KR100271065B1 - Wing of aircraft - Google Patents

Abstract

PURPOSE: A wing of an aircraft is provided to delay the flow separation occurring at the upper surface of a wing when an aircraft flies in a high angle of attack, to make easy the application to an aircraft in the medium or small size by rotating a flap via a simple hinge, and to be applied to a military aircraft needing high mobility and lift. CONSTITUTION: A wing of an aircraft has a body(41) and a trailing edge flap(43) or a leading edge flap(42). The leading edge flap faces forward in the advancing direction. The leading edge flap is rotatably combined to the body via a hinge(44), while the trailing edge flap is rotatably combined to the body via a hinge(45). While the flaps are not rotated, the upper surfaces of the body and the flaps form a smooth surface without rapid change of curvature. To form a slot between the leading ledge flap and the wing body when the leading edge flap rotates, a bottom face of the trailing edge of the leading edge flap spaces apart from the leading edge of the wing body. Air is supplied through the slot. Then, reverse pressure state occurring at the upper surface of the wing is released. Therefore, flow separation is delayed.

Description

Aircraft wing

The present invention relates to a wing for an aircraft, and more particularly, a slot is formed in a control surface to prevent a phenomenon of flow seperation that may occur on the surface of the wing during the high angle of attack of the aircraft. It relates to an aircraft wing.

Typically, a medium or large aircraft is provided with a slat at the leading edge of the horizontal wing body to change the lift of the plane. The slats can be arbitrarily adjusted by lifting or contracting from the leading edge of the wing body in accordance with the aircraft's operating conditions. For example, in the cruise state of the aircraft, the slats remain in close proximity to the leading edge of the wing body, and when the aircraft takes off or lands, the slats are developed spaced apart from the leading edge of the wing body.

The trailing edge of the slat and the leading edge of the wing body correspond in an uneven relationship.

Therefore, no space is formed between the trailing edge of the slat and the leading edge of the wing body in the state where the slat is close to the horizontal blade body. On the other hand, when the slat is deployed from the wing body, a slot is formed between the trailing edge of the slat and the leading edge of the wing body, and air flow occurs through the space.

The air flow through the slot formed between the slat and the wing body at the time of deployment of the slat has the function of preventing flow seperation occurring at the upper surface of the wing. In other words, when the angle of attack of the blade increases with respect to the direction of the flow field, flow separation occurs on the upper surface of the blade due to a discontinuous reverse pressure phenomenon. It can be.

On the other hand, it is difficult to employ a wing having a deployable slat as described above in a medium or smaller aircraft that must have a relatively thin wing. This requires that wings with deployable slats require relatively complex linkages and actuators, thus resulting in negative consequences such as an increase in the overall weight of the wings, an increase in power only needed to drive the slats, and a reduction in fuel fill space. Because. As a result, simple hinged flaps are adopted in sub-medium sized aircraft and, in particular, fighters requiring high maneuverability and high lift.

1 shows a schematic perspective view of an aircraft wing with a hinged flap according to the prior art.

Referring to the drawings, the wing 10 for an aircraft is pivotally mounted to the main body 11 of a wing, the front-front flap 12 provided so that rotation was possible in front of the wing body 11, and the wing body 11 rearward. It is provided with the rear front flap 13 provided. The front flap 12 is connected to the main body 11 via a hinge 14, and the rear front flap 13 is also connected to the main body 11 through a hinge not shown. The flaps 12, 13 are adapted to change the angle with respect to the body by a hinge drive mechanism not shown.

FIG. 2 is a side view showing the aircraft wing shown in FIG. 1 at a high angle of attack in the flow field, and FIG. 3 is an enlarged view of the portion indicated by circle A in FIG.

Referring to the drawings, when the main body 11 of the wing 10 is placed at an angle of α with respect to the direction of flow indicated by the arrow 21, the leading edge flap 12 is with respect to the main body 11 to correspond to this. It rotates by the angle of β. In the above, α represents the angle of attack of the wing, and as the angle of attack of the wing increases, β, which is the rotational angle of the leading edge flap 12, must also increase. The rotation of the leading edge flap 12 is for delaying the flow detachment phenomenon occurring at the upper surface of the wing 10. In fact, the flow occurring at the upper surface of the main body 11 as shown in FIG. The tendency of peeling 31 cannot be avoided. In terms of aerodynamics, although the front flap 12 may be rotated to an average position with respect to the flow direction of the air, although it may somewhat delay the flow separation, since the air supply to the upper surface of the wing is practically impossible, Flow separation will occur.

As a solution to the above problems, Boeing's U.S. Patent Nos. 4,457,702, 4,553,772, and 4,706,913 disclose a structure in which a flexible plate is installed at the trailing edge portion of the leading edge flap. However, even in a wing having such a flexible plate, it is impossible to supply air to the upper surface of the wing, and since the curvature of the upper surface changes rapidly during rotation of the flap, it cannot be a countermeasure against fundamental flow separation.

The present invention has been made to solve the above problems, it is an object of the present invention to provide an aircraft wing that can minimize the flow separation phenomenon.

Another object of the present invention is to provide an aircraft wing capable of supplying air to a portion of the flaky peeling of the wing.

Another object of the present invention is to provide a wing for an aircraft in which a flap is supported by a hinge and at the same time a slot can be formed upon rotation of the flap.

1 is a schematic perspective view of a wing for an aircraft according to the prior art.

FIG. 2 is a side view showing the side where the aircraft wing shown in FIG. 1 is in the flow field. FIG.

3 is an enlarged view showing an enlarged portion of a circle denoted by A of FIG.

4 is a perspective view showing an aircraft wing according to the present invention, which shows a state in which the flap is not rotated.

5 is a perspective view showing a state in which the flap is rotated in the wing of the aircraft shown in FIG.

6 (a) and 6 (b) are schematic cross-sectional views showing planes cut along lines A-A and B-B in FIG.

7 (a) and 7 (b) are schematic cross-sectional views showing planes cut along lines A'-A 'and B'-B' in FIG.

8 is a cross-sectional view of a portion of an aircraft wing having additional features in accordance with the present invention.

9 is a cross-sectional view of a portion of an aircraft wing having other additional features in accordance with the present invention.

* Explanation of symbols for main parts of the drawings

11,41: wing body 12,42: front flap

13,43: rear flap 14,44: hinge

51,52: Slot 81,91: Hinge Gear

82,92: transfer gear 83: rotating gear

84: trailing edge member 93: tension gear

94: cable 95: flexible plate

In order to achieve the above object, according to the invention of the present invention, a wing body and a slot which is rotatably installed in front of a leading edge of the wing body and open at least a part of the connecting portion with the wing body at the time of rotation can be formed. A wing for an aircraft is provided so that the bottom surface of the trailing edge has a portion corresponding to the top surface curvature of the leading edge of the wing body and a portion extending therefrom and spaced apart from the leading edge of the wing body.

According to one feature of the invention, the wing body and the front flap are interconnected via a hinge at a portion that does not form a slot.

According to another feature of the present invention, in the state where the forefront flap is not rotated with respect to the wing body, the upper surface of the forefront flap and the upper surface of the wing body form a smooth plane as a whole to close the top of the slot, In the state in which the piezoelectric flap is rotated with respect to the wing body, air flows through a slot formed at the trailing edge of the front edge flap and the leading edge of the wing body.

According to another feature of the invention, the gear train for transmitting the rotation of the hinge by being installed in the hinge, and the trailing edge member formed separately from the member for forming the leading edge flap on the trailing edge portion of the front edge flap And the trailing edge member is fixed with respect to one of the gear trains so that the trailing edge member is interlocked with respect to the rotation of the front leading flap.

According to another feature of the invention, the trailing edge flap of the trailing edge flap of the forefront flap is parallel to the upper surface of the blade body by the rotation of the gear train when the leading edge flap is rotated with respect to the blade body. The ring edge member rotates.

According to another aspect of the present invention, the gear train for transmitting the rotation of the hinge by being installed on the hinge, a flexible member integrally formed on a part of the upper surface of the trailing edge of the front leading flap and one end of the trailing of the front leading flap A cable fixed to an edge and the other end fixed to one of the gear trains, and having a cable guided along the circumferential surface of the gear, wherein one side of the bottom surface of the trailing edge of the forefront flap is cut so that the front flap is rotated. The cut top of the trailing edge is formed to enter the inside of the leading edge flap.

According to another feature of the present invention, the gear train rotates when the forefront flap is rotated with respect to the wing body, and accordingly, the upper surface of the trailing edge of the forefront flap is moved by the tension applied to the cable. Is rotated to a position parallel to the upper surface of the.

According to the present invention, there is provided a wing body and a rear anterior flap rotatably installed at the trailing edge of the wing veneer, and opened at least in part of a connecting portion of the wing main body and the rear anterior flap when the rear anterior flap is rotated. A wing for an aircraft having a bottom surface of the trailing edge of the wing body corresponding to the top surface curvature of the leading edge of the trailing front flap so as to form a slot and extending therefrom and spaced apart from the leading edge of the trailing front flap. Is provided.

According to another feature of the invention the wing body and the trailing front flap are interconnected via a hinge at a portion where the slot is not formed.

Hereinafter, the present invention will be described in more detail with reference to an embodiment shown in the accompanying drawings.

4 and 5 show a schematic perspective view of a wing for an aircraft according to the present invention, in which the flap is not rotated and the flap is shown in FIG. It shows the rotated state.

Prior to the description with reference to the drawings, terms used herein will be defined as follows. The leading edge and the trailing edge refer to the leading and trailing portions, respectively, in the entire wing, wing body or flap. That is, when the whole wing is considered, the portion corresponding to the front and rear flaps becomes the leading edge and the trailing edge, respectively. On the other hand, when considering the flap and the wing body, respectively, there is a leading edge and a trailing edge on the flap and the wing body, respectively, so that the trailing edge of the leading edge flap is close to the leading edge of the wing body.

Referring to FIG. 4, the wing 40 for an aircraft may be selectively provided with a main body 41 and a rear front flap 43 and a front front flap 42 formed to be rotatable with respect to the main body 41. The leading edge flap 42 is directed forward in the direction of travel of the aircraft. The rear anterior flap 42 is rotatably coupled to the main body 41 via the hinge 44 and the rear anterior flap 43 is rotatably coupled to the main body 41 via the hinge 45. In the state where the flaps 42 and 43 are not rotated, the upper surface of the wing body 41 and the upper surface of the flaps 42 and 43 form a smooth surface without a sudden change in curvature as a whole. Reference numeral 46 and reference numeral 47 denote the portions where the respective flaps 42 and 43 are connected to the wing main body 41, and have a concave-convex shape.

According to one feature of the invention, the bottom surface of the trailing edge of the forefront flap 42 is such that a slot can be formed in at least a portion between the forefront flap 42 and the wing body 41 when the forefront flap 42 is rotated. And a portion corresponding to the leading edge upper surface curvature of the wing body 41 and extending therefrom and spaced apart from the leading edge of the wing body 41. Further, according to another feature of the invention, the trailing edge of the wing body 41, so that at least a portion of a slot can be formed between the trailing front flap 43 and the wing body 41 when the trailing front flap 43 is rotated. The bottom face has a portion that corresponds to the leading edge upper surface curvature of the trailing edge flap 41 and extends therefrom and spaced apart from the leading edge of the trailing edge flap 43. This feature will become more apparent from the description which follows.

Referring to FIG. 5, the front anterior flap 42 and the rear anterior flap 43 are shown pivoted with respect to the wing body 41, respectively, between the flaps 42 and 43 and the wing body 41. Slots 51 and 52 are formed respectively. The formation of these slots 51, 52 is the relative shape between the trailing edge of the leading edge flap 42 and the leading edge of the wing body 41, and the trailing edge of the wing body 41 and the trailing edge flap 42. By the relative shape of the leading edge.

6 (a) and 6 (b) show a cross-sectional view of the portion shown in FIGS. 4A-B and B-B, respectively.

Referring to FIG. 6 (a), the wing body 41 and the leading edge flap 42 remain interconnected through the hinge 44. This connection method is the same as the conventional connection method shown in FIG. 1, and in the present invention, the connection portion through the hinge 44 extends only for a part in the transverse direction of the entire wing.

Referring to FIG. 6 (b), the bottom surface of the trailing edge of the leading edge flap 42 is a portion 65 corresponding to the upper curvature of the leading edge of the wing body 41 and the portion ( And a portion 67 extending from 65 and spaced apart from the leading edge of the wing body 41. Between the spaced portion 67 and the leading edge of the wing body 41 is formed a slot 63 with the top closed. The hinge 44 is installed to penetrate through the vicinity of the center of gravity of the forefront flap 42.

6 (a) and 6 (b) show a cross-sectional view of the portion indicated by A'-A 'and B'-B' in FIG. 5, respectively.

Referring to Fig. 7 (a), the front flap 42 is shown in a pivoted state. The front anterior flap 42 rotates about the hinge 44, and only a predetermined curvature change exists between the front anterior flap 42 and the wing body 41.

Meanwhile, referring to FIG. 7 (b), the front anterior flap 42 rotates around the hinge 44 penetrating the vicinity of the center, and thus the front anterior flap 42 and the wing body ( Between the slots 41 are formed slots 67 with the top open. That is, when the front flap 42 rotates, the bottom part 65 of this trailing edge is spaced apart from the contact state with the leading edge of the blade main body 41, and the slot 67 is formed. Reference numeral 71 denotes a flow of air flowing through the bowl 51. The air supplied in this way can solve the reverse pressure state generated on the upper surface of the wing, thereby maximizing the delay of the delamination phenomenon.

Those skilled in the art will understand that the contents described with reference to FIGS. 7 (a) to 7 (b) may be applied to the interrelationship between the wing body 41 and the trailing front flap 43 as it is. That is, the configuration of the trailing edge of the front leading flap 42 described above is applied to the trailing edge of the wing body 41, and the configuration of the leading edge of the wing body 41 is applied to the leading edge of the trailing front flap 43. It is understood that a slot is formed between the wing main body 41 and the rear front flap 43 to be opened at every rotation over a portion thereof.

8 is a schematic cross-sectional view of another embodiment with other features of the present invention.

Referring to the drawings, this shows a portion of the leading edge flap 42 and the wing body 41 of the aircraft wing, the portion corresponding to the trailing edge of the leading edge flap 42 in FIG. It is formed separately from the member which forms 42, and is provided so that rotation is possible with respect to the front flap 42. As shown in FIG. The trailing edge member 84 formed as a separate member has a bottom surface having a curvature corresponding to the curvature of the upper leading edge of the wing body 41 as described with reference to FIG. 6 (b). The bottom portion of the flap 42 close to the trailing edge member 84 also remains spaced apart from the leading edge of the wing body 41.

The trailing edge member 84 is fixed with respect to the rotation gear 83, and thus can be rotated according to the movement of the rotation gear 83. The rotation gear 83 meshes with the hinge gear 81 provided concentrically with respect to the hinge 44 via a gear train such as transfer gear 82. Therefore, when the hinge 44 is rotated, the rotational force is transmitted to the rotation gear 83 through the transfer gear 82, thereby rotating the rotation gear 83 at a predetermined angle. That is, the rotation of the hinge 44 is linked with the rotation of the trailing edge member 84.

The trailing edge member 84 shown in solid lines in the drawing shows a state in which the slot 51 in the open state is formed by the rotation of the flap 42, and the trailing edge member 85 shown in phantom in the drawing The case where the flap 42 is in the state not rotated is shown. That is, in the state where the flap 42 is not rotated, the upper surface of the upper surface trailing edge member 84 of the flap 42 and the upper surface of the wing body 41 form a smooth flat surface as a whole. On the other hand, when the flap 42 is rotated by the rotation of the hinge 44, the rotation of the hinge 44 is transmitted to the rotation gear 83 through the hinge gear 81 and the transfer gear 82, Thus, the trailing edge member 84 fixed relative to the rotation gear 83 is rotated in a direction parallel to the upper surface of the wing body 41 as shown in the figure. This rotation of the trailing edge member 85 allows the trailing edge member 85 to protrude above the upper surface of the wing body 41, thereby preventing the flow of the wing upper surface from being disturbed.

9 is a schematic cross-sectional view of an embodiment with additional features of the present invention.

Referring to the drawings, a portion of the upper surface of the trailing edge 96 of the leading edge flap 42 is formed of a flexible plate 95, and an upper cut portion 97a and a lower cut portion 97b are formed at the bottom of the trailing edge. Is formed. The preliminary shape of the trailing edge 95 is, as described above, a bottom having a curvature corresponding to the curvature of the upper leading edge of the wing body 41 and extending therefrom to be spaced apart from the leading edge of the wing body 41. Has a portion

The trailing edge 96 is rotated with respect to the flap 42 itself. This action is such that the cuts 97a and 97b are connected to each other according to the rotation of the flap 42, or the upper cut 97a is connected to the flap 42. This is done by entering inside of. That is, in the rotation state of the flap 42 shown by the solid line in the figure, the trailing edge 96 is rotated by the upper cut portion 97a entering the inside of the flap 42. On the contrary, when the flap 42 is not rotated as shown by the virtual line in the figure, the upper cut portion 97a and the lower cut portion 97b are connected to each other.

A hinge gear 44 concentrically installed at the center of rotation of the hinge 44, a hinge 44, a transfer gear 92 for transmitting rotational force so as to generate rotation of the trailing edge 96, The tension gear 93 meshed with the transfer gear and a cable 94 fixed at one end of the trailing edge 96 and the other end fixed to the tension gear 93 are provided. Rotation of the hinge 44 causes the flap 42 to rotate, which cooperates with the rotation of the trailing edge 96. When the hinge 44 is rotated, the rotation gear of the hinge gear 91 rotates, and the transfer gear 92 and the tension gear 93 meshed thereto rotate. One end of the tension gear 93 is fixed to the end of the cable 94, the cable 94 is guided along the circumference of the tension gear (93). The rotation of the tension gear 93 thus provides tension to the cable 94, and the trailing edge 96 fixed at the other end of the cable 94 rotates with respect to the flap 42. At this time, the upper cut portion (97a) is to enter the inside of the flap (42). Conversely, when the flap 42 returns to its original position, the trailing edge 96 returns to the shape as indicated by the imaginary line 98 by the reverse action of the operation described above. Rotation of the trailing member 96 as above allows the trailing edge 96 to protrude above the upper surface of the wing body 41, thereby preventing the flow of the wing upper surface from being disturbed.

The aircraft wing described with reference to FIGS. 4 to 9 can be applied to the vertical wing as well as the horizontal wing. In particular, the trailing edge pivot mechanism of the front fore flap described with reference to FIGS. 8 and 9 can be applied to the pivoting edge of the wing body between the wing body and the rear fore flap.

Aircraft wing according to the present invention has the advantage that can be delayed as much as possible the flow separation phenomenon occurring on the upper surface of the wing during the high angle of flight of the aircraft. In particular, the present invention rotates the flap by a simple hinge, it has the advantage that it is easy to apply to the aircraft of the medium size or less that the thickness of the wing is formed thin. In addition, the present invention has the advantage that it can be applied to military purpose aircraft requiring high maneuverability and high lift.

Although the present invention has been described with reference to one embodiment shown in the accompanying drawings, this is only illustrative, and it will be understood by those skilled in the art that various modifications and equivalent other embodiments are possible. Could be. Therefore, the true scope of protection of the present invention should be defined only by the appended claims.

Claims (9)

The wing body and the leading edge of the wing body is rotatably installed, and a slot is formed at a part of the connection portion with the wing body at the time of rotation so that air flowing along the bottom surface of the wing body is For aircraft having a leading edge flap having a bottom surface of the trailing edge corresponding to the top surface curvature of the leading edge of the wing body and a portion extending therefrom and spaced apart from the leading edge of the wing body so as to flow upwardly wing. 2. The wing of claim 1, wherein the wing body and the front flap are interconnected through a hinge at a portion that does not form a slot. The top surface of the slot is closed by forming an overall smooth surface between the upper surface of the forefront flap and the upper surface of the wing body in the state that the front anterior flap is not rotated with respect to the wing body. In the state that the flap is rotated with respect to the wing body, the aircraft wing, characterized in that air flows through the slot formed on the trailing edge of the leading edge flap and the wing body. According to claim 2, It is provided on the hinge further comprises a gear train for transmitting the rotation of the hinge, and a trailing edge member formed separately from the member for forming the leading edge flap on the trailing edge portion of the front edge flap, And the trailing edge member is fixed with respect to one of the gear trains so that the trailing edge member is interlocked with respect to the rotation of the front leading flap. 5. The trailing edge according to claim 4, wherein the trailing edge member upper surface of the forefront flap is parallel to the upper surface of the wing body by the rotation of the gear train when the leading edge flap rotates with respect to the wing body. An aircraft wing, characterized in that the member rotates. 3. The gear train of claim 2, further comprising: a gear train for transmitting the rotation of the hinge, the flexible member integrally formed with a portion of the upper surface of the trailing edge of the front forearm flap, and one end of which is provided on the trailing edge of the front forearm flap. The other end is fixed to one of the gear trains, and has a cable guided along the circumferential surface of the gear, the trailing edge of the trailing edge of the forefront flap being cut so that the trailing along the rotation of the forefront flap An aircraft wing, characterized in that the cut top of the edge is formed to enter the inside of the leading edge flap. The top surface of the trailing edge of the forefront flap according to claim 6, wherein the gear train rotates when the forefront flap is rotated with respect to the wing body. An aircraft wing characterized in that it is rotated to a position parallel to the upper surface. And a wing body and a rear front flap rotatably installed at a trailing edge of the wing body, wherein a slot opened at a portion of a connection portion between the wing body and the rear front flap is formed when the rear front flap rotates. The bottom surface of the trailing edge of the wing body corresponds to the upper surface curvature of the leading edge of the trailing front flap and extends therefrom so that air flowing along the bottom surface of the wing body flows to the top surface of the wing body. Wings for aircraft having portions spaced from leading edges. The wing of claim 8, wherein the wing body and the rear front flap are interconnected through a hinge at a portion where the slot is not formed.

Images