overlapped by the lower surface of the front element, at each point along the length of the air gap; andtwo or more elongate stiffening ridges extending downwards from the lower surface of the front element, wherein the two or more elongate stiffening ridges overlap the rear element while the actuated system is in the retracted position;wherein each adjacent pair of ridges is separated by a channel, and wherein each channel has an open rear end which is positioned substantially at a trailing edge of the front element,wherein the actuation system is configured to orient the moveable element so that, at least one intermediate position of the actuation system the width of the air gap is constant or convergent along the length of the air gap in the direction of flight, and such that the width of the air gap at each point forward of a rear outlet is at least as great as the width of the air gap at the rear outlet. 18. The wing of claim 17, wherein the front element is the main wing element which is a fixed wing and the rear element is the movable element which is a moveable flap, and said actuation system is connected to move said moveable flap between the retracted and the extended positions. 19. The wing of claim 17, wherein said front element is the moveable element which is a moveable slat and the rear element is the main wing element which is a fixed wing, and said actuation system is connected to move said moveable slat between the retracted and the extended positions. 20. An aircraft wing comprising: a main wing;a flap behind the main wing relative to a flight direction of the aircraft, wherein the flap moves between a retracted position and an extended position with respect to the main wing and the main wing overlaps a portion of an upper surface of the flap at least at the retracted position;a pair of elongate stiffening ridges each extending down from a section of the lower surface of the main wing towards the overlapped portion of the upper surface of the flap, wherein the stiffening ridges along their entire lengths overlap the overlapped portion of the upper surface of the flap while the flap is in the retracted position;a channel defined between the pair of elongate stiffening ridges, wherein the channel includes an open trailing end and a closed leading end, andan air gap between the lower surface of the main wing and the overlapped portion of the upper surface of the flap, wherein the air gap has a length in a direction of flight of the aircraft and a width defined by a shortest dimension between the lower surface of the main wing and the overlapped portion of the upper surface of the flap, at each point along the length of the air gap, and wherein the air gap, at an intermediate position of the flap between the retracted and the extended positions, is constant or convergent along a length of the air gap in the direction of flight, and wherein the width of the air gap, at the intermediate position of the flap, is narrowest at a trailing edge of the main wing. 21. An aircraft wing comprising: a main wing;a leading edge slat forward of the main wing relative to a flight direction of the aircraft, wherein the leading edge slat moves between a retracted position and an extended position with respect to the main wing, and the leading edge slat overlaps a portion of an upper surface of the main wing while the slat is in the retracted position,a pair of elongate stiffening ridges each extending down from the leading edge slat towards the overlapped portion of the upper surface of the main wing, wherein the stiffening ridges along their entire lengths overlap the overlapped portion of the upper surface of the main wing while the slat is in the retracted position;a channel defined between the pair of elongate stiffening ridges, wherein the channel includes an open trailing end and a closed leading end;an air gap between the upper surface of the main wing and the leading edge slat, wherein the air gap has a length in a direction of flight of the aircraft and a width defined by a shortest dimension between the upper surface of the main wing and a portion of the leading edge slat adjacent the air gap and overlapping the upper surface of the main wing, at each point along the length of the air gap, andwherein the air gap, at an intermediate position of the slat between the retracted and the extended positions, is constant or convergent along the length of the air gap in the direction of flight, and wherein the width of the air gap, at the intermediate position, is narrowest at a trailing edge of the slat.
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이 특허에 인용된 특허 (9)
Presz ; Jr. Walter M. (Wilbraham MA) Paterson Robert W. (Simsbury CT) Werle Michael J. (Hartford CT), Airfoil-shaped body.
Blackwelder Ron F. (30531 Rue Langlois Rancho Palos Verdes CA 90274) Gad-el-Hak Mohamed (15275 Hunting Ridge Trail Granger IN 46530), Method and apparatus for reducing turbulent skin friction.
Vijgen Paul M. H. W. (Hampton VA) Howard Floyd G. (Hampton VA) Bushnell Dennis M. (Wicomico VA) Holmes Bruce J. (Newport News VA), Serrated trailing edges for improving lift and drag characteristics of lifting surfaces.
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