KR20200006470A - Wing having self-adaptive deforming projection - Google Patents

Abstract

According to one embodiment, a wing having a self-adaptive deforming protrusion can include: a frame forming a framework; a film covering the frame to form an outer cover; and a protrusion selectively formed on the film, wherein the frame is partially retracted by external force in the film. According to retraction of a part of the frame, the film attached to the frame is also deformed so that the protrusion can be formed.

Description

Wings with self-adaptive deformation projections {WING HAVING SELF-ADAPTIVE DEFORMING PROJECTION}

A wing having a self-adaptive deformation protrusion is disclosed. Specifically, the wing angle (Angle Of Attack (AOA)) of the wing is changed according to the flight of the vehicle, and the wing is provided with a self-adaptive deformation protrusion projecting the protrusion by changing the appearance of the wing according to the change of the angle of attack.

When flying, depending on various situations, the leading edge of the wing and the air hitting the wing may be out of alignment. That is, the angle of the wing and the angle of the air may be shifted, and thus the angle of attack between the wing and the air may be changed.

Stalling may occur due to the change in the angle of attack between wings and air. Stalling refers to a phenomenon in which the air flow around a wing changes to turbulence or vortex, causing the wing to lose its lift rapidly.

Therefore, the aircraft must be operated while maintaining the angle of attack within the stall angle to prevent accidents due to loss of lift.

The fin of a humpback whale has protrusions projecting forward on the leading edge portion. Through these projections, humpback whales can delay or prevent stalling.

Specifically, the protrusion projecting from the wing hits the flow of air applied in the direction of the leading edge of the wing to break the air flow. That is, the protrusions may break the flow of air hitting the wings by the concave surface formed between the protrusions and the protrusions to form vortices, and the formed vortices may flow along the surface of the wings to resist stall.

The U.S. Navy conducted wind tunnel tests using wings with smooth wings and small projections, which resulted in 8% improved lift and 32% less drag than conventional wings. Experiments with wings with small projections also yielded experimental data indicating that they resisted stalling even at steep angles of attack of 40 degrees.

The invention for delaying or alleviating such a stall phenomenon is specifically disclosed in Korean Patent No. 10-2014-0099197 'Swirl generator and vortex generating method'.

An object according to an embodiment is to provide a wing having a cost-effective self-adaptive deformation projection can be implemented in a simple structure self-deformation projection.

Another object according to an embodiment is to provide a wing having a self-adaptive deformation protrusion that can improve the lift of the wing at various angles of attack.

Another object according to an embodiment is to provide a wing having a self-adaptive deformation protrusion that can reduce the drag of the wing to improve fuel efficiency.

Another object according to an embodiment is to provide a wing having a self-adaptive deformation protrusion capable of delaying or alleviating stalling of the wing.

Another object according to one embodiment is to provide a wing having a self-adaptive deformation projection that can improve the stability of the vehicle during driving, takeoff, landing.

Another object according to an embodiment is to provide a wing having a self-adaptive deformation protrusion that is applied to a rudder of a vehicle or a vessel to reduce the radius of rotation during steering.

The wing having a self-adaptive deformation protrusion according to an embodiment for achieving the above object may include a frame constituting the skeleton, a film covering the frame to form an envelope and a protrusion selectively formed on the film, The frame is partially retracted by an external force inside the film, and the film attached to the frame may also be deformed to form the protrusion as the part of the frame is retracted.

In addition, the frame of the wing having a self-adaptive deformation protrusion according to an embodiment may include a fixed frame and a moving frame arranged in a line, the moving frame may be retracted with respect to the fixed frame by an external force The film may be attached to each of the movable frame and the fixed frame, and may be retracted together with the movable frame to form the protrusion according to the retraction of the movable frame.

In addition, the fixed frame of the wing having a self-adaptive deformation protrusion according to an embodiment may include a first frame having a droplet-shaped cross-section, the moving frame is a second frame having a cut droplet-shaped cross-section It may include, the cross-sectional shape of the front end portion of the second frame may be the same as the cross-sectional shape of the front end portion of the first frame.

In addition, the fixed frame of the wing having a self-adaptive deformation protrusion according to an embodiment may include a plurality of first frames, the moving frame may include a plurality of second frames, a plurality of the first One frame and the plurality of second frames may be arranged to overlap each other.

In addition, the frame of the wing having a self-adaptive deformation projection according to an embodiment may further include a reaction force member disposed between the movable frame and the fixed frame, the reaction force member corresponding to the external force is added The moving frame may be advanced to prevent retraction of the moving frame or to arrange the moving frame in line with the fixed frame.

In addition, the fixed frame of the wing having a self-adaptive deformation projection according to an embodiment may further include a third frame disposed behind the moving frame, the reaction force member is the rear of the moving frame and the first It is disposed between the three frames, it can generate a reaction force for the movement of the moving frame.

In addition, the fixed frame of the wing having a self-adaptive deformation protrusion according to an embodiment may further include a fourth frame and the linear ball bearing disposed in the rear of the movable frame and in front of the third frame. The moving frame may include a central axis protruding in the direction of the third frame from the center of the front end portion of the moving frame, and the central axis may pass through the fourth frame and the linear ball bearing.

In addition, the reaction force member of the wing having a self-adaptive deformation projection according to an embodiment may be formed of a spring having elasticity.

In addition, the film of the wing having a self-adaptive deformation protrusion according to an embodiment may be provided with an elastic to change the shape to form the protrusion by the frame is deformed according to the change in the angle of attack of the wing.

According to the wing having the self-adapting deformation protrusion according to an embodiment, it is possible to provide a wing having a cost-effective self-adapting deformation protrusion can be implemented in a simple structure.

In addition, according to the wing having a self-adaptive deformation protrusion according to an embodiment, it may be provided with a wing having a self-adaptive deformation projection that can improve the lift force of the wing at various angles of attack.

In addition, according to the wing having a self-adapting deformation projection according to an embodiment, it may be provided with a wing having a self-adapting deformation projection that can reduce the drag drag of the wing to improve fuel efficiency.

In addition, according to the wing having a self-adapting deformation projection according to an embodiment, it may be provided with a wing having a self-adapting deformation projection that can delay or alleviate the stall phenomenon of the wing.

In addition, according to the wing having a self-adapting deformation projection according to an embodiment, it may be provided with a wing having a self-adapting deformation projection that can improve the stability when the vehicle is running, take off, landing.

In addition, according to the wing having a self-adaptive deformation projection according to an embodiment, it may be provided with a wing having a self-adaptive deformation projection that is applied to the rudder of the aircraft or the vessel can reduce the radius of rotation during steering. .

1 is a perspective view of an inner frame of a wing having a self-adapting deformable protrusion according to an embodiment.
2 illustrates a change in the shape of a protrusion of a wing having a self-adapting deformation protrusion according to an embodiment.
Figure 3 illustrates a change in lift according to the shape of the protrusion of the wing having a self-adaptive deformation projection according to an embodiment.
4 is a plan perspective view of a wing having a self-adaptive deformation protrusion according to one embodiment.
5 is a cross-sectional view of a wing having a self-adaptive deformation protrusion according to one embodiment.

Hereinafter, embodiments will be described in detail with reference to exemplary drawings. In adding reference numerals to the components of each drawing, it should be noted that the same reference numerals are used to refer to the same components as much as possible, even if displayed on different drawings. In addition, in describing the embodiment, when it is determined that the detailed description of the related well-known configuration or function interferes with the understanding of the embodiment, the detailed description thereof will be omitted.

In addition, in describing the components of the embodiment, terms such as first, second, A, B, (a), and (b) may be used. These terms are only for distinguishing the components from other components, and the nature, order or order of the components are not limited by the terms. If a component is described as being "connected", "coupled" or "connected" to another component, that component may be directly connected or connected to that other component, but there is another component between each component. It will be understood that may be "connected", "coupled" or "connected".

Components included in any one embodiment and components including common functions will be described using the same names in other embodiments. Unless stated to the contrary, the description in any one embodiment may be applied to other embodiments, and detailed descriptions thereof will be omitted in the overlapping range.

1 illustrates a perspective view of an inner frame 110 of a wing 100 having a self-adaptive deformation protrusion 130 according to an embodiment, and FIG. 4 illustrates a self-adaptive deformation protrusion 130 according to an embodiment. A plan perspective view of a wing 100 provided, FIG. 5 shows a cross section of a wing 100 having a self-adaptive deformation protrusion 130 according to one embodiment.

1, 4, and 5, the wing 100 including the self-adapting deformation protrusion 130 according to an embodiment may include a frame 110, a film 120, and a protrusion 130. have.

Frame 110 may be a skeleton constituting the body of the wing 100, it may include a fixed frame 112 and the moving frame 114 in its lower configuration. The fixed frame 112 and the moving frame 114 may be arranged in a line at the tip (leading edge) position of the wing (100). The frame 110 may be changed in shape by an external force such as gravity. Specifically, the frame 110 is disposed inside the film 120, and a portion (moving frame 114) may be retracted by the external force (relative to the fixed frame 112).

In addition, the frame 110 may be changed to prevent stall of the wing 100 according to the angle of attack of the wing 100.

The film 120 covers the frame 110 to form an envelope. Specifically, the film 120 is attached to each of the fixed frame 112 and the moving frame 114 in the frame, so that the film 110 may change together as the shape of the frame 110 changes. have. That is, a part of the film 120 attached to the moving frame 114 may be retracted as the moving frame 114 is retracted to deform the shape of the film 120. Accordingly, the protrusion 130 may be formed on the surface of the wing 100. This is explained in more detail below.

Specifically, the film 120 may have elasticity to form a protrusion 130 by changing the shape by the frame 120 deformed according to an external force according to a change in the angle of attack of the wing 100.

The protrusion 130 may be formed of the fixed frame 112 and the film 120 attached to the fixed frame 112 that remain in place as the moving frame 114 and the film 120 retreat. In addition, the protrusion 130 may be removed when the moving frame 114 returns to the front and the moving frame 114 and the fixed frame 112 are rearranged in a line with each other (see FIGS. 2A to 2D).

Fixed frame 112 may be composed of a plurality of first frame 1122 having a droplet-shaped cross section, such as wings commonly used in the art, the moving frame 114 is also a plurality of cut droplet-shaped cross-section It may be composed of a second frame 1142.

The end surfaces of the first frame 1122 and the second frame 1142 may be identically formed. More specifically, referring to FIG. 1, the cross section of the tip end of the first frame 1122 may be a curved surface, and the cross-sectional curved end surface of the second frame 1142 may be a curved surface. The leading curved surfaces of the first frame 1142 and the second frame 112 may have the same diameter and may have the same shape so that the surface of the wing 100 is smooth.

As shown in the drawings, each of the plurality of first frames 1122 and the plurality of second frames 1142 may be disposed to overlap each other, and the second frames 1142 may be disposed in the first frames ( 1122 may be moved backwards.

4A is a top perspective view briefly illustrating an initial state of a wing 100 with a self-adapting deformable protrusion 130 according to one embodiment.

FIG. 4B is a plan perspective view briefly illustrating a state in which protrusions 130 of a wing having less self-deformation protrusions 130 protrude.

4A and 4B, the frame 110 may further include a reaction force member 116 disposed between the movable frame 114 and the fixed frame 112.

The reaction force member 116 prevents the retreat of the moving frame 114 in response to an external force, for example, gravity, which is added to the wing 100 or moves to the initial position where the moving frame 114 is aligned with the fixed frame 112. The moving frame 114 may be advanced to turn.

Specifically, the fixed frame 112 may further include a third frame 1124 disposed behind the moving frame 114. In addition, the plurality of second frames 1142 included in the moving frame 114 may be integrally formed with their rear parts connected to each other. A reaction force member 116 may be disposed between the second frame 1142 and the third frame 1124. When the second frame 1142 is retracted backward by an external force, the third frame 1124 and the second frame 1124 may be disposed. The reaction force member 116 between the frames 1142 may elastically store the potential energy as much as the retraction of the second frame 1142.

Therefore, the elasticity accumulated in the reaction force member 116 may be in equilibrium with an external force added to the wing 100, and when the external force decreases, the elasticity of the reaction force member 116 may be converted into kinetic energy to form the second frame 1142. Can move forward. That is, the reaction force member 116 may generate reaction force for the movement of the movement frame 114. To this end, the reaction force member 116 may have an elasticity, preferably a spring.

Referring to FIG. 4A, the initial shape of the wing 100 may be arranged in parallel with the movable frame 114 and the fixed frame 112, and the reaction force member 116 may be in a relaxed state.

Referring to FIG. 4B, the moving frame 114 may be retracted backward according to the external force, and thus the reaction force member 116 may contract by the moving amount of the moving frame 114.

2 illustrates a shape change of the protrusion 100 of the wing having the self-adapting deformation protrusion 130 according to an embodiment, and FIG. 3 is provided with the self-adapting deformation protrusion 130 according to an embodiment. Lifting change according to the shape of the protrusion 130 of the wing 100 is shown as a graph.

FIG. 2A shows the initial shape of the wing 100, and FIGS. 2B-2D show the wing 100 with the protrusions 130 protruding slowly.

In the graph of FIG. 3, the y-axis denotes a lift coefficient and the x-axis denotes an angle of attack.

The line L1 of FIG. 3 shows the change of lift according to the angle of attack in the shape L1 of the blade 100 shown in FIG. 2A, and the lift loss around 20 degrees means stall.

The line L2 of FIG. 3 shows the change of lift according to the angle of attack in the wing 100 shape L2 shown in FIG. 2B, and the line L3 of FIG. 3 shows the shape of the wing 100 L3 shown in FIG. 2C. ), The change in lift according to the change of angle of attack, and the line L4 in FIG. 3 shows the change in lift according to the angle of change in the wing shape 100 L3 shown in FIG. 2D.

The line L5 of FIG. 3 is a projection 130 which changes according to an external force, for example, the angle of attack of the wing 100 includes the tilting of the wing 100, and the wing (according to the tilting of the wing 100). The gravity added to the moving frame 114 in the 100 is changed, and the lift coefficient versus lift angle is measured as the moving frame 114 is retracted according to the gravity and the protrusion 130 gradually protrudes.

Referring to line L5 of FIG. 3, an optimal lift coefficient relative to the angle of attack can be achieved without an optimal stall phenomenon.

As shown in FIG. 3, when the protrusion 130 is formed by the movement of the moving frame 114, a stall phenomenon caused by a change in the angle of attack may be delayed or alleviated.

Specifically, the shape of the conventional wing in Figure 3 shows the highest lift at a low angle of attack, but stall occurs near the angle of attack 20 degrees, the lift is reduced. On the other hand, as the angle of attack after stalling gradually increases, a wing having a progressively deep protrusion may have a high lift in proportion to it. Wings with improved deformation projections not only have high lift at low angles of attack, but also abruptly change or suppress sudden changes in lift at angles of attack of more than 20 degrees.

FIG. 5A illustrates a cross-sectional view of an initial state of the wing 100 having the self-adapting deformation protrusion 130 according to an embodiment, more specifically to FIG. 4A.

5B illustrates a cross-sectional view of the protrusion 130 of the wing 100 having the self-adapting deformation protrusion 130, according to one embodiment, in more detail.

Specifically, FIG. 5A illustrates an initial cross section of a wing 100 having a self-adapting deformation protrusion 130 according to an embodiment, and FIG. 5B is a wing having a self-adapting deformation protrusion 130 according to an embodiment. The state in which the protrusion 130 protrudes to 100 is shown.

5A and 5B, the fixing frame 112 of the wing 100 having the self-adapting deformation protrusion 130 according to an embodiment further includes a fourth frame 1126 and a linear ball bearing 1128. In addition, the moving frame 112 may include a central axis 1144.

The central axis 1144 may extend from the distal end of each of the plurality of second frames 1142 in the direction of the third frame 1124 rearward (to cross the inside of the second frame). An end of the central axis 1144 may be connected to the third frame 1124 through the reaction force member 116. That is, the reaction force member 116 may be disposed between the distal end of the central axis 114 and the third frame 1124.

The distal portions of the plurality of central axes 1144 may be connected to each other to connect the plurality of second frames 1142.

The fourth frame 1126 may be disposed in parallel with the third frame 1124 in front of the third frame 1124. A plurality of openings may be formed in the fourth frame 1126, and the plurality of openings may be penetrated by the central axis 1144.

The rear end of the second frame 1142 may protrude in the direction of the central axis, and the protruding portion of the second frame 1142 may contact the fourth frame 1126. That is, when the moving frame 112 is retracted, the protruding portion of the second frame 1142 may be contacted with the retreat while being spaced apart from the fourth frame 1126, which is excessive retraction of the moving frame 112. Can be prevented.

A linear ball bearing 1128 may be disposed behind or in front of the opening of the fourth frame 1142. Accordingly, the central axis 1144 may penetrate the linear ball bearing 1128 together with the opening, and the linear ball bearing 1128 may allow only vertical movement of the central axis 1144 and prevent rotation or horizontal movement. have.

Accordingly, the wing 100 having the self-adapting deformation protrusion 130 according to an embodiment can be implemented in a simple structure of the self-deforming protrusion is cost-effective, and automatically improves the lift of the wing 100 at various angles of attack. It is possible to reduce the drag of the wing 100 to improve the fuel efficiency.

In addition, the wing 100 having the self-adapting deformation protrusion 130 according to an embodiment may delay or alleviate stall phenomenon of the wing 100, and may improve stability when the vehicle is driven, taken off, or landed. In addition, it is applied to the rudder of the aircraft or the ship can reduce the radius of rotation during steering.

As described above, the embodiments of the present invention have been described by specific embodiments, such as specific components and the like, but the embodiments and the drawings are provided only to help the overall understanding of the present invention, and the present invention is limited to the above embodiments. Various modifications and variations can be made by those skilled in the art to which the present invention pertains. For example, the described techniques may be performed in a different order than the described method, and / or components of the described structure, apparatus, etc. may be combined or combined in a different form than the described method, or may be combined with other components or equivalents. Appropriate results can be achieved even if they are replaced or substituted. Accordingly, the spirit of the present invention should not be limited to the described embodiments, and all of the equivalents or equivalents of the claims as well as the claims below will belong to the scope of the present invention. .

100: wings
110: frame
112: fixed frame
1122: first frame
1124: third frame
1126: fourth frame
1128: Linear Ball Bearing
114: moving frame
1142: second frame
1144: central axis
116: reaction force member
120: film
130: projection

Claims (9)

Frames that make up the armature;
A film covering the frame to form an envelope; And
Protrusions selectively formed on the film;
Including,
And the frame is partially retracted by an external force inside the film, and the film attached to the frame is also deformed as the part of the frame is retracted so that the protrusions are formed.
The method of claim 1,
The frame includes a fixed frame and a moving frame arranged in a line,
The moving frame is retracted with respect to the fixed frame by an external force,
The film is attached to each of the movable frame and the fixed frame, the wing having a self-adaptive deformation projection is retracted with the movable frame to form the protrusion in accordance with the retraction of the movable frame.
The method of claim 2,
The fixed frame includes a first frame having a droplet-shaped cross section,
The moving frame includes a second frame having a cut droplet-shaped cross section,
A blade having a self-adaptive deformation protrusion, wherein the tip cross-sectional shape of the second frame is the same as the tip cross-sectional shape of the first frame.
The method of claim 2,
The fixed frame includes a plurality of first frames,
The moving frame includes a plurality of second frames,
The plurality of the first frame and the plurality of the second frame is a wing having a self-adaptive deformation projection, each disposed to overlap.
The method of claim 2,
Further comprising a reaction force member disposed between the movable frame and the fixed frame,
The reaction force member is a wing having a self-adaptive deformation projection to prevent the retreat of the moving frame in response to the external force added or to advance the moving frame so that the moving frame is arranged in line with the fixed frame.
The method of claim 5,
The fixed frame further includes a third frame disposed behind the moving frame,
The reaction force member is disposed between the rear of the movable frame and the third frame,
A wing having a self-adaptive deformation protrusion for generating a reaction force to the movement of the moving frame.
The method of claim 6,
The fixed frame further comprises a fourth frame and the linear ball bearing disposed in the rear of the movable frame and in front of the third frame,
The moving frame includes a central axis protruding in the direction of the third frame from the center of the front end of the moving frame,
And a central axis passing through the fourth frame and the linear ball bearing.
The method of claim 5,
The reaction force member is a wing having a self-adaptive deformation protrusion formed of a spring having elasticity.
The method of claim 1,
The film has a self-adaptive deformation projections having elasticity to form a projection by changing the shape by the frame is deformed in accordance with the angle of attack of the wing.

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