WO2019212066A1

WO2019212066A1 - Third-generation aircraft, ship, train and automobile having angle-variable lift force adjusting wings

Info

Publication number: WO2019212066A1
Application number: PCT/KR2018/005007
Authority: WO
Inventors: 최동규
Original assignee: Choi Dong Kuoo
Priority date: 2018-04-30
Filing date: 2018-04-30
Publication date: 2019-11-07
Also published as: JP2021530404A; JP7112141B2

Abstract

The present invention provides third-generation aircraft, ship, train and automobile having angle-variable lift force adjusting wings. The present invention comprises: a fuselage; angle-variable lift force adjusting compound wings which are disposed on both lateral parts of the upper part of the fuselage and of which the angle is adjusted about a wing drive shaft portion so as to provide the fuselage with a lift force or a reversed lift force opposite from the lift force; and a driving unit which is for driving the angle-variable lift force adjusting compound wings so as to adjust same about the wing drive shaft portion in an angle for providing a lift force or an angle for providing a reversed lift force. The present invention enables the adjustment and control of the anti-centrifugal force by means of erecting the wings vertically, and thus enables safe operation even in case of sudden weather changes or unexpected situations and enables stable takeoff and landing in a short taxiing distance.

Description

2019/212066 1 »（： 1 ^ 1 {2018/005007

One

【Specification】

[Name of invention]

Third-generation aircraft, ships, trains, and cars with variable lift vanes

Technical Field

The present invention relates to a technique for mounting a wing of a variable lift type on a vehicle, such as an aircraft, a ship, a train, a car, and more specifically, lift, anti-lift on any one of the aircraft, ship, train, car And, by attaching a variable lift control wing that is selectively applied by the antigenic force, it can compensate for the weakness that cannot cope with variables such as the limitations of the aircraft, ships, trains, and automobiles and the functional limitations and bad weather. A third generation aircraft, ships, trains and automobiles equipped with angular lift control wings.

Background Art

In a conventional runway type aircraft, the main wing 200 is fixed to the fuselage 100 as shown in FIG. 3A, and taken off by a horizontal rudder 201 at the rear of the main wing 200. And to control landing or altitude.

However, the aircraft to which the technology of the present invention is applied is capable of simultaneously performing the function of the horizontal rudder through a fused wing that combines the functions of the wing and the horizontal rudder into one. Therefore, if the present invention is specified, the variable lift type wing = wing + The horizontal tar is a formula. Thus, the first application of the principle of the kite to the wing of the aircraft, so that the rise theory of the kite can be applied to each wing. 2019/212066 1 »（： 1 ^ 1 {2018/005007

In other words, the conventional aircraft has a main wing 200 fixed to the fuselage 100, and take off at a takeoff and landing angle (1 to 1) defined on a runway of a predetermined length as shown in FIGS. 2 and 5 (a). It is also possible to carry out frequent landings and landings, and if there is a problem with the direction of the wind, the fog, clouds, or other indication devices such as airport control stations at night, or if the aircraft breaks down on its own, Caused. In addition, the conventional aircraft 100 occupies a large area of the airport due to the long main wing 200 unnecessary, there was a lot of inconvenience when wearing in the hangar for reasons such as repair or storage.

In addition, the conventional aircraft bears more than 90% of the lift on the main wing 200, so that lift is concentrated on a limited portion of the main wing 200 and the fuselage 100, causing lift imbalance, and the fuselage stability to the main wing. By relying on more than 30% of the vandals, a serious situation such as a fall can occur.

In addition, the conventional aircraft as another problem, since the aircraft body tilts at an oblique angle (Mo 1) at take-off, it may have a great impact on the cargo stability in the case of an uncomfortable posture and a cargo plane that the passenger feels.

In addition, the conventional aircraft had to bear almost all the lift to the main wing 200, so there was a limit to the length of the fuselage, which is directly connected to the capacity of passengers or cargo, because the altitude control 201 is in charge Because of the impossibility of soaring or descending and decelerating, the runway had to be made long for takeoff and landing.

On the other hand, vehicles such as cars and trains are not equipped with variable lift type wings, so if the load increases according to passengers and cargo, In addition to the excessive consumption of fuel, the increased load is transmitted to the wheels of cars or trains, and has the disadvantage of being damaged. .

In addition, a vehicle such as a vessel is applied to the ballast tank (Bal last Tank) to enable a stable operation, but this also does not have a variable lift type wing, the number of ballast filled in the ballast tank As the overall load increases due to (Bal last Water), fuel consumption increases, and in particular, environmental pollution caused by the discharge of ballast water is emerging.

Detailed Description of the Invention

[Technical problem]

Therefore, the present invention is to improve the conventional problems as described above, by mounting the wing of the variable lift type on each aircraft, ship, train, car as a means of transportation, lift or half by adjusting the angle of the wing It is to provide lift and provide stable mobility for passengers using vehicles such as aircraft, ships, trains and automobiles, and to ensure that the loaded cargo is also stable and manual. Its purpose is to provide third-generation aircraft, ships, trains and automobiles equipped with variable lift lifts that can significantly reduce fuel consumption.

In other words, when the present invention is applied to the aircraft fuselage, it is possible to make the horizontal landing and landing more safe for passengers and cargo.

In another object of the present invention, antigens in aircraft, ships, trains and automobiles 3rd generation aircraft, ships, trains and vehicles equipped with angular lift-controlled wings to prevent thrust during aircraft, ships and trains, and the vehicle's curve movement by constructing the wing providing the force. Is to provide.

Another object of the present invention is to provide a uniform lifting distribution along the longitudinal direction of the entire body and thereby to eliminate the lifting bias concentration concentrated on the wing, to prevent serious safety accidents even if some of the wings are damaged. will be.

Another object of the present invention, by changing the position and size of the main wing that was responsible for almost all lift, by distributing it so that the length of the fuselage directly connected to the capacity of passengers or cargo can be easily extended as needed. I will.

Another object of the present invention, when applied to a vehicle such as a car or train, through the fused wing of the variable lift control system, even if the load increases according to the passengers and cargo, due to the increased load To solve the problem that the wheels of the train is easily damaged, and to provide a vehicle with improved stability that effectively prevents the jungle even in bad driving conditions such as rain roads, ice roads or curves.

Another object of the present invention is to replace a ballast tank when applied to a ship, and to carry a passenger or cargo by a load that is generally increased by the ballast water filled in a conventional ballast tank. It is intended to provide additional transport, and in particular to solve the environmental pollution problem caused by the discharge of ballast water.

In other words, as fish swim in the water, birds and butterflies swim in the atmosphere. Therefore, even man-made land vehicles, aircraft, or even missiles and rockets are not free from air flow and resistance if they are motility. So seen The inventors have tried to make the best effect by finding the way to use if not free and inducing the resistance of air and water as much as possible in the desired direction. As a result, the present invention has been reached.

Technical Solution

A third generation aircraft equipped with a wing of the variable lift type of the present invention for achieving the above object, the fuselage; The left and right pairs are arranged on both sides or the upper portion of the fuselage at least two or more consecutively, and the angle is adjusted based on the wing drive shaft located at the center of the wing to provide the lift or anti-lift force opposite to the lift force. It is possible to install, the variance lift type fusion wing to perform the function of the wing and the horizontal stroke at the same time; And a driving unit for tilting the variable lift type control fusion blade at an angle providing lifting or anti-lifting force around the wing driving shaft. The variable lift type fusion wing includes a wing body that generates lift by having a general aircraft wing shape with a streamlined cross section, and a windscreen in front and rear of the wing body ( A wind dividor and a wind pressor are installed to extend, respectively, wherein the wind dividor and the wind pressor are positioned on a line passing through the wing driving shaft and at the same time. It is installed in the form of a flat plate placed on a straight line connecting the front and rear end, characterized in that the streamlined wing body is configured to provide increased lift during high angle takeoff and landing while maintaining a minimum cross section.

In the aircraft of the present invention, the angular lift type fusion wing which is arranged in a pair of left and right, at least two or more consecutively, the rear from the front to both sides of the fuselage 2019/212066 1 »（： 1 ^ 1 {2018/005007

It can be installed evenly up to 6 to distribute the lift evenly among the fuselage, so that the fuselage can take off and land horizontally.

In the aircraft of the present invention, the drive unit may be configured to be connected to the wing drive shaft portion and the connecting member of the variable lift type fusion fusion blade to adjust the angle of the variable lift type fusion fusion blade disposed at the same time at the same angle. have.

In the aircraft of the present invention, each of the drive unit 1: 1 to each of the wing drive shaft portion of the variable lift type fusion fusion blade to individually adjust the front, rear, left and right angles of the variable lift type fusion wing is arranged in plurality. It can be configured as

In the aircraft of the present invention, the drive unit may be driven to adjust the angle of the variable lift type fusion wing according to the wind direction and wind speed information detected by the wind direction detection unit.

In the aircraft of the present invention, the variable lift control type fusion blades disposed on both sides of the fuselage may be arranged on the same horizontal line.

In the aircraft of the present invention, the variable lift control type fusion vanes disposed in plural on both sides of the fuselage may be disposed in a stepped manner.

In the aircraft of the present invention, the angular lift type control fusion wings disposed in a plurality on both sides of the fuselage can be arranged in a zigzag form that crosses each other up and down.

In the aircraft of the present invention, the variable lift control type fusion wing disposed in a plurality of both sides of the fuselage is configured to gradually expand the width and length of the wing in the order arranged from the front side to the rear side, From the front wing Minimize interference caused by vortices or waves.

In the aircraft of the present invention, between the angular lift type fusion fusion blades disposed on both sides of the fuselage is further arranged to form a fixed wing that is not angle adjustment to prevent interference flow, The variable lift control method is to ensure the flight stability by performing the rudder role through the angle control of the fusion wing and to maintain the basic lift in the event of the abnormal lift type fusion wing.

In the aircraft of the present invention, the variable lift type fusion wing disposed in a plurality of sides of the fuselage, outside the fixed wing is attached to the fixed form on the fuselage outer wall, the angle wing is adjustable angle of rotation It can be configured to form a single unit compound wing, the unit compound wing is a vertical structure compared to the fuselage installed at right angles to the fuselage, or a rear push-type structure compared to the fuselage installed at an inclined angle to the fuselage Is optionally applied.

In the aircraft of the present invention, the angular lift type control type fusion wing disposed in a plurality on both sides of the fuselage, a unit composite wing repeatedly installed fixed blade portion and angular wing portion along the longitudinal direction on one independent wing Can be applied.

In the aircraft of the present invention, the unit compound wing is an outer type composite wing installed in the fixed wing portion fixed to the outer wall fixed to the fuselage and the outer wing portion is adjustable in the rotation angle (outer type), or the angle wing portion Intermediate type compound blades arranged to be located between two fixed blade parts spaced apart from each other, or inner type compound blades installed so that the angled wing parts are located inside the fixed wing parts. 2019/212066 1 »（： 1 ^ 1 {2018/005007

Any one of eight may be selectively applied.

In the aircraft of the present invention, the variable lift type fusion wing disposed in both sides of the fuselage, can be applied to the structure of the expansion return type variable slide composite wing in which one independent wing is extended in the longitudinal direction. In this case, the variable slide type composite wing is a length in which the inner blade of the wide width is fixed and the narrow outer wing accommodated therein is driven in a piston manner with a pneumatic or hydraulic cylinder to expand or contract from the tip of the inner blade. It is a variable fusion wing, or a narrow inner blade that is fixed to act as an axis, and a wide outer wing that is installed so as to be wrapped around the outside is driven and expanded by a piston method with a pneumatic or hydraulic cylinder. Either of the reduced length variable fusion wings is selectively Can be used.

In the aircraft of the present invention, the angle for the lifting of the variable lift control type fusion wing is adjustable in the range of 43 ^° to 87 ^{° in} the upward direction with respect to the horizontal line, minimizing the running distance In order to achieve this, it is more preferable to adjust the ^{temperature in} the range of 85 ^° to 87 ^° .

In the aircraft of the present invention, the angle for providing a semi-lift force of the variable lift type fusion wing can be adjusted within the range of 13 ^° to 15 ^{° in} the downward direction based on the horizontal line.

In the aircraft of the present invention, the rear side of the aircraft can be configured with one or more engine parts and injection holes, at least one of the plurality of engines is installed to be located in the center of the fuselage rear. 2019/212066 1 »（： 1 ^ 1 {2018/005007

9 In the aircraft of the present invention, the engine unit has a cone-shaped engine injection hole having a rotation angle of 360 ^° up, down, left and right.

When the present invention for achieving the above objects is applied to a train, a third generation train equipped with a wing of the variable lift type, the fuselage; At least two of the left and right pairs are arranged continuously on both sides of the fuselage or on the outer side of the fuselage, providing lift to the fuselage or anti-lift force opposite to the lift force, and the angle is adjusted around the wing drive shaft. Variable lift control fusion blades that provide fuselage stability through lift and always maintain constant gap between fuselage and rail through anti-lift; Centrifugal force control blades for providing the antigenic core force on the outer side or the outer side of the body; And a driving part configured to drive the variable lift control type fusion blade and the centrifugal force control blade to be adjusted at an angle for providing lift or an angle for providing a semi-lift force about the wing drive shaft. Characterized in that it comprises a.

In the train of the present invention, the angular lift control type fusion wing which is arranged in a pair of left and right and at least two are consecutively installed, evenly installed from the front to the rear of the fuselage to distribute the lift evenly between all the fuselage. do.

In the train of the present invention, the drive unit may be configured to be connected to the wing drive shaft portion and the connecting portion of the variable lift type fusion fusion blade to adjust the angle of the variable lift type fusion fusion blade disposed in a plurality.

In the train of the present invention, the drive unit may be configured to be 1: 1 each of the wing drive shaft portion of the variable lift type fusion fusion blade to individually adjust the angle of the variable lift type fusion fusion blade disposed in a plurality. have. 2019/212066 1 »（： 1 ^ 1 {2018/005007

In the train of the present invention, the driving unit is to drive to adjust the angle of the variable lift type fusion wing according to the wind direction and wind speed and wind speed information detected by the wind direction detection unit.

In the train of the present invention, the variable lift type fusion wing disposed in a plurality on both sides or the outer side of the fuselage may be arranged in the same horizontal line. In the train of the present invention, the variable lift type fusion wing disposed in plurality on both sides or the outer side of the fuselage may be arranged in a stepped manner.

In the train of the present invention, the variegated lift control type fusion wing disposed in a plurality on both sides or the outer side of the fuselage may be arranged in a zigzag shape to cross up and down.

In the train of the present invention, the centrifugal force control blade can be configured perpendicular to the variable lift type fusion wing.

When the present invention is applied to a motor vehicle for achieving the above objects, a fuselage; It is disposed on the front and rear sides of the fuselage, and provides the lifting force or the anti-lift force opposite to the lifting force, and the angle is adjusted around the wing drive shaft, providing the fuselage stability through lifting force, Variance lift control fusion wing that keeps the distance between the fuselage and the road surface at all times; Centrifugal force control blades for providing the antigenic core force on the outer upper side or the outer side of the body; And a drive unit for driving the variable lift control type fusion wing and the centrifugal force control vane to be adjusted at an angle for providing lift or an angle for providing a semi-lifting force to the wing drive shaft. It characterized by including the. 2019/212066 1 »（： 1 ^ 1 {2018/005007

11 In the vehicle of the present invention, the driving unit is to drive to adjust the angle of the variable lift type fusion wing according to the wind direction and wind speed information detected by the wind direction detection unit.

In the automobile of the present invention, the centrifugal force control vane may be configured perpendicular to the variable lift type fusion wing.

When the present invention is applied to a ship for achieving the above objects, a fuselage; The left and right pairs of left and right pairs are arranged consecutively on the outer bottom of the fuselage of the fuselage, and provide the buoyancy or anti-buoyancy opposite to the buoyancy and provide the ballast tank 犯 12 此). It is to replace the variable lift type fusion wing that is angle-controlled around the wing drive shaft; And a driving unit configured to adjust the variable lift control type fusion wing to an angle providing buoyancy or an angle providing anti-buoyancy based on the wing drive shaft. It will be configured to include.

In the ship of the present invention, the angular lift control type fusion wing that is arranged at the left and right pairs at the bottom of the outer side of the fuselage at least two consecutively, is installed evenly from the front to the rear of the fuselage to lift the lift body It is characterized in that it is evenly distributed among the bulbs.

In the ship of the present invention, the drive unit may be configured to be connected to the wing drive shaft portion and the connecting member of the variable lift type fusion fusion blade to adjust the angle of the variable lift type fusion fusion blade disposed in a plurality.

In the ship of the present invention, the drive unit is a variable lift type control fusion so as to individually adjust the angle of the variable lift type fusion wing is arranged in plurality 2019/212066 1 »（： 1 ^ 1 {2018/005007

12 can be composed of 1: 1 in the blade drive shaft part of the blade.

In the ship of the present invention, the driving unit is characterized in that for driving to adjust the angle of the variable lift type fusion wing according to the water flow information detected by the water flow detection unit.

In the ship of the present invention, the variable lift type fusion fusion wing disposed in plurality on the outer bottom or the upper side or roof of the fuselage may be arranged in the same horizontal line.

In the ship of the present invention, the variable lift type fusion wing disposed in plurality on the outer bottom or the upper side or the roof of the fuselage can be arranged stepwise.

In the ship of the present invention, the angular lift type fusion fusion wings arranged in plurality on the outer bottom of the fuselage or on the upper side or the roof of the fuselage may be arranged in a zigzag shape crossing each other up and down.

In the ship of the present invention, if the fuselage is a large low speed vessel, the variable lift type fusion wing can be arranged in plurality on the outer bottom of the vessel.

In the ship of the present invention, if the fuselage is a small high-speed vessel, the variable lift type fusion wing can be disposed in plurality on both sides of the outer side of the vessel or the roof of the vessel.

【Effects of the Invention】

As such, the present invention is equipped with a wing of the variable lift type to each of the transport means such as aircraft, ships, trains, and cars, as described above 2019/212066 1 »（1 ^ 1 {2018/005007

13 Adjusting to provide lift or anti-lift and antigenic force to vehicles, ships, trains and vehicles, to ensure the stable movement of vehicles, ships, trains and vehicles, and passengers. However, even if the load increases due to cargo, it is possible to achieve a stable movement as well as to save fuel due to the movement.

In addition, the present invention, when applying a variable lift type wing to a vehicle such as an aircraft, while forming a short fuselage body to reduce the runway while reducing the cost of the runway, while at the airport waiting area In addition, it can be expected to increase the number of passengers and cargo by increasing the width of the fuselage and designing the fuselage.

In addition, the present invention is to enable the rapid rise and fall and rapid deceleration of the aircraft when applying the variable lift type wing to a vehicle, such as an aircraft.

In addition, the present invention can provide an effect of significantly shortening the take-off and landing distance of the aircraft, while generating a uniform lift in all sections of the fuselage, when the wing of the variable lift type is applied to a vehicle such as an aircraft. will be.

In addition, the present invention is applied to the multi-stage variable lift type wing in a vehicle, such as an aircraft, even if any of the wings are broken, so that only the broken wing can be replaced, to prevent a sudden fall accident You can expect the effect. In addition, the present invention can be expected to have an effect of minimizing the atmospheric area at the airport when applying the variable lift type wing to a vehicle, such as an aircraft, to improve the inconvenience caused when the hangar. In addition, the present invention when the wing of the variable lift type is applied to a vehicle such as a train or a vehicle, even if the load increases due to the increase in passengers and cargo, as well as stable running is possible, as well as the wheel from the gravity action due to the increased load This can be expected to prevent the problem of (especially trains) from being damaged.

In addition, the present invention, when applying the variable lift (buoyancy) and anti-lift (half buoyancy) control method to a vehicle, such as a ship, can be expected to increase the load of cargo and guide the stable operation of the ship will be.

In other words, in the case of providing anti-buoyancy to the ship's body through the variable lift type fusion wing, the ship's body is pulled down to provide stability to the fuselage. Consideration is given to cruising at the best speed.

In addition, if the necessary conditions are caused by the rapidly changing weather or algae during cruising, the wing angle control of the variable lift control fusion blade increases to increase the anti-buoyancy (receiving force), thereby rapidly acting as a substitute for the ballast tank. When the function of the ballast tank is replaced by the variable lift type fusion vane, the overall load is reduced compared to the conventional vessel filled with the ball last water, and the fuel consumption is significantly reduced. In particular, it is possible to solve the environmental pollution problem caused by the discharge of ballast water.

Existing ballast tank type vessels may cause the body to shake or temporarily tilt in the front and rear, especially left and right in the wind, waves or storms, and in the worst case, even if you feel the risk of sinking, the variant type of the present invention 2019/212066 1 »（： 1 ^ 1 {2018/005007

15 In the case of a ship with a lift control fusion wing, after detecting the shaking of the fuselage, it controls the angle of each wing to control the flight without severe fluctuations or waves as if the fuselage is stuck in the water. will be.

More technically, the variable lift type fusion vanes applied to large vessels are subject to great pressure and resistance due to the specificity of air and other water materials, while minimizing the cross section of the variable lift type fusion vanes. Durable materials must be used and structurally stronger bonds are required.

In addition, the present invention by applying the wing of the variable lift type to exert the antigenic force on a vehicle such as a train or a car, while preventing the occurrence of jungle on the rain or ice or curve road of the train or car The driving can be expected to be stable in a constant speed driving state without deceleration.

[Brief Description of Drawings]

1 is a view showing the overall wing characteristics and concept of the aircraft to which the wing of the variable lift type of the present invention is applied.

2 is a cross-sectional view of a conventional fixed main wing (A) and a cross section of a variable lift type wing (B) which is the core of the present invention. With ratio （101 ·）

It is a drawing showing the configuration that the wing drive shaft portion is installed in the center of the wing of the variable lift type.

Figure 3 shows the overall shape of the aircraft to which the main wing is applied to the conventional fixed type and the aircraft to which the variable lift type wing of the present invention is applied and the function and role of the wing 2019/212066 1 ^» （： 1 ^ 1 {2018/005007

In comparison, (a) and (city) show the top view of the two aircraft, (b) and (b) show cross sections of the wing, (c) (d) and (e). 00））（£） is the wing function and role of only one wing. The aircraft with fixed main wing shows the side cross section, and the aircraft with variable lift type wing shows the front cross section. to be.

4 is a view showing the core principle of the present invention aircraft and the variable lift type variable wing applied to the principle of soft and water ski.

5 is a view showing a state in which the conventional aircraft equipped with a fixed main wing and the aircraft of the present invention equipped with a wing of the variable lift type take off, (A) is a fixed main wing is mounted so that the takeoff angle is The conventional aircraft is small and the fuselage rises at an oblique angle, (b) is a plane drawing of the present invention that the takeoff angle is large and the horizontal rise by mounting a variable lift type wing.

(A) of Fig. 6 shows the limit angle for the wing of the variable lift type, the limit angle is defined for the safety of the fuselage, and may cause serious danger when exceeded, the upper limit based on the horizontal line Below each is a view showing the minimum limit angle, (B) is a view showing the landing form for the aircraft of the present invention equipped with a variable lift type wing, (C) is a fixed main wing A diagram showing a landing form of a conventional aircraft.

(A) (b) (c) of FIG. 7 is a view showing a method of arranging a variable lift type wing on the aircraft of the present invention, (a) is a horizontal arrangement, (b) is a staircase arrangement, (C) is a diagram showing a state where a zigzag array method is applied. 2019/212066 1 »（： 1 ^ 1 {2018/005007

FIG. 8 illustrates a side and a plane of an aircraft to which a wing of a variable lift type control method shown in FIG. 7 is applied, and shows an enlarged area before and after the wing of a variable lift control method.

FIG. 9 is a plane view of an aircraft to which a wing of a variable lift type control method showing a horizontal arrangement in FIG. 7 is applied, and the wing of the variable lift control method is configured to have a wider area from left to right. Drawing.

FIG. 10 is a diagram showing a wing arrangement in which a fixed wing and a wing of a variable lift type are fused.

(A) and (b) of FIG. 11 are plan views showing a structure in which a fixed blade portion and a variable wing portion are installed in a single independent wing, and on the outside of the fixed wing portion fixedly attached to the outer wall of the fuselage. The additional rotation angle is adjustable so that it can be configured to form a single compound wing. (A) of FIG. 11 illustrates a vertical structure compared to the body body in which the compound wing is installed at right angles to the body. (B) shows the rear-limb type structure compared to the fuselage in which the compound blade is installed at a certain inclination angle on the fuselage.

(A) and (B) of FIG. 12 are plan views showing the functional positions of the fixed blade opening and the flap wing, which are complexly installed on one independent wing, and (A) of FIG. 12 is fixed to the outer wall of the fuselage. It shows a state in which the angular blade portion is installed to adjust the rotation angle outside the fixed blade portion attached to the, and (b) of Figure 12 is arranged so as to be positioned between the fixed blade portion spaced apart from each other, and 12 (C) shows a state in which they are installed so as to be positioned inside the angled wing part temporarily fixed blade part. 2019/212066 1 »（： 1 ^ 1 {2018/005007

18 is a view for explaining a structure in which one independent wing is extended in the longitudinal direction.

14 is a conceptual view of a fused wing of variable lift type.

15 is a view showing the basic mechanism of the wing and the anti-centrifugal wing of the lift and anti-lift (or traction) control system.

16 is a view showing the basic application state of the lift and anti-lift (or traction) control method wing and centrifugal force wing.

Fig. 17 is a side view and a bottom view showing a state in which a wing of the lift (buoyancy) and anti-lift (half buoyancy) adjustment method is applied to a large ship.

18 is a side view and a plan view showing a state in which a wing of the lift (buoyancy) and anti-lift (anti-buoyancy) adjustment method is applied to a small ship.

19 is a front view and a side view showing a state in which the lift and anti-lift control method of the wing and the antigen center force wing is applied to the train. -

[Best form for implementation of the invention]

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.

According to an embodiment of the present invention, the variable lift control method applied to the fuselage 10 of an aircraft, a ship, a train, and a vehicle includes a variable lift control type fusion wing 20 and / or a fixed wing, and a drive unit 30 And wind direction detection unit 40, and further include a centrifugal force control blade 50 and a horizontal rudder (not shown).

At this time, as an embodiment of the present invention can be applied to the wing 20 of the variable lift type. 2019/212066 1 »（： 1 ^ 1 {2018/005007

The principle of 19 is to use the principle of flying kite as in (A) of Fig. 4, which is more specifically, the oblique downward direction (gravity direction) of the kite body and the resistance force (air flow) that makes the wind resistance It was conceived from the strings tied up to flow into.

Also, as shown in (b) of FIG. 4, it was conceived from the buoyancy principle of water skiing, and it was conceived as the buoyancy by flowing the resistance of water downward as the ski moves forward.

On the other hand, in addition to the principle described above may be applied to the principle applied to the screw of the ship, the windmill and the fan blade, etc., the common point of these is to induce water and wind resistance in the desired direction.

That is, the variable lift control type fusion wing 20 according to the embodiment of the present invention is designed to induce the water and wind resistance in a desired direction from the material of air and water described above. By adjusting the angle of the half wing (20), it is possible to adjust the lift (or buoyancy) in response to the situation or variables caused by the movement of aircraft, ships, trains and ships.

(Formula of variable lift type fusion blade applied to aircraft)

* Wing + horizontal stroke-> variable lift type wing = kite (each wing)

The pilot who controls the aircraft feels more tension at landing than at takeoff. The variable lift wing type aircraft of the present invention does not have a fixed landing angle. Can be reduced.

Looking at this as a more specific embodiment, the variable lift type fusion blade Dog 20 is disposed on both sides of the fuselage 10 of the aircraft, ships and trains, and the vehicle, the wing drive shaft portion (20a) to provide a lift or anti-lift force opposite to the fuselage (10) The angle is adjusted to form a configuration. In this case, the variable lift type fusion wing 20 is adjusted to have a limit angle for providing lift and a limit angle for providing a half lift, as shown in Figure 6 (a) attached to the The maximum limit angle for lifting force of the angular lift control type fusion wing 20 is to be adjusted in the range of 43 ^° to 87 ° in the upward direction with respect to the horizontal line (H), the variable lift type fusion control method The minimum limit angle for providing the anti-lift force of the wing 20 is configured to be adjusted within the range of 13 ^° to 15 ^{° in} the downward direction with respect to the horizontal line.

Here, the maximum limit angle of the lift and the half lift is not limited to the numerical range as described above, it is possible to reset the limit angle through research and experiment.

On the other hand, the front and rear of the angular lift control type fusion wing 20, as illustrated in Figures 1 and 2 (b) in detail, by having a streamlined structure protruding upward to generate the lift The wind dividor and wind pressor, which are installed at the front and rear of the wing body, respectively, are extended to have a plate-like structure.

That is, when the wind separating plate 21 and the wind pressing plate 22 applies the variable lift type fusion wing 20 to the aircraft fuselage 10, when the aircraft takes off and lands, To induce air flow in consideration of the pressure, 2019/212066 1 »（： 1 ^ 1 {2018/005007

21 Accordingly, the windscreen 21 and the wind pressor plate 22 should be made of a rigid material so as to be as thin as possible but not broken or separated from the variable lift type fusion wing 20, and the rigidity described herein. The material of is to describe the carbon fiber as a known material, but is not necessarily limited to these.

On the other hand, the angular lift type fusion wing 20 is composed of at least two or more pairs arranged on both sides of the aircraft fuselage 10 on both sides, preferably arranged in multiple stages as a plurality, which is attached to Figure 7 Arrange horizontally on the same horizontal line as in (A) of, or staircase as shown in (b) of FIG. 7, or cross each other up and down as shown in (c) of FIG. It can be arranged in a zigzag arrangement.

At this time, the variable lift type fusion wing 20 arranged in a horizontal type is disposed on the rear end side, while the interference of air (for example, vortex or wave) affects the rear wing side due to the arrangement interval. It is not desirable because there is a problem of reducing the lift provided by the angular lift control method fusion wing. Accordingly, it is possible to arrange the variable lift type fusion vanes 20 in a stair step type relatively free from interference flow or to arrange the variable lift type fusion vanes 20 in a zigzag form.

And, it is most ideal to arrange the variable lift type fusion blades 20 in a stepped manner, which is a lift of the variable lift type fusion blades 20 arranged at the front and rear ends at least 5, respectively. ^' 7%, the maximum lifting force of the variegated lift control fusion wings (20) can be provided the largest, with a difference of up to 10% 2019/212066 1 »（： 1 ^ 1 {2018/005007

22 because, according to the variable lift type fusion wing 20 is arranged in such a step can be easily applied to a large vehicle (large passenger plane, large cargo plane).

On the other hand, in order to compensate for being affected from interference flow when the variable lift type fusion wing 20 is disposed in a horizontal type, the variable lift type fusion method is arranged horizontally as shown in FIG. 10. By constructing a mixed type in which fixed blades (not shown) which are not rotated between the blades 20 are configured, the influence of the interference flow can be eliminated.

That is, Figure 10 is a diagram showing the arrangement of the fusion of the fixed wing and the wing of the variable lift control method, which can be applied to both a horizontal arrangement and a stepped arrangement, as well as a zigzag arrangement structure, Its advantages are that from the standpoint of the angular type, due to the fixed wing of the variable lift type fusion wing (20) to prevent the serious situation such as falling, and more flexible from the standpoint of the fixed wing It is to enable effective flight, and most importantly, to reduce the effects of air interference (wind), a disadvantage of multi-wing aircraft. The reason is that the gap between the two wings is widened due to the fixed wing between the angular lift type fusion wing 20, so that it is less affected by the interference (wind), The wings are continuous and can be an obstacle in terms of the effect of lift. This is especially true for all aircraft with multi-winged wings, but the more wings available, the better. However, they should not be designed too closely, as in the accompanying Figure 3, and in fact there should be considerable distance. 2019/212066 1 »（： 1 ^ 1 {2018/005007

23 In other words, non-small interference effective distance must be maintained, and the effective distance varies depending on the type of multi-wing aircraft (horizontal type, stair type, zigzag type, fusion type), but if the distance between wings is short, If the area is narrow and the distance between the wings is long, the area of the wing should be made large, which means that the larger the wings, the smaller the size, and the smaller the wings, the larger the wings. This is probably because it is a law of physics and reason before it is a formula.

In carrying out the present invention, the number of installation of the variable lift type fusion wing 20 is more effective to be composed of a plurality of smaller wings than a few large wings. This is because many small wings have less load per wing, less noise generated by the wing, softer control, operation (variation), and less interference. Therefore, even if some wings are broken in an accident, it is fatal to fuselage safety. It does not cause any effect.

Many of these small wings are, above all, smooth in flight and agile in operation, and furthermore, the wing area is small in the event of unexpected gusts or extreme weather, thus avoiding accidents or dangers when flying or waiting at the airport. Therefore, it is advantageous in every way to install many small wings (10 16) rather than a few large wings (4 6).

Here, when the multi-stage variable lift type fusion wing 20 and / or fixed blades are horizontally, stepped and zigzag arranged in multiple stages, it is inevitable that the lift is reduced at the rear side rather than the front side. Accordingly, in the embodiment of the present invention, as shown in Figs. 2019/212066 1 »（： 1 ^ 1 {2018/005007

It can also be configured to extend the width of the wings 1 <square 2 <3 <4 (or area). In other words, by applying the variable lift type fusion wing 20 that increased the width (or area) toward the rear side from the front side, it is possible to compensate for the lift lost in the rear side.

In more detail, the horizontal array structure does not complement the stepped array structure, that is, it is not possible to apply the variable lift type fusion wing 20 of the same size or the same area, for the reason This is because, in the case of multi-wing aircraft, unlike the single-wing type, the interference of air (vortex or wave) caused by the front wing affects the rear wing. This causes the lift to decrease toward the rear. In the case of the step type, which is relatively free in the interference flow, the lift difference between the front wing and the end wing is expected to be at least 5-7% and up to 10%. This phenomenon is most severe in a horizontal array.

In order to compensate for this, a method of increasing the area of the wing at a predetermined ratio toward the rear side should be used, one of which is to enlarge the area before and after the wing as shown in FIG. 8, and the other is as shown in FIG. Likewise, it is to widen the area from side to side, it is also possible to apply a mixed way to balance the front and rear and left and right areas of the wing.

On the other hand, as an embodiment of the present invention, the variable lift type fusion wing 20 disposed on both sides of the body 10 is configured to adjust the angle by the drive unit 30, the drive unit 30 is Deceleration motor for driving forward and reverse rotation to adjust the variable lift type fusion wing 20 to the angle providing the lift force or the angle providing the anti-lift force about the wing drive shaft portion (2) can be used generally Hydraulic or pneumatic 2019/212066 1 »（： 1 ^ 1 {2018/005007

It goes without saying that the control mechanism of 25 can be used selectively.

At this time, the drive unit 30 and the blade opening coaxial part (2) of the variable lift type fusion fusion blade 20 to simultaneously adjust the angle of the variable lift type fusion wing (20) arranged in plurality It is configured to be connected to a connecting body (not shown), but the wing drive shaft portion of the variable lift type fusion fusion wing 20 to individually adjust the angle of the variable lift type fusion wing (20) arranged in plurality ( It can be composed of 1: 1 in 2 each.

At this time, the wing drive shaft portion (2) is the angle of the variable lift type fusion wing 20, while connecting the variable lift type fusion wing (20) disposed on both sides of the body (10). The variable lift type fusion fusion blades are coaxial to adjust at the same time, or are respectively connected to the variable lift type fusion wing 20 which is disposed on both sides of the body 10 to face each other. The angle adjustment of 20 is configured to be made separately.

Here, in the case of connecting the variable lift type fusion wing 20 to a coaxial wing drive shaft part (2), the variable lift type fused wing according to an aircraft, a ship, a train, and a vehicle (20) ) May be provided with a horizontal rudder (not shown), which is to provide an additional lift in addition to the lift generated from the variable lift type fusion wing (20) coaxially connected.

And, the drive unit 30 is driven to adjust the angle of the variable lift type fusion wing 20 according to the wind direction and wind speed information detected by the wind direction detection unit 40, according to the implementation of the present invention The fuselage 10 of the vehicle (aircraft) according to the example is angular 2019/212066 1 »（： 1 ^ 1 {2018/005007

26 Lifting control method The wind from the angle adjustment of the fusion wing (20) will allow safe takeoff or landing.

On the other hand, look at the application of the variable lift type fusion wing 20 described above according to the vehicle in more detail, first, the variable lift type fusion wing to the fuselage of the transportation means such as aircraft When applying (20), the aircraft is capable of taking off and landing at a sharp takeoff angle 犯 11) by adjusting the angle of the variable lift type fusion wing 20 as shown in (b) of FIG. 5. As a result, it is possible to expect an effect that can significantly reduce the aircraft's runway compared to the conventional.

At this time, the fuselage (10) is the aircraft fuselage and the two-sided variable lift type fusion wing (20) as described above on both sides of the aircraft fuselage (10) in the multi-stage arrangement, at least on the rear side of the aircraft fuselage (10) By constructing at least one engine section 11 and engine injection port 12, the engine section 11 has a conical engine injection port 12 having a rotational angle of 360 ° in up, down, left and right.

That is, since the angular lift type fusion wing 20 is arranged in multiple stages on both sides of the aircraft fuselage 10, the engine portion 11 cannot be configured in the adjacent portion of the wing, and thus the half-angle wing 20 ), The engine unit 11 is arranged in a space where there is no interference, i.e., the lower left and right side walls of the wing or the rear side of the upper body 10.

In constructing the engine unit 11, the engine unit 11 has a conical engine injection hole 12 having a rotation angle of 360 in the up, down, left, and right directions, and thus the aircraft body 10 can take off and land. Given that the direction of the wind, which has a great influence on the air, is different from time to time, turning the nose of the aircraft fuselage 10 toward the wind blowing 2019/212066 1 »（： 1 ^ 1 {2018/005007

It is to induce landing.

In addition, when the variable lift type fusion wing 20 is arranged in multiple stages on both sides of the aircraft fuselage 10 as described above, an auxiliary engine may be further applied to the aircraft fuselage 10, which is an aircraft. When there is a need for a large lift due to excessive load on the fuselage (10) or the excess number of passengers in need, or when the aircraft fuselage (10) needs to ascend to a large takeoff angle due to extreme weather, etc. This is to provide auxiliary thrust in case of no or low air pressure.

11 (a) (b) is a composite wing in which the fixed wing portion 20-1 and the angled wing portion 20-2 are installed in one independent variable lift type fusion wing 20 in combination The top view of the aircraft to which the structure is applied is shown.

Aircraft employing the structure of a compound wing, the outer wing (20-1) is attached to the outer wall of the fuselage (10) in a fixed form, the angle wing 20-2 is installed to adjust the rotation angle one 11 (a) illustrates a vertical structure compared to the fuselage in which the composite wings are installed at right angles to the fuselage (10), and in Fig. 11 (b) shows the composite wings. It shows the rear of the structure compared to the fuselage installed inclined at a constant inclination angle on the fuselage (10).

12 (a) (b) (c) is a plan view of the structure of a composite wing in which the fixed blade portion 20-1 and the angled wing portion 20-2 are repeatedly installed in one independent wing along the longitudinal direction. It is shown as.

12 (a) is an outer side showing a state in which the variable wing portion 20-2 is installed on the outer side of the fixed wing portion 20-1 fixedly attached to the outer wall of the fuselage 10 to adjust the rotation angle. 12 shows an outer type composite wing, and FIG. 12 (b) shows a state in which the angled wing parts 20_2 are arranged to be positioned between two fixed wing parts 20-1 to be spaced apart from each other. Intermediate type compound wings are shown, and FIG. 12 (c) shows an inner type in which the angled wing part 20-2 is installed to be positioned inside the fixed wing part 20-1. Each compound wing is shown.

13 (a), (b), (c) and (d) also show a view for explaining the structure of an extended return variable slide type composite wing in which one independent wing extends in the longitudinal direction.

FIG. 13A represents a general variable lift type fusion wing 20 having a structure of an integrated wing, whereas in FIG. 13A, FIG. 13A, FIG. It illustrates an angular lift type fused wing 20 having a structure of an extended return variable slide-type compound wing that is extended to.

(A) and (a ratio of the wide inner blade is fixed, and the narrow outer blade accommodated therein is driven in a piston type with a pneumatic or hydraulic cylinder driven to expand or contract from the tip of the inner wing The angular lift control method is showing a fusion blade (20).

On the other hand, Fig. 13 (c) (d) is fixed to act as a narrow inner blade axis is fixed, the wide outer wings that are installed so as to be wrapped around the outside is also equipped with a pneumatic or hydraulic cylinder Piston drive is to show the variable lift type variable fusion wing 20 of variable length to be expanded or reduced. Such a function of the present invention and the variable lift type fusion wing 20 and its effect is shown in FIG. 2019/212066 1 »（： 1 ^ 1 {2018/005007

29

The conceptual diagram presented in Figure 14 will give a better understanding.

(A) (B) (C) of Figure 14 is a general conceptual view of the variable lift type fusion wing, which can be applied to various types of transportation to be described below.

In other words, looking at the main concept of the present invention, the variable lift type fusion blade (20) is arranged in a row on the outer wall surface of the individual wings of the fan having a plurality of wings radially arranged around the rotating body Each of these blades is then subject to each transformation so that it can selectively provide as much lift (or buoyancy) and anti-lift (anti-buoyancy) as needed.

On the other hand, as an embodiment of the present invention, as shown in the accompanying Figure 15, the curve of the object having a lifting force (or buoyancy), anti-lift force (half buoyancy), and mobility to the body such as ships, trains, and automobiles It can also be applied to the wing of the antigen core force, the antigen core force is to control the force of the fuselage side.

That is, as shown in Figure 16, the long angular lift lifting fusion wing 20 lying horizontally on the basis of the drawing is to adjust the angle in the vertical direction by adjusting the angle, the small wings standing vertically ( 50) is to minimize the centrifugal force in the curve section by adjusting the angle, the angular lift control type fusion wing (20) and the small wing (50) in front of and behind the car is a very effective device.

In particular, when a load is exceeded due to a large load on a vehicle, the lift can be increased to lighten the vehicle, and on a rain or ice road, the vehicle can be stably operated by increasing the anti-lift force (grounding force). In addition, the wing of the antigen will catch the jungle of curves on the icy road, which will be a great help in winter or rain. 2019/212066 1 »（： 1 ^ 1 {2018/005007

30 prizes.

On the other hand, as an embodiment of the present invention, when the vehicle is a train or a car body (10 '), as shown in ①, ② of Figure 19, the variable lift type fusion wing 20 is the train The outer side of the upper side, or may be arranged in plurality on both sides of the outer side. Then, when the fuselage (10 ') of the vehicle or vehicle (10') moves along the ground or rail, the lift or anti-lift (ground force) can be provided through the angle adjustment of the variable lift type fusion wing (20). It is.

At this time, in the case of providing lift to the fuselage (10 ') of the vehicle through the variable lift type fusion wing (20), when the load is increased due to a lot of cargo or occupants in the fuselage (10') This is to reduce the fuel consumption when the fuel is consumed a lot to provide more propulsion while the fuselage (10 ') is not moved properly due to the increased load.

That is, when the lifting force is provided to the fuselage 10 'of the vehicle through the variable lift type fusion wing 20, the fuselage 10' has a slight flotation effect when moving along the ground or the rail. As expected, even if a lot of cargo is loaded or there are many tower approval sources, the movement can be made smoothly while reducing fuel consumption.

Here, the buoyancy effect of the fuselage (10 ') by the angular lift control type fusion wing (20) does not mean completely falling from the ground or rail, the wheel provided at the bottom of the fuselage (10') To minimize contact pressure. 2019/212066 1 »（： 1 ^ 1 {2018/005007

31 In the case of providing a semi-lift force to the fuselage 10 ¹ of the vehicle through the angular lift control type fusion vane 20, that is, the ground or the rail to the ground, cargo or cargo to the fuselage 10 'is provided. When the load is reduced while the number of passengers is small, the reduced load prevents the body (10) from shaking from the ground or the rail.

That is, when the anti-lift (grounding force) is provided to the fuselage 10 'of the vehicle through the variable lift type fusion wing 20, the fuselage 10' is moved along the ground or rail. As the contact force with the ground or the rail increases, the fuselage 1 can stably move along the ground or the rail.

On the other hand, if the vehicle is a fuselage (10 ¹ ), such as a train or a car as described above, as shown in ( ³ ), ④ of Fig. 19 attached to the outer upper side or both sides of the outer body of the fuselage (1) antigen core force It can be configured to arrange the centrifugal force control blades 50 for providing, the centrifugal force control blades 50 are configured alone or perpendicular to the variable lift type fusion wing 20 as shown in Figure 16 You can do it.

That is, the centrifugal force control wing 50 is to minimize the centrifugal force by adjusting the angle when the body 10 'of a vehicle or a vehicle such as a train or a vehicle moves along a curved road, a rain road or an ice road, and thus a train or a car. The fuselage of the vehicle (10 ') is to be able to move stable on curves, rain or ice roads.

On the other hand, as an embodiment of the present invention, when the vehicle is a fuselage (10'_) of the vessel (for example, large or small vessel), as shown in Figures 17 and 18 attached, the variable lift type fusion wing 20 may be arranged in plural on both sides of the outer bottom of the vessel, the wing drive shaft portion 20 of the variable lift type fusion wing 20 is the angle to provide a semi-buoyancy Is connected to the drive unit 30 to drive to adjust, the drive unit 30 is also configured to adjust the angle of the variable lift type fusion wing according to the water flow information detected by the water flow detection unit.

Then, when the fuselage (10 ″) of the vehicle, such as a ship moves along the water surface, it is possible to provide a semi-buoyancy (receiving force) through the angle adjustment of the variable lift type fusion wing (20).

At this time, when providing the buoyancy force to the fuselage (10 ") through the angular lift control method fusion wing (20), by pulling down the ship's fuselage (10") to provide stability to the fuselage, and therefore Considering the loaded cargo or the number of passengers to cruise at the best speed, if necessary due to the rapidly changing weather or tide during the cruise control the wing angle control of the variable lift type fusion wing 20 By increasing the anti-buoyancy (receiving force), it is possible to quickly play the role of a ballast tank.

In this way, if the function of the ballast tank is replaced by the variable lift type fusion vane 20, the fuel consumption is significantly reduced while reducing the overall load as compared to the conventional vessel that was filled with the ballast water (Bal last Water) In particular, it is possible to solve the environmental pollution problem caused by the discharge of ballast water.

That is, when the anti-buoyancy is provided to the fuselage (10 ") through the angular lift control method fusion wing (20), the fuselage (10 '') selects the flotation or half-lift effect when moving along the water surface As it can be expected, even if a large amount of cargo or a large number of passengers, the fuel consumption can be reduced while moving smoothly 2019/212066 1 »（： 1 ^ 1 {2018/005007

33 would.

On the other hand, in the case of a small high speed vessel as shown in FIG. 18, the variable lift type fusion wing 20 serves to lift the fuselage 10 "so that the ski slides on the surface of the water to minimize water resistance. It is.

In addition, when providing the buoyancy force, that is, the reception force with the water surface to the fuselage (10 '') through the variable lift type fusion wing (20), the cargo or passengers to the fuselage (10 '') When the load is reduced while being small, the reduced load prevents the fuselage (10 ") from falling too much from the water surface and overturning.

That is, when the anti-buoyancy (receiving force) is provided to the fuselage (10 ") through the variable lift type fusion wing (20), when the fuselage (10") moves along the water surface, As the contact force increases, the fuselage 10 'can move stably along the surface of the water.

Industrial Applicability

In the above description, the technical concept of the third generation aircraft, the ship, the train, and the vehicle equipped with the wing of the variable lift type of the present invention has been described with the accompanying drawings, which describes the most preferred embodiment of the present invention by way of example. It does not limit the invention.

Accordingly, the present invention is not limited to the above-described specific embodiments, and various modifications can be made by those skilled in the art without departing from the spirit of the invention as claimed in the claims. Of course, such changes are within the scope of the claims.

Claims

[Range of request]

[Claim 1]

Fuselage;

The left and right pairs are arranged on both sides or the upper portion of the fuselage at least two or more consecutively, and the angle can be adjusted based on a wing drive shaft positioned at the center of the wing so as to provide lift or anti-lift force opposite to the lift. It is installed so as to perform the function of the wing and the horizontal stroke at the same time the angular lift type fusion control method; And, a drive unit for tilting the variable lift control type fusion wing at an angle to provide a lift or a semi-lift lift around the wing drive shaft; Including;

The variable lift control type fusion wing has a wing body that generates lift by having a general aircraft wing shape of a streamlined cross section, and in the front and rear of the wing body (wind dividor) and wind pressure plate ( The wind pressor is installed to extend, respectively, wherein the wind dividor and the wind pressor are positioned on a line passing through the wing driving shaft, and at the same time, connecting a line and a rear end of the wing body. A low-13th generation aircraft equipped with a variable lift type wing, which is installed in a flat shape placed on the plane, so that the streamlined wing body maintains a minimum cross section and provides increased lift during high angle takeoff and landing.

[Claim 2]

According to claim 1, wherein the angular lift-type fusion wing is formed evenly from the front to the rear of the fuselage to form a pair of left and right, at least two or more consecutively, by evenly distributing the lift between all the fuselage, Fuselage horizontally 2019/212066 1 »（： 1 ^ 1 {2018/005007

35 _Third- generation aircraft with variable lift control wings, characterized by being configured for landing.

[Claim 3]

The method of claim 1, wherein the drive unit is configured to connect to the wing drive shaft portion and the connecting member of the variable lift type fusion fusion blades to adjust the angle of the variable lift type fusion fusion blades arranged in a plurality at the same time. A third generation aircraft equipped with a wing of the variable lift type characterized in that.

[Claim 4]

The method according to claim 1, wherein the drive unit is a plurality of 1: 1 each of the wing drive shaft of the variable lift control method fusion blades arranged to individually adjust the front, rear, left and right angles of the variable lift control method fusion blades are arranged in plurality. Third generation aircraft equipped with a wing of the variable lift type, characterized in that consisting of.

[Claim 5]

The variable lift type control method according to claim 3 or 4, wherein the driving unit drives the variable lift type adjustment method to adjust the angle of the fusion wing according to the wind direction and wind speed information detected by the wind direction detection unit. 3rd generation aircraft with wings

[Claim 6]

The third-generation aircraft equipped with the wing of the variable lift type, characterized in that the variable lift type fusion wing disposed in both sides of the fuselage is arranged in the same horizontal line. 2019/212066 1 »（： 1 ^ 1 {2018/005007

36

[Claim 7]

The third-generation aircraft equipped with the wing of the variable lift type, characterized in that the variable lift type fusion wing arranged in a plurality of portions on both sides of the fuselage.

[Claim 8]

According to claim 1, wherein the variable lift type fusion wing disposed in a plurality on both sides of the fuselage is equipped with a wing of the variable lift type, characterized in that arranged in a zigzag shape cross each other up and down. Third generation aircraft.

[Claim 9]

According to claim 1, The variable lift type fusion wing disposed in a plurality on both sides of the fuselage is configured to gradually expand the width and length of the wing in the order arranged from the front side to the rear side, A third generation aircraft equipped with a wing of a variable lift type, characterized by minimizing interference caused by vortices or waves from the wing.

[Claim 10]

According to claim 1, Between the variable lift lifting type fusion blades disposed in a plurality on both sides of the fuselage is further configured to configure a fixed wing that does not adjust the angle to prevent interference flow, adjacent angular Variable lift control, characterized in that it performs the role of rudder through the angle control of the lift control method fusion wing, and ensures flight stability by maintaining the basic lift in the event of the angular lift control method fusion wing failure. Third generation aircraft equipped with wing of type.

[Claim 11]

According to claim 1, wherein the variable lift type fusion wing disposed in a plurality on both sides of the fuselage, outside the fixed blade is attached to the fixed form on the fuselage outer wall, the angle of the wing is adjustable angle of rotation Installed to form one unit compound wing,

The unit composite wing has a vertical structure compared to the fuselage installed at right angles to the fuselage; Or a rear jungle type structure compared to the fuselage installed at an inclined angle to the fuselage; A third generation aircraft equipped with a wing of the variable lift type, characterized in that any one of which is selectively applied.

[Claim 12]

According to claim 1, wherein the variable lift type fusion wing disposed in a plurality on both sides of the fuselage, unit composite wings repeatedly installed fixed blade portion and the angled blade opening along the longitudinal direction on one independent wing Is applied,

The unit compound wing, the outer wing (combined outer type) composite wing is installed to be fixed to the outer wall fixed to the fuselage form and the variable wing portion on the outer side to adjust the rotation angle; Or intermediate blade (Intermediate type) composite blade arranged to be positioned between the two fixed blades are installed spaced apart from each other wings; Or an inner type compound wing installed to have an angled wing portion located inside the fixed wing portion; Third generation aircraft equipped with a wing of the variable lift type, characterized in that any one of the optional installation.

[Claim 13] 2019/212066 1 »（： 1 ^ 1 {2018/005007

38. The variable lift type fused wing of claim 1, wherein the variable lift control type fusion wing disposed in a plurality of sides of the fuselage is applied with a structure of an extended return variable slide type compound wing in which one independent wing extends in the longitudinal direction. ,

The variable slide type composite wing has a wide inner blade fixed thereto, and a narrow outer blade accommodated therein is driven in a piston manner with a pneumatic or hydraulic cylinder to expand or contract from the tip of the inner blade. wing; Alternatively, the variable width of the inner blade that is fixed so that the inner blade is fixed to act as an axis, and the wide outer blade that is installed so as to be unfolded and expandable is driven by a piston method with a pneumatic or hydraulic cylinder to expand or contract. Fusion wing; A third generation aircraft equipped with a wing of the variable lift type, characterized in that any one of the installation.

[Claim 14]

According to claim 1, The lifting angle of the variable lift control type fusion wing is provided for the variable lift type adjustment method characterized in that it is adjusted within the range of 43 ^° to 87 ^{° in} the upward direction relative to the horizontal line. 3rd generation aircraft with its wings.

[Claim 15]

According to claim 1, wherein the angle for providing the anti-lift of the variable lift control type fusion wing is adjusted in the range of 13 ^° to 15 ^{° in} the downward direction based on the horizontal line variable lift control Third generation aircraft equipped with wing of type.

[Claim 16]

According to claim 1, The rear side of the aircraft at least one engine unit and 2019/212066 1 »（： 1 ^ 1 {2018/005007

A third-generation aircraft equipped with a wing of a variable lift type, comprising a nozzle.

[Claim 17]

17. The third generation aircraft of claim 16, wherein the engine unit has a cone-shaped engine injection port having a rotation angle of 360 ^° in up, down, left, and right directions.

[Claim 18]

Fuselage;

At least two of the left and right pairs are arranged continuously on both sides of the fuselage or the upper portion of the fuselage, providing the fuselage or the anti-lift force opposite to the lift force, and the angle is adjusted around the wing drive shaft part. Fused wing with variable lift control method, which provides the fuselage stability through lift and maintains constant clearance between the fuselage and rail through anti-lift;

Centrifugal force control blades for providing the antigenic core force on the outer upper portion or the outer both sides of the fuselage body; And

A drive unit configured to drive the variable lift control type fusion blade and the centrifugal force control vane at an angle providing lift or an angle providing anti-lift force about the blade drive shaft; Third generation train equipped with a wing of the variable lift type, characterized in that it comprises a.

[Claim 19]

The method of claim 18, 2019/212066 1 »（： 1 ^ 1 {2018/005007

At least two of the variegated lift control fusion vanes which are arranged in pairs at right and left and at least two are arranged evenly from the front to the rear of the fuselage to distribute the lift evenly between the fuselage bulbs. Third generation train with variable lift control wings.

[Claim 20]

19. The method of claim 18, wherein the drive unit is configured to be connected to the connecting shaft and the blade opening coaxial part of the variable lift type control type fusion blades to simultaneously adjust the angle of the variable lift type control fusion blades are arranged in plurality. The third generation train equipped with variable lift type wing.

[Claim 21]

19. The method according to claim 18, wherein the drive unit is configured to be 1: 1 to each of the wing drive shaft portion of the variable lift type fusion fusion wing to individually adjust the angle of the variable lift type fusion fusion wing disposed in plurality. A third generation train equipped with a variable lift type wing.

[Claim 22]

22. The variable type as claimed in claim 20 or 21, wherein the driving unit is configured to adjust the angle of the variable lift type control fusion blade according to the wind direction, wind speed, and wind speed information detected by the wind direction detecting unit. Third generation train with lift control wing.

[Claim 23]

20. The apparatus of claim 19, wherein the plurality of the body parts are arranged on both sides of the fuselage or on the outside of the body. 2019/212066 1 »（： 1 ^ 1 {2018/005007

41 is the third-generation train equipped with a wing of the variable lift type, characterized in that the variable lift type fusion wing is disposed on the same horizontal line.

[Claim 24]

[Claim 20] The angular lift control system of claim 19, wherein the angular lift control type fusion blades disposed on both sides of the fuselage or a plurality of outer sides of the fuselage are arranged in a step shape. Third generation train.

[Claim 25]

20. The angular lift control system according to claim 19, wherein the angular lift control system fusion blades disposed on both sides of the fuselage or on an outer side of the fuselage are arranged in a zigzag manner as being crossed up and down. Third generation train with wings.

[Claim 26]

19. The third generation train of claim 18, wherein the centrifugal force control vane is configured to be perpendicular to the variable lift type fusion vane.

[Claim 27]

Fuselage;

It is disposed on the front and rear sides of the fuselage, and provides the lifting force or anti-lifting force opposite to the lifting force, and the angle is adjusted around the wing drive shaft, providing the fuselage stability through lifting, Variable lift control fusion wing that maintains a constant distance between the fuselage and the road surface through the lift; 2019/212066 1 »（： 1 ^ 1 {2018/005007

42 a centrifugal force control wing for providing an antigenic core force on the outer upper side or outer outer side of the fuselage; And

A drive unit for driving the variable lift control type fusion blade and the centrifugal force control blade to be adjusted at an angle for providing lift or an angle for providing a semi-lift force about the blade drive shaft; Third generation cars equipped with a wing of the variable lift type control method comprising a.

[Claim 28]

The wing of the variable lift type control method according to claim 27, wherein the driving unit drives to adjust the angle of the variable lift type fusion fusion blade according to the wind direction and wind speed information detected by the wind direction detector. Equipped with third generation car.

[Claim 29]

28. The third generation of automobiles according to claim 27, wherein the centrifugal force control vane is configured to be perpendicular to the variable lift type fusion vane.

[Claim 30]

Fuselage;

At least two or more pairs are arranged in a row on the outer bottom of the fuselage or on the upper side or the roof of the fuselage, and at least two or more are arranged consecutively and provide buoyancy or anti-buoyancy opposite to the buoyancy, and ballast.

1 ₃此) variable angle lift control fusion wing with angle adjustment centered on the coaxial part of the wing; And ，

The variable lift type fusion wing is buoyancy centering on the wing drive shaft 2019/212066 1 »（： 1 ^ 1 {2018/005007

43 a drive unit for driving to adjust the angle provided or the angle providing the anti-buoyancy; Third generation ship equipped with a wing of the variable lift type, characterized in that comprising a.

[Claim 31]

31. The angular lift control type fusion vane according to claim 30, wherein left and right pairs of left and right pairs are arranged consecutively on the outer bottom of the fuselage are evenly installed from the front of the fuselage to the rear of the fuselage. Third generation ship equipped with a wing of the variable lift type, characterized in that evenly distributed throughout the fuselage.

[Claim 32]

31. The method of claim 30, wherein the drive unit is configured to be connected to the connecting shaft and the blade opening coaxial part of the variable lift type adjustable fusion fusion blade to adjust the angle of the variable lift type fusion fusion blade is arranged in a plurality. The third generation of ships equipped with a wing of the variable lift type.

[Claim 33]

31. The method of claim 30, wherein the drive unit is configured to be configured to each 1: 1 in the wing drive shaft of the variable lift type fusion fusion wing to individually adjust the angle of the variable lift type fusion fusion wing disposed in plurality. A third generation ship equipped with a wing of the variable lift type.

[Claim 34]

34. The method of claim 32 or 33, wherein the drive unit is driven to adjust the angle of the variable lift type fusion wing according to the water flow information detected by the water flow detection unit 2019/212066 1 »（： 1 ^ 1 {2018/005007

A third-generation ship equipped with a wing of a variable lift type, characterized in that.

[Claim 35]

31. The variable lift control method according to claim 30, wherein the variable lift type fusion vanes disposed in plural on the outer bottom of the fuselage or on the upper side or roof of the fuselage are arranged on the same horizontal line. Third generation ship with wings.

[Claim 36]

31. The variable lift type wing according to claim 30, wherein the variable lift type fusion wing disposed in plurality on the outer side of the fuselage or on the upper side or roof of the fuselage is disposed in a step shape. 3rd generation ship equipped with a.

[Claim 37]

31. The angular type according to claim 30, wherein the variable lift type fusion fusion blades disposed on the outer bottom of the fuselage or on the upper side or roof of the fuselage are arranged in a zigzag shape that crosses each other up and down. Third generation ship equipped with lift control wing.