WO2012077857A1

WO2012077857A1 - Airplane equipped with a wing booster

Info

Publication number: WO2012077857A1
Application number: PCT/KR2011/000644
Authority: WO
Inventors: 이진규
Original assignee: Ree Jinkyue
Priority date: 2010-12-07
Filing date: 2011-01-31
Publication date: 2012-06-14
Also published as: KR20120063248A; KR101239918B1

Abstract

The present invention relates to an airplane equipped with a wing booster. An airplane (1), which includes a fuselage (3) forming the body thereof and a main wing (5) coupled to intersect the central portion of the fuselage, is characterized by comprising: one or more intakes (11) formed in the main wing (5) and through which outside air flows into the main wing (5); one or more blower means (13) surrounded by a cladding (21) of the main wing (5) and disposed corresponding to the intake (11) to accelerate the outside air flowing in through the intake (11) along the length of the main wing (5) and to diffuse the air; a driving means (15) for driving the rotation of the blower means (13); an exhaust (17), open rearward along the leading edge of the top surface (23) of the main wing (5), for exhausting the outside air accelerated by the blower means (13) along the surface layer of the top surface (23) of the main wing (5); and a passage means (19), connecting the intake (11) and the exhaust (17), for compressing and diffusing the outside air accelerated by the blower means (13) disposed next to the intake (11) toward the exhaust (17). Thus, especially during takeoff, outside air which has flowed into the main wing through the intake is compressed and diffused at high speed by the blower means and is discharged through the exhaust and evenly diffused along the surface layer of the top surface of the main wing so as to significantly shorten takeoff time by increasing the lift at the main wing and to greatly improve the comfort of the flight for passengers.

Description

Airplane with wing booster

The present invention relates to an airplane provided with a wing booster, and more particularly, by amplifying the lift force at take-off, and in the main wing to form a power structure that can compensate for the propulsion force during the flight to significantly reduce the run distance and the range The present invention relates to an airplane having a wing booster.

The plane is a vehicle that lifts the main wing by thrust by propeller or jet injection as well as the air, and is composed of the fuselage, main wing, and the tail bar, and the speed difference of the air flow passing through the top and bottom surfaces of the main wing. And the body is lifted by the lift generated by the pressure difference.

By the way, the conventional structure of such an airplane can not arbitrarily adjust the lift on the main wing other than optimizing the profile of the main wing. Of course, the lift strength can be partially adjusted by the flap when descending or rising, but the lift change In addition, since the drag also changes, it cannot be said that only pure lift is adjusted, so there is a limit that the overall lift on the main wing cannot be changed.

The present invention has been made to solve the above-mentioned conventional problems, by increasing or changing the lifting force on the main wing during flight or takeoff, significantly shortening the time taken for takeoff, and the resulting time duration, and take off The aim is to improve flight control during flight.

The present invention to achieve the above object is the body forming the body; And a main wing transversely coupled to the middle portion of the fuselage, the plane comprising: at least one air inlet through the upper constituting the plane to allow outside air to flow into the interior of the plane; At least one blowing means surrounded by the upper of the main blade and disposed to correspond to the intake port, thereby accelerating and diffusing outside air introduced through the intake port in the longitudinal direction of the main blade; Driving means for rotating the blowing means; An exhaust port opened rearward along an upper end surface of the main blade to discharge external air accelerated by the blower to flow along the upper surface surface layer of the main blade; And a conduit means for connecting the intake port and the exhaust port to compress and spread outside air accelerated by the blowing means disposed adjacent to the intake port toward the exhaust port. do.

In addition, the intake port is preferably opened in a state in which a plurality of the inlet is spaced apart from each other along the front end of the main wing.

In addition, the blowing means is preferably a cone-shaped radial fan protruding sharply toward the body opposite side to refract the direction of incidence of the outside air flowing through the intake port in the longitudinal direction of the main blade.

In addition, the blowing means is arranged in a position adjacent to the intake port in a one-to-one correspondence to the plurality of the intake port opened in a state spaced apart from each other on the front of the upper along the tip of the main blade, the synchronous rotation by the drive means It is desirable to do so.

In addition, the conduit means is preferably in the form of a funnel in which the cross-sectional area is gradually reduced from the blade root portion of the main blade widened to accommodate the outside air blown from the blowing means to the exhaust port narrowed to discharge the outside air along the top surface surface of the main blade. Do.

In addition, the intake port is preferably opened through the upper at the bottom of the body.

In addition, the blowing means is on the inner bottom surface of the fuselage so that the hub protrudes sharply into the fuselage in order to refract the direction of incidence of the outside air flowing through the intake port from the bottom of the fuselage in the longitudinal direction of the left and right main wing. It is preferable that it is a conical radial fan mounted behind the inlet port.

In addition, the conduit means is in the form of a funnel in which the cross-sectional area is gradually reduced from the blade root portion of the main blade widened to accommodate the outside air blown from the blowing means to the exhaust port narrowed to discharge the outside air along the top surface surface of the main blade, It is preferable that the guide vanes protrude on the inner wall surface of the body facing the blowing means so as to branch the outside air introduced from the intake port to the left and right main wings about the blowing means.

In addition, the guide vane has a central portion protrudes sharply toward the blowing means to branch the outside air blown by the blowing means to the left and right, the air volume control plate that can adjust the air volume of the branched outside air blowing means It is preferable to be pivotally installed by the rotating shaft mounted to the tip portion toward.

In addition, it is mounted to the upper end surface of the main wing so as to move up and down to form a profile that maintains the airfoil of the main wing when aligned with the upper of the upper end of the exhaust port by rising from the upper end surface, while the rear end of the main wing It is preferable to further include a double upper formed in the injection port to inject the outside air discharged from the exhaust port through the injection port.

In addition, the double upper is preferably configured to be movable up and down by a plurality of scissor lifts mounted between the upper end surface of the main blade.

In addition, the double upper is preferably divided into a plurality of divided along the longitudinal direction of the main wing to be selectively moved up and down for each divided portion it is possible to be different from the height of the arrangement.

1 is a schematic perspective view of an airplane having a wing booster according to an embodiment of the present invention.

FIG. 2 is a front view of the plane shown in FIG. 1. FIG.

Figure 3 is a schematic cross-sectional view showing a right side including the main wing of the airplane shown in FIG.

4 is a front view of an airplane according to another embodiment of the present invention.

Figure 5 is a schematic cross-sectional view showing a right side surface including the main wing of the airplane according to another embodiment of the present invention.

Figure 6 is a perspective view showing in detail the blowing means shown in Figures 1, 3 and 5.

7 is a plan view of the conduit means shown in FIG.

8 is a cross-sectional view of the main wing shown in FIG. 1.

Figure 9 is a schematic perspective view of a plane having a wing booster according to another embodiment of the present invention.

10 is a cross-sectional view of the main wing shown in FIG. 9.

FIG. 11 is a detailed sectional view of the scissor lift shown in FIG. 9; FIG.

12 is a partial cutaway front view of an airplane according to another embodiment of the present invention.

FIG. 13 is a partial cutaway side view of FIG. 12. FIG.

14 is a partial perspective view showing in detail the blowing means and the duct means of FIG.

Hereinafter, a plane equipped with a wing booster according to an embodiment of the present invention will be described with reference to the accompanying drawings.

The plane of the present invention has a structure named wing booster in the sense that it can boost the lift of the main wing, as shown by the reference numeral 1 in Figs. 1 and 2, the fuselage 3 and the main wing (5) An airplane comprising: an inlet 11, at least one blowing means 13, a driving means 15, an exhaust port 17, and a conduit means 19.

Here, the fuselage (3) is a portion constituting the body of the plane, the main blade (5) is a wing that is laterally coupled to the middle portion of the fuselage (3), a well-known configuration bar its detailed description is omitted.

On the other hand, the at least one inlet 11 is a portion to allow the outside air to enter the inside of the main blade (5), as shown in Figure 1 and 2, bar penetrating the portion of the tip 26 of the main blade (5) As shown in FIG. 4, it is preferable to be formed to penetrate the front surface of the upper 21 at the wing portion of the main blade 5 adjacent to the streamline of the outside air flowing along the surface of the fuselage 3, ie adjacent to the fuselage 3. A plurality of openings are spaced apart from each other on the front surface of the upper 21 in the longitudinal direction of the main blade 5 along the tip 26 of the main blade 5, that is, at a right angle to the fuselage 3. May be At this time, each inlet 11 is formed to be almost the same height as the thickness of the main blade (5), as shown in Figures 2 and 4 can be opened in various forms, such as open in a louver type on the front of the upper 21. have.

The at least one blower means 13 is a boosting fan that boosts the lift of the main blade 5, and accelerates and spreads outside air introduced through the intake port 11 in the longitudinal direction of the main blade 5 through the conduit means 19. As shown in FIG. 3, the outer wall or main blade 5 of the fuselage 3 is disposed to be adjacent to the inside of the intake port 11 and is installed at the blade root portion of the main blade 5 surrounded by the upper 21. It is mounted on the inner circumferential surface of the, but when there is only one inlet 11 is formed in the root portion as shown in Figure 2, as shown in Figure 3 there is only one blower means right inside, but in Figure 4 As illustrated, when the plurality of air inlets 11 are opened in a state spaced apart from each other on the front surface of the upper 21 along the tip 26 of the main blade 5, a plurality of blowers may correspond to the respective air inlets 11 one-to-one. The means 13 may be arranged in adjacent positions. At this time, each blowing means 13 is coaxially mounted on the rotational shaft 45 extending in the longitudinal direction of the main blade 5 to be synchronously rotated by one driving means 15 as shown in FIG. . However, each blowing means 13 may of course be driven by separate driving means, respectively.

As such, the blowing means 13 refracts the incidence direction of the outside air introduced through the inlet 11 in the longitudinal direction of the main blade 5 so as to be discharged along the conduit means 19 to the exhaust port 17. Although a blower of the type may be used, the hub 31 may be a body 3 among radial fans in which a plurality of spiral wings 47 are protruded on the hub, as shown in FIGS. 3, 5, and 6. It is preferable that it is a conical radial fan which protrudes sharply toward the opposite side of ().

The driving means 15 is a driving means such as an engine and a motor for rotationally driving the blowing means 13, but is schematically illustrated in FIGS. 3 and 5, but is mounted on the side wall of the body 3 or as shown in FIG. It can be mounted on the inner wall of the upper 21 of (5), and the blowing thrust of the blower means 13 is rotated by rotating the blower means 13 through various types of transmission means such as belts or gears regardless of the mounting position. It is only necessary to point the exhaust port 17 along the conduit means 19 in the longitudinal direction of 5).

The exhaust port 17 is a means for discharging the outside air introduced into the conduit means 19 of the main blade 5 through the inlet 11 along the entire length of the main blade 5, FIGS. 2, 3, and 7. 8 is laterally elongated along the tip of the top surface 23 of the main blade 5 and relatively thinner than the thickness of the main blade 5 and is open to the rear, thus providing air to the blowing means 13. The outside air accelerated by the exhaust port 17 is evenly distributed throughout the upper surface 23 surface layer from the front end 26 to the rear end of the main wing 5 so that the main air flow 5 can be divided into, for example, curtain flow. Take the top surface 23 to flow at high speed.

Finally, the conduit means 19 is a means for connecting the inlet port 11 and the exhaust port 17 as described above, as shown in Fig. 1, 3, 7 the outside air introduced into the inlet port 11 (11) Accelerated by the air blowing means 13 disposed adjacent to the rear side, the gas is gradually compressed toward the exhaust port 17 and diffused to the entire exhaust port 17 to be discharged. To this end, the conduit means 19 is a curtain flow in the form of a curtain flow along the surface of the upper surface 23 of the main blade 5 at the root portion of the main blade 5 widened to accommodate all the outside air transmitted from the blowing means 13. Although it is preferable to form a funnel in which the cross-sectional area is gradually reduced to the exhaust port 17, which is relatively narrowed to discharge, gradually, to the relatively narrow exhaust port 17, the outside air introduced through the first relatively large inlet 11 is gradually formed. Any form may be used as long as it can be compressed and widened and discharged through a long narrow vent.

On the other hand, it is possible to install a double upper 41 on the upper surface 23 of the main blade 5, this double upper 41, as shown in Figs. 9 and 10, the upper surface of the main blade (5) It is mounted so as to be movable up and down at 23, when it is in the lower position as shown in FIG. 9, that is, when it is superimposed on the upper surface 23 of the main blade 5, the main blade 5 is similar to the upper surface 23. ) To form an upper surface layer so that outside air discharged from the exhaust port 17 flows along the upper surface 49. As a result, the velocity of the airflow flowing through the upper surface 49 of the double upper 41 is also faster by the outside air discharged from the exhaust port 17, so that the lift force applied to the main blade 5 is increased accordingly. The position of 41 is called the boosting position for convenience.

On the contrary, the double upper 41 is aligned with the upper end 25 of the upper end of the exhaust port 17 when the double upper 41 is raised from the upper surface 23 as shown in FIG. The exhaust pipe path 51 is formed between the upper surface 23 of the main blade 5 while maintaining the same, and the injection port 29 is formed just in front of the rear end of the main blade 5, and thus the outside air discharged from the exhaust port 17 is formed. Since it is injected to the outside from the injection port 29 through the exhaust pipe passage 51, it is helpful to the propulsion of the plane (1), the position of the double upper 41 is called the propulsion position. At this time, it is preferable that the rear end of the double upper 41 end slightly ahead of the rear end of the main blade 5 so as not to interfere with the flap (not shown) operation of the rear end of the main blade 5.

On the other hand, the double upper 41 may employ a variety of fixing means to be mounted to the main wing (5) as described above, as an example, as an example of the scissor lift 43 shown in FIG. Can be mentioned. A plurality of lifts 43 are mounted between the upper surface 23 of the main blade 5 and the inner circumferential surface of the double upper 41 in a direction parallel to the fuselage 3, and like a general scissor lift, a pair of links 53 For example, one side of the upper, lower, left, and right sides is moved left and right along the upper surface 23 of the main blade 23 and the inner circumferential surface of the double upper 41 so that the upper and lower left and right sides thereof are not moved up and down, for example, as shown in FIG. It can be fixed to the left and right by the guide rail 55, it is operated by the hydraulic cylinder (57).

In addition, the double upper 41 may be divided into a plurality of portions along the longitudinal direction of the main blade 5 as shown in FIG. 1 to selectively move up and down for each divided portion. The upper 41 may be arranged at different heights. For example, all the divided double uppers 41 except for the divided double uppers A disposed on the tip side are placed in the propulsion position of FIG. When only the upper A is placed in the boosting position of FIG. 9, the main blade 5 is inclined so as to be inclined upward toward the double upper A, so that the rotation radius can be greatly reduced when the airplane 1 first takes precedence in FIG. 1.

On the other hand, as another embodiment of the present invention, the plane 101 shown in Figs. 12 to 14 is similar to the plane 1 described above, the intake port 11, the blowing means 13, the drive means 15, the exhaust port , And conduit means (19).

Here, first, the inlet 11 is formed at the bottom of the body 3, preferably at the front of the bottom center intersecting the main blade 5, as shown in Figs. 12 and 13, as shown. Although it may protrude outward from the body 3, it may be formed to penetrate the entire upper 21 of the body 3 without protruding from the body 3 to reduce resistance.

Since the blowing means 13 is also made of a conical radial fan like the blowing means described above, a detailed description thereof is omitted. 12 to 14, however, the air inlet 11 on the inner bottom surface 33 of the body 3 corresponds to the inlet 11 formed at the bottom of the body 3, as shown in Figs. It is mounted on the rear side, so that the hub 31 protrudes sharply toward the inside of the body 3 so as to deflect the incidence direction of the outside air introduced through the inlet 11 in the longitudinal direction of the left and right main blades 5. The body 3 is installed on the bottom surface 33.

Similarly, the driving means 15 is composed of an engine or a motor in the same manner as the driving means 15 described above. However, as shown in FIG. 13, the driving means 15 cannot be directly connected to the blowing means 13 facing upward for reasons of space arrangement. The rotational driving force is transmitted to the blowing means 13 through a transmission means 59 such as a belt.

Since the exhaust port is the same as the exhaust port 17 described above, a description thereof will be omitted.

Lastly, as shown in FIGS. 12 to 14, the conduit means 19 is formed in the left and right main wings 5 in the same manner as the conduit means 19 described above. It is a funnel shape in which the cross-sectional area is gradually reduced from the blade root portion of the main blade (5), which is widened to accommodate the external air, to discharge the outdoor air along the top surface of the left and right main blades (5) through the narrowed exhaust port. A guide vane 37 protrudes on the inner wall surface 35 of the body 3 facing the means 13, and blows out the outside air introduced from the inlet 11 as shown by the arrow in FIG. Branch to the left and right main blades (5).

At this time, the guide vanes 37, as shown in Figs. 12 to 14, the outside air is blown by the blowing means 13 as a plate having a V-shaped cross-section protruding sharply toward the blowing means (13). Bar to the left and right, the air flow control plate 39 is pivotally installed around the rotation shaft 38 at the lower tip of the guide vane 37, and the rotation shaft 38 is the motor 61. By rotationally driving by, etc., the air volume of the outside air branched by the guide vanes 37 can be adjusted according to the rotation angle of the airflow control plate 39.

Now, the operation of the airplane (1) having a wing booster of the present invention configured as described above is as follows.

The plane 1 is designed to form a steady stream when the frontal form is in flight. Therefore, the flow of the steady flow flows around the plane body in a uniform pattern, and the outdoor air of the uniform pattern is continuously introduced into the pipeline means 19 through the inlet port 11. The outside air introduced into the conduit means 19 is refracted by the blowing means 13 which rotates at high speed by the driving means 15 in the longitudinal direction of the main blade 5, that is, the direction substantially perpendicular to the fuselage 3. It is accelerated and compressed into the narrow part of the conduit means 19. At this time, the speed of the plane 1 and the air blowing means 13 has a relationship of a virtuous cycle, which means that the more the air flows from the engine 1, the more air flows into the inlet 11, the inlet 11 That is to say that the outdoor air introduced into the) is discharged through the exhaust port 17 to further accelerate the plane (1).

Meanwhile, the outside air accelerated by the blowing means 13 and gradually compressed from the large diameter portion of the funnel-shaped conduit means 19 and introduced into the small diameter portion of the conduit means 19 along the main blade 5 is shown in FIG. 8. Likewise, it is dispersed throughout the upper surface 23 of the main blade 5 through the relatively narrow exhaust port 17 and discharged at high speed along the surface layer.

Accordingly, the air velocity of the upper surface 23 surface layer is much faster than the main surface 5, the lower surface 24, which increases the pressure difference between the upper surface 23 and the lower surface 24, the main blade (5) Increases the lift taken on. Therefore, the airplane 1 of the present invention can shorten the take-off time much compared to the general airplane.

In addition, according to another embodiment of the present invention, as shown in FIGS. 9 and 10, a double upper 41 which is movable up and down while being aligned with the exhaust port 17 is placed on the upper surface 23 of the main blade 5. When the boosting according to the present invention is required, such as by taking off, the double upper 41 may be placed in the boosting position located at the bottom as shown in FIG. 9 to increase the lift on the main blade 5 as described above. In the constant speed state, the double upper 41 may be placed in the propulsion position shown in FIG. 10 to use the outside air discharged from the exhaust port 17 to propel the airplane 1.

In addition, according to another embodiment of the present invention, when the double upper 41 is divided in the longitudinal direction of the main blade 5, by changing the position of the double upper 41 different from each other, for example, as mentioned above Rotation radius when the plane (1) turns to the opposite side as the main wing (5) is inclined ascends toward the part where the part of the divided double uppers is placed at the boosting position by arranging only the double upper part of the short side at the boosting position. Can be made much shorter.

On the other hand, according to another embodiment of the present invention shown in Figures 12 to 14, when the airplane 101 starts taking off, the blowing means 13 is also activated to suck the outside air through the inlet port (11).

At this time, since the air inlet 11 is formed at the center of the bottom surface of the body 3, and the air blowing unit 13 is provided immediately behind the air inlet 11, the outside air sucked in the air inlet 11 is blown out. It is divided into left and right along the guide vane (37) by the blowing force of the acceleration to the pipeline means 19 inside the left and right main rotor (5), respectively, after which the lift force of the main blade (5) through the same process as described above Incidentally, since the same process is described above, detailed description thereof will be omitted.

Thus, unlike the airplane 1 described above, the airplane 101 can simultaneously blow air to the left and right sides of the main wing by one blowing means 13, but of course the blowing means 13 of the fuselage 3 It is also possible to arrange a plurality in parallel in the longitudinal direction. In this case, in particular, the plane 101 may be mounted on the tip of the guide vane 37 as shown in FIG. 14 to adjust the amount of air flowing into the left and right main wings 5, for example, FIG. When the airflow control plate 39 is rotated in the clockwise direction at 14, the amount of air flow to the left main wing 5 on the right side of the drawing is larger than the right main wing 5 on the opposite side, which is larger than the lift right side of the left main wing 5, The plane 101 can be inclined to the right side to greatly reduce the radius of rotation at the time of priority, and according to the plane 101 as described above, the plane performance can be greatly increased.

Therefore, according to the airplane provided with the wing booster of the present invention, the outside air flowing into the main wing through the intake port during flight or takeoff is compressed and diffused at high speed by the blowing means in the longitudinal direction of the main wing, the upper end of the main wing through the exhaust port Since it spreads in the longitudinal direction of the main wing along the surface layer of the plane and can be discharged at high speed, the air velocity flowing through the upper surface of the main wing can be greatly increased, thereby increasing the amount of lift applied to the main wing, and thus, especially taking off the plane. By drastically shortening, it is possible to greatly improve the passenger comfort of boarding.

In addition, when the lift does not require an increase in lift, the double upper is mounted on the upper end surface of the main wing so as to be placed in an ascending position, whereby the high speed air discharged from the exhaust port is formed at the rear of the main wing when the double upper is raised. By spraying through the nozzle, it can be used as a complement to airplane propulsion as needed.

In addition, when the double upper is divided into a plurality of positions, by changing the position of each double upper, it is possible to make the flight adjustment more quickly and smoothly than to adjust depending on the flap or the like, causing partial lift deviation in the main wing. .

In addition, by arranging the intake port and the blower means along the center line under the fuselage, not only can the outside air introduced into the fuselage through the intake port be blown by the main blades on both the left and right sides but also by the only blower means in the center. Significantly reduces the turning radius of the left and right turning flights that depended solely on the flap of the car, making it possible to fly very quickly and smoothly even during sharp turns.

Claims

Torso fuselage; And

In the plane comprising; a main blade which is laterally coupled to the middle portion of the body;

At least one air inlet through the upper constituting the plane to allow outside air to flow into the inside of the plane;

At least one blowing means surrounded by the upper of the main blade and disposed to correspond to the intake port, thereby accelerating and diffusing outside air introduced through the intake port in the longitudinal direction of the main blade;

Driving means for rotating the blowing means;

An exhaust port opened rearward along an upper end surface of the main blade to discharge external air accelerated by the blower to flow along the upper surface surface layer of the main blade; And

And a conduit means for connecting the intake port and the exhaust port to compress and diffuse the outside air accelerated by the blowing means disposed adjacent to the intake port toward the exhaust port. airplane.
According to claim 1,

The air inlet is provided with a wing booster, characterized in that the plurality of openings are spaced apart from each other on the front of the upper along the tip of the main wing.
The method of claim 2,

The blowing means is a plane having a wing booster, characterized in that the hub is a conical radial fan protruding sharply toward the body opposite side to deflect the direction of incidence of the outside air introduced through the intake port in the longitudinal direction of the main wing.
The method of claim 3, wherein

The blowing means is arranged in a position adjacent to the intake port in a one-to-one correspondence with the plurality of intake ports opened in a state spaced apart from the front of the upper along the front end of the main wing, so that the synchronous rotation by the drive means An airplane equipped with a wing booster, characterized in that there is.
According to claim 1,

The conduit means is in the form of a funnel in which the cross-sectional area is gradually reduced from the blade root portion of the main blade widened to accommodate the outside air blown from the blowing means to the exhaust port narrowed to discharge the outside air along the top surface surface of the main blade An airplane equipped with a wing booster.
According to claim 1,

And the air inlet is opened through the upper at the bottom of the fuselage.
The method of claim 6,

The air blowing means is configured to refract the incidence direction of the outside air introduced through the intake port from the bottom of the fuselage in the longitudinal direction of the left and right main wings, so that the hub protrudes sharply into the fuselage, so that the intake port on the inner bottom surface of the fuselage is inclined. An airplane equipped with a wing booster, characterized by a rear mounted conical radial fan.
The method of claim 7, wherein

The conduit means is in the form of a funnel in which the cross-sectional area is gradually reduced from the blade root portion of the main blade widened to accommodate the outside air blown from the blower means to the exhaust port narrowed to discharge the outside air along the top surface surface of the main blade. Wing booster, characterized in that the guide vane is projected on the inner wall surface of the fuselage facing the blowing means to divert the outside air flowing in from the main wing of the left and right around the blowing means. airplane.
The method of claim 8,

The guide vane has a central portion protruding sharply toward the blowing means to branch the outside air blown by the blowing means from side to side, and the air volume control plate for adjusting the air volume of the branched outside air toward the blowing means. An airplane provided with a wing booster, characterized in that the pivot is installed by the pivot shaft mounted on the tip.
The method according to any one of claims 1 to 9,

Mounted to the upper end surface of the main wing so as to be movable upward and downward to form a profile that maintains the airfoil of the main wing when aligned with the upper end of the upper end of the exhaust port by being raised from the upper end surface, and at the same time as the injection port Forming a plane having a wing booster, characterized in that it further comprises a double upper shell which is configured to spray the outside air discharged from the exhaust port through the injection port.
The method of claim 10,

The double upper plane is equipped with a wing booster, characterized in that the movable up and down by a plurality of scissor lifts mounted between the upper surface of the main wing.
The method of claim 11, wherein

The double upper plane is divided into a plurality in the longitudinal direction of the main wing is provided with a wing booster, characterized in that the arrangement height can be different from each other by selectively moving up and down.