KR20160121197A

KR20160121197A - Flying object opration system

Info

Publication number: KR20160121197A
Application number: KR1020150050878A
Authority: KR
Inventors: 장수영
Original assignee: 장수영
Priority date: 2015-04-10
Filing date: 2015-04-10
Publication date: 2016-10-19
Also published as: WO2016163794A1; KR101715731B1

Abstract

The present invention relates to a system for operating flying objects which are connected to the ground to receive power from the ground, and are controlled to stay at a certain position. The system for operating flying objects levitated from the ground, comprises: at least two flying objects which fly in the air; a ground unit installed on the ground; and wire units which connect between the flying objects and the ground unit. In regards to this, the wire unit comprises a wire whose one end is connected to the ground unit, and the other end is connected any one of the flying objects; a wire whose one end is connected to the ground unit, and the other end is connected any one of the other flying objects; and a wire which connects between the flying objects. According to the present invention, only one ground unit is used for positioning the flying objects in the air at high altitude, and a plurality of the wire units that connect the flying objects and the ground unit are spaced from each other to prevent a short circuit caused by interference between the wire units. Thus, the system for operating flying objects may easily be installed.

Description

Flying object opration system

BACKGROUND OF THE INVENTION 1. Field of the Invention [0002] The present invention relates to a flying body, and more particularly, to a flying body operating system that is connected to the ground and is supplied with power from the ground and is controlled to stay at a predetermined position.

In general, a flying object is an object flying in the air, and can be largely divided into self-powered vehicles such as airplanes and non-powered vehicles such as airships and gliders.

A typical example of a non-powered aircraft is an airplane that injects a lighter gas than the air into the air bag (气囊) to obtain most of the lift from the gas.

The characteristics of these airships, that is, the stability of airship in the air, the flexibility and economy, have been widely used in advertisement, sports broadcasting, travel, transportation industry and observation fields.

Recently, along with the development of the information communication field, researches for utilizing the stratosphere that is advantageous for communication and observation are actively carried out. Since the stratosphere is formed from about 8 to 10 km above the earth and about 50 to 56 km long, the weather is very stable compared to the troposphere. Various techniques are being developed to utilize the meteorological phenomenon. Airships are being studied together.

In other words, since the density of air in the stratosphere is about one-quarter of that of sea level, the drag force on the airship is small, the propulsion energy required to maintain the position is not so large and the altitude is higher than that of the satellite in the geostationary orbit of 3,6000 km The 30 km stratosphere has advantages such as low transmission delay, low transmission loss, wide area high speed mobile communication / high capacity high speed communication / fire detection.

In addition, the stratosphere can acquire a wider range of images than aircraft, and can be very useful in the field of earth observation.

In this way, airships must perform at least 2km or more from the ground to perform various missions even if they do not reach the stratosphere or the stratosphere. In such high altitudes, it is a harsh environment with a density and temperature which is significantly lower than the ground. Stable power is essential for airship operation.

In order to carry out various tasks, more stable electric power is required for the airship. In order to supply the stable power, the connection with the ground is the most reliable method.

However, due to the nature of the airship which can not be fixed at a certain position, it is not easy to supply electric power through connection with the ground, and it is very costly to realize this.

As a result of this study, the applicant of the present invention has provided a flight unit capable of stably supplying power through a separate wire unit by separating a power line from Korean Patent No. 10-1429567 (Prior Art 1).

However, in the prior art 1, since a plurality of ground units must be installed on the ground in order to fix a plurality of wire units, there is a problem that the installation cost due to site acquisition increases, and installation construction becomes complicated.

In order to reliably perform various tasks such as communication and observation using such a flight body, it is essential to stably maintain the position of the flight body within a predetermined range.

As a result of this study, the applicant of the present invention has provided a flight unit capable of stably controlling the position of a flying object on a high altitude through a horizontal wing and a vertical wing in Korean Patent No. 10-1388491 (Prior Art 2).

At this time, the above-mentioned air vehicle can be effectively used for military purposes because it can be used for observation and communication by operating a small air vehicle at low altitude on high altitude.

However, in the prior art 2, because the position control of the flying object is performed through the horizontal wing and the vertical wing, the positional exposure through the radar is easy due to the vertical wing, which poses a problem of security weakness in use as a military facility.

Korean Patent No. 10-1429567 Korean Patent No. 10-1388491

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems of the prior art, and it is an object of the present invention to provide a flight operation system that can separate a wire unit while using one ground unit.

It is another object of the present invention to provide a flight operation system having a stealth function by significantly reducing a detection rate on a radar, while allowing a flight to stably stay within a specific range and performing its mission.

According to an aspect of the present invention, there is provided a system for operating a flying object floating from the ground, comprising: at least two airborne flying objects; One ground unit installed on the ground; And a wire unit connecting between the airship and the ground unit, wherein the wire unit comprises: a wire having one end connected to the ground unit and the other end connected to one of the flying objects; A wire having one end connected to the ground unit and the other end connected to one of the other flying objects; And a wire connecting between the flying objects.

The present invention also provides a system for operating a floating body from above ground, comprising: a flying body that floats in the air; One ground unit installed on the ground; And a wire unit connecting between the airship and the ground unit, wherein the wire unit comprises at least two wires, wherein the wires comprise wires of different lengths .

At this time, at least one of the wires other than at least the longest wire among the wires may further include a friction unit for generating frictional force.

A plurality of the friction units may be provided on the wire.

The friction unit may be composed of frictional units of different sizes so that different drag forces are generated depending on the length of the wire to be installed.

And at least the shortest wire among the wires may be formed of a plurality of high-strength fiber materials.

Further, the wire may be configured to include a power line for power supply.

The ground unit or the air vehicle may be provided with a guide unit for fixing the ends of the wires so as to be disposed in a spaced apart direction.

Further, the guide unit may include: a fixing plate fixed to the ground unit or the lower end of the air vehicle; A rotating plate which is rotated in a horizontal direction with respect to the fixed plate; A support plate installed upright in a direction perpendicular to the rotation plate; And a plurality of supports connected to the support plate by hinges and rotatably installed in the vertical direction and extending in mutually spaced directions to be coupled with the wires.

According to another aspect of the present invention, there is provided a system for operating a flying object floating from the ground, comprising: a flying object supported in the air; One ground unit installed on the ground; And a wire unit connecting between the airship and the ground unit, wherein the airship body is formed to extend in a direction inclined upward or downward from a side surface of the airship body, And a tilt blade that adjusts the direction of the drag with respect to the wind.

The inclined riff may be formed to be inclined upward from both left and right sides of the air vehicle.

In addition, the inclined ripples may be formed to be inclined downward from both left and right sides of the air vehicle.

The present invention also provides a system for operating a floating body from above ground, comprising: a flying body that floats in the air; One ground unit installed on the ground; And a wire unit connecting between the airship and the ground unit, wherein the airship body is formed to extend in a horizontal direction from a side surface of the airship body and is rotatably provided with respect to a side surface of the airship body, And a horizontal wing to control the direction of the aircraft.

At this time, the flight body may further include an adjustment wire that rotates the flying body to position the horizontal blade in an inclined shape.

And the flight body comprises: an adjustment wire including a first adjustment wire and a second adjustment wire respectively connected to the left and right sides of the airplane; And an adjusting unit for adjusting the lengths of the first adjusting wire and the second adjusting wire.

The following effects can be expected in the airship operating system according to the present invention as described above.

That is, in the present invention, a plurality of wire units for connecting the air vehicle and the ground unit are used to prevent a short circuit due to interference between the wire units, while using only one ground unit, So that the installation of the flight operation system can be facilitated.

Further, the present invention has an effect of providing a flight operation system optimized for military purposes by controlling the radar to detect a flying object stably within a specific range, and by providing a stealth function by significantly reducing the detection rate of the radar.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a block diagram showing a first embodiment of a flight operating system according to a specific embodiment of the present invention. FIG.
BACKGROUND OF THE INVENTION 1. Field of the Invention [0002] The present invention relates to a flight operation system,
3 is a block diagram showing a third embodiment of a flight operation system according to a specific embodiment of the present invention.
4 is a detailed block diagram showing the configuration of a guide unit applied to a flight operation system according to a specific embodiment of the present invention.
5 is a block diagram showing a first embodiment of a flight operation system according to another embodiment of the present invention.
FIG. 6 is a block diagram showing a second embodiment of a flight operation system according to another embodiment of the present invention; FIG.
7 is a schematic view showing a principle of generation of position control drag of a flight operating system according to another embodiment of the present invention.
FIG. 8 is a block diagram showing a third embodiment of a flight operation system according to another embodiment of the present invention. FIG.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a flight operation system according to a preferred embodiment of the present invention will be described with reference to the accompanying drawings.

The airborne vehicle operation system according to the specific embodiment of the present invention supports the airborne vehicle through one ground unit. Various embodiments of the present invention will now be described.

FIG. 1 is a block diagram showing a first embodiment of a flying object operating system according to a specific embodiment of the present invention. FIG. 2 is a block diagram showing a second embodiment of a flight object operating system according to a specific embodiment of the present invention. FIG. 3 is a configuration diagram showing a third embodiment of a flying object operating system according to a specific embodiment of the present invention, FIG. 4 is a view showing a guide unit applied to a flying object operating system according to a specific embodiment of the present invention. And Fig.

First, as shown in Fig. 1, a first embodiment of the specific embodiment of the present invention includes a single ground unit 200, two wires connected to the ground unit 200, And a plurality of air vehicles 100 staying in position.

The ground unit 200 is installed on the ground to maintain the position of the air vehicle 100, receives data observed by the air vehicle 100, and supplies power to the air vehicle 100 as the case may be .

A first wire 310 and a third wire 330 are connected to the ground unit 200 to supply power to the air vehicle 100. The first wire 310 and the third wire 330 are connected to each other, Are connected to different air vehicles 100, respectively.

The air vehicle 100 may be various types of air vehicles 100 having an auxiliary power unit in the non-powered air vehicle 100 or the non-powered air vehicle 100 to perform various operations while staying in the stratosphere.

Hereinafter, for convenience of explanation, the air vehicle 100 will be described as a representative example.

The airplane 100 can be used for a long period of time by floating in the air through an air bag filled with gas, so that various operations such as observation can be economically used. The gas filled in the air sac of the air vehicle 100 can be various kinds of gases such as helium which are lighter than air.

The operation unit 120 includes a power unit for operating the air vehicle 100 or a variety of devices for performing the mission of the air vehicle 100 (measurement, observation, communication, etc.) .

Meanwhile, a rotating socket 140 may be provided at a lower portion of the air vehicle 100. The rotary socket 140 is rotatably installed on the air vehicle 100 and functions to prevent the wire from being twisted by the rotation of the air vehicle 100.

A solar panel 150 may be provided on the upper portion of the air vehicle 100. The solar panel 150 is for collecting solar heat, and can supply some of the power required for operation of the air vehicle 100. Of course, the solar panel 150 may be selectively applied according to the purpose and method of use of the air vehicle 100.

In addition, the air vehicle 100 is provided with a position control unit for controlling the position of the air vehicle 100. The position control unit is configured to vary the direction of the drag of the air body 100 to allow the air body 100 to stay at a specific position, and may be composed of various types of blades, which will be described in detail below.

It is important to fix the position of the air vehicle 100 within a certain range and it is also important to keep the power (power) for performing the operation of the air vehicle 100, It is also necessary to provide stable supply.

At this time, the air vehicle 100 receives electric power from a wire connected to the ground unit 200.

The wire unit 300 includes a first wire 310 and a third wire 330 connected to the ground and a second wire 320 connected between the air vehicle 100.

That is, the wire unit 300 includes a first wire 310 having one end connected to the ground unit 200 and the other end connected to the air vehicle 100, a second wire 310 connected between the air vehicles 100 And a third wire 330 having one end connected to the other flying object 100 and the other end connected to the ground unit.

Accordingly, the air vehicles 100 are connected in series on a power supply circuit composed of the first wire 310, the second wire 320 and the third wire 330, and are supplied with electric power.

Although FIG. 1 illustrates the air vehicle operation system including two air vehicles 100, it is also possible that a plurality of air vehicles 100 are connected in series by a second wire (connecting wire) 320, respectively Do.

Two wires are connected to the ground unit 200 and each airplane 100. The ground unit 200 and the airplane 100 are connected to two wire connections And guide units 160 and 210 as shown in FIG.

The detailed structure of the guide unit will be described in detail below.

On the other hand, disposing the wires apart from each other can prevent a short circuit between the wires for power supply. As a result, the possibility of electric leakage is low because the wires are sufficiently spaced apart from each other, so that a large voltage (a high voltage of several hundreds to tens of thousands of volts or more) can be applied to each wire. This means that the thickness of the wire can be made relatively small as a result.

As shown in FIG. 2, the second embodiment of the aircraft operation system according to the embodiment of the present invention includes one ground unit 200, one air vehicle 100, and a plurality of wires And a wire unit 200 including the wire unit 200.

At this time, the wires are configured to have different lengths. That is, as shown in FIG. 2, when a wire unit is composed of two wires, the wire unit is composed of a short wire 340 and a long wire 350 having a short length.

As a result, a tension greater than that of the long wire 350 is generated in the short wire 340. Accordingly, the long wire 350 is held in an elongated shape by the wind force and the self weight, whereby the short wire 340 and the long wire 350 are kept spaced apart from each other.

Therefore, as described above, high-voltage power can be supplied through the wires without risk of occurrence of a short circuit between the wires.

Meanwhile, the wire unit may include two or more wires, and may have different lengths to supply three-phase, five-phase, or more power types with each wire being spaced apart.

In other words, power can be supplied to the air vehicle 100 in various configurations according to the number of the wires. For example, when the wire unit is composed of two wires, each wire is connected to two May be separately included in the wire.

Alternatively, when the wire unit is composed of three wires, each of the wires may include two power supply lines and a ground line for supplying the direct current or alternating current power separately to each of the wires, May be separately included in the wires.

When the wire unit is composed of three wires, each of the wires may include two power lines for supplying the DC or AC power, and a communication line for communication with the ground.

Of course, the wire unit may consist of five wires, each of which may include five power sources, and may include more wires.

As described above, when the number of the wire units is increased, the wires necessary for power supply and communication are separately arranged for each wire unit, thereby making it possible to utilize the wire unit stably and economically.

The short wire 340 also functions to prevent the flying object 100 from moving away from the ground unit 200 by a predetermined distance.

For this, the short wire 340 may be formed of a plurality of high-strength fiber materials. Of course, the short wire 340 may be made of a fiber material including glass-reinforced fiber or shrinkable fiber, or may include various other materials.

When the short wire has a weight to tensile strength of 900% or more, for example, a short wire having a diameter of 0.5 mm is extended to 20 km, the shot wire provides a tensile strength of about 45 kg to 75 kg to the flight body 100, Can be sufficiently fixed within the buoyancy range.

Although not shown, the wire unit may be provided with a current sensor unit. The plurality of current sensors are intermittently provided along the longitudinal direction of the wire unit to detect a short circuit of the wire unit. When a wire unit having a very long length is disconnected, Make it easy to find out.

It is preferable that at least a part of the wire unit adjacent to the ground unit is provided with a reinforcing cover for reinforcing the strength of the wire unit or the thickness of the wire unit is increased. This is to prevent damage of the wire unit due to collision with a bird or the like.

In order to secure the end portions of the wires, guide units 160 and 210 may be provided in the air body 100 and the ground unit 200 so that the wires are arranged in a direction away from each other.

3, the third embodiment of the air vehicle operation system according to the embodiment of the present invention may further include a friction unit 360 on the long wire.

That is, the third embodiment of the air vehicle operation system according to the specific embodiment of the present invention further comprises the friction unit 360 in the same configuration as the second embodiment of the air vehicle operation system according to the specific embodiment of the present invention .

At this time, the friction unit 360 generates frictional force by the wind force. As shown in FIG. 3, the frictional unit 360 may be formed in a continuous form, but may be formed in various forms having high wind resistance.

On the other hand, a plurality of the friction units may be provided on the wire.

When the wire unit includes three or more wires, friction units of different sizes may be provided on the wires to generate different drag forces.

Hereinafter, the specific structure of the guide units 160 and 210 provided at the ends of the wires to guide the arrangement of the wires so that the wires are oriented in different directions will be described.

4, the guide units 160 and 210 include supporting units 215 and 216 for fixing and supporting the wires in the arranging direction, and hinges (not shown) for allowing the supporting units 215 and 216 to rotate in the vertical direction 214), and a rotary plate (212) for allowing the support rods (215, 216) to rotate in the horizontal direction.

A fixing plate 211 fixed to the ground unit 200 or the lower end of the air body 100 and a rotary plate 212 rotated in the horizontal direction with respect to the fixing plate 211.

On the rotation plate 212, a support plate 213 is provided, which is installed upright in a direction perpendicular to the rotation plate 212.

The support plate 213 includes support rods 215 and 216 which are connected to each other by a hinge 214 so as to be rotatable in a vertical direction and extend in directions separated from each other.

At this time, a plurality of support rods 215 and 216 are formed according to the number of wires, and they are formed at angles apart from each other.

In the following, another embodiment of the present invention relating to a position control method of a flying object will be described.

Another embodiment of the present invention relates to a flight control system having a stealth function and capable of controlling the position of the aircraft, and is capable of controlling the position of the aircraft in vertical and horizontal positions without the vertical vanes, System.

FIG. 5 is a configuration diagram showing a first embodiment of a flight operation system according to another embodiment of the present invention, FIG. 6 is a configuration diagram showing a second embodiment of a flight operation system according to another embodiment of the present invention FIG. 7 is a schematic view showing a principle of generating a position control drag force of a flight operation system according to another embodiment of the present invention, and FIG. 8 is a view showing a third embodiment of a flight operation system according to another embodiment of the present invention FIG.

As shown in FIG. 5, a flying body 100 constituting a first embodiment of a flying body operation system according to another embodiment of the present invention is provided with a upward inclined wing 130.

The upwardly inclined wing 130 is a wing extending in a direction obliquely upward toward both sides of the air vehicle 100 and is configured to be rotatable with respect to a side surface of the air vehicle 100.

The upward inclined wing 130 generates a drag with respect to the vertical direction of the upward inclined wing 130 as it rotates with respect to the side of the air vehicle 100, The direction of the drag force and the magnitude of the drag are changed.

7, the sum of the drag force a generated by the rotation of the left upward inclined wing and the drag force beta generated by the rotation of the right upward inclination wedge occurs in the air vehicle 100 .

Since the drag force α and the drag force β are changed by the rotation direction and the rotation angle of the right upward slope and the leftward upward slope, respectively, the drag force in all directions is generated from the sum of the drag force α and the drag force β, Can be moved in all directions.

Next, as shown in FIG. 6, the air vehicle 100 constituting the second embodiment of the air vehicle operation system according to another embodiment of the present invention is provided with a downwardly inclined wing 135.

The downwardly inclined wing 135 is a wing extending in the obliquely downward direction on both side surfaces of the air vehicle 100 and is configured to be rotatable with respect to a side surface of the air vehicle 100.

The downwardly inclined wing 135 also generates a drag with respect to the vertical direction of the downwardly inclined wing 135 as the upper inclined wing 130 rotates about the side of the air vehicle 100, The direction of the drag and the magnitude of the drag are changed according to the rotational direction and the degree of the drag.

The principle of drag generation of the downward incline wing 135 is the same as that of the upward incline wing 130 described with reference to FIG.

8, the air vehicle 100 constituting the third embodiment of the air vehicle operation system according to another embodiment of the present invention includes a horizontal wing 180, control wires 510 and 520, (530).

The horizontal wing 180 is a wing extending horizontally on both sides of the air vehicle 100 and is rotatable with respect to a side of the air vehicle 100.

At this time, the horizontal wing 180 generates a drag force in the vertical direction as it rotates with respect to the side surface of the air vehicle 100, and adjusts the direction and the magnitude of the drag force according to the rotation direction and the degree of the horizontal wing 180 .

Meanwhile, the control wires 510 and 520 rotate the air body 100 to position the horizontal wing 180 in a sloped manner.

The control wires 510 and 520 include a first control wire 510 and a second control wire 520 connected to the left and right sides of the air vehicle 100, respectively. The ends of the first control wire 510 and the second control wire 520 are connected to the control unit 530 and the control unit 530 controls the first control wire 510 and the second control wire 520 To determine the degree of rotation of the air vehicle 100.

As the adjustment unit 530 adjusts the length of the adjustment wires 510 and 520, the air vehicle 100 rotates so that the horizontal wing 180 is positioned in an inclined shape. In this state, 180, the drag force of the gradient vector is generated.

Thus, the horizontal wing 180 can generate forward drag in accordance with the same principle as the above-described upward wing wing and downward wing wing.

In order to control the position of the air vehicle 100, a means for detecting the position of the air vehicle 100 is required.

That is, the position calculation of the air vehicle 100 can be performed by various methods. It is possible to calculate the position from the GPS module by providing a GPS module inside the air vehicle 100, It is also possible to calculate the position of the air vehicle 100 by observing the air vehicle 100 and transmit the calculated position information of the air vehicle 100 to the control unit.

Alternatively, an observing section composed of a camera for observing the terrain and the ground on the ground is installed. It is also possible to calculate the position of the air vehicle 100 from an observation result (a topographic photograph, a photograph showing a relative position with respect to a specific milestone, etc.) observed by the observation unit.

At this time, by further including the radar measuring unit or the laser measuring unit, the distance from the ground is calculated and used together with the observing result of the observing unit, it is possible to calculate the position value with higher accuracy.

It is to be understood that the invention is not limited to the disclosed embodiment, but is capable of many modifications and variations within the scope of the appended claims. It is self-evident.

The present invention relates to a flight operation system that is connected to a ground and is supplied with electric power from the ground and is controlled to stay at a predetermined position. According to the present invention, when a flying object is positioned above an elevation, The plurality of wire units connecting the air unit and the ground unit can be spaced apart from each other so that a short circuit due to interference between the wire units can be prevented.

100: air vehicle 120:
130: Upward slope 135: Downward slope
140: Rotating socket 150: Solar panel
170: wire guide 180: horizontal wing
200: ground unit 210, 160: guide unit
211: fixed plate 212: rotary plate
213: support plate 214: hinge
215: first support bar 216: second support bar
300: wire unit 310: first wire
320: second wire 330: third wire
340: short wire 350: long wire
360: Friction unit 400: Single wire
510: first adjustment wire 520: second adjustment wire
530:

Claims

CLAIMS 1. A system for operating a floating body from above ground,
Two or more airborne vehicles supported in the air;
One ground unit installed on the ground; And
And a wire unit connecting between the airship and the ground unit,
The wire unit includes:
A wire having one end connected to the ground unit and the other end connected to one of the flying objects;
A wire having one end connected to the ground unit and the other end connected to one of the other flying objects; And
And a wire connecting the flying objects to each other.

CLAIMS 1. A system for operating a floating body from above ground,
A flying body that is supported in the air;
One ground unit installed on the ground; And
And a wire unit connecting between the airship and the ground unit,
The wire unit includes:
Wherein the wire comprises two or more wires, wherein the wires comprise wires of different lengths.

CLAIMS 1. A system for operating a floating body from above ground,
A flying body that is supported in the air;
One ground unit installed on the ground; And
And a wire unit connecting between the airship and the ground unit,
The wire unit includes:
Wherein a friction unit for generating frictional force is provided on at least one of the wires, the friction unit including at least two wires.

The method of claim 3,
The wires constituting the wire unit include wires of different lengths:
The friction unit includes:
And a plurality of wires are provided on the wire.

5. The method of claim 4,
The friction unit includes:
Wherein the frictional units are constructed of frictional units of different sizes so that different drag forces are generated depending on the length of the wire to be installed.

3. The method of claim 2,
Wherein at least the shortest wire among the wires is formed of a plurality of strands of high-strength fiber material.

7. The method according to any one of claims 1 to 6,
The wire
And a power supply line for power supply.

8. The method of claim 7,
In the ground unit or the air vehicle,
And a guide unit for fixing the end portions of the wires so as to be arranged in a spaced apart direction.

9. The method of claim 8,
The guide unit includes:
A fixing plate fixed to the ground unit or the lower end of the air vehicle;
A rotating plate which is rotated in a horizontal direction with respect to the fixed plate;
A support plate installed upright in a direction perpendicular to the rotation plate;
And a plurality of supports connected to the support plate by a hinge so as to be rotatable in a vertical direction and extending in directions separated from each other and coupled with the wires.

CLAIMS 1. A system for operating a floating body from above ground,
A flying body that is supported in the air;
One ground unit installed on the ground; And
And a wire unit connecting between the airship and the ground unit,
The air-
And a tilt blade which is formed to extend in a direction inclined upward or downward from a side surface of the flying object and is rotatable with respect to the side surface of the flying object to adjust the direction of the drag force against the wind.

11. The method of claim 10,
The above-
Wherein the airbag is formed to be inclined upward from both left and right sides of the airplane.

11. The method of claim 10,
The above-
Wherein the airbag is formed in a shape inclined downward from both left and right sides of the airplane.

CLAIMS 1. A system for operating a floating body from above ground,
A flying body that is supported in the air;
One ground unit installed on the ground; And
And a wire unit connecting between the airship and the ground unit,
The air-
And a horizontal blade which extends horizontally from a side surface of the airplane and is rotatable with respect to a side surface of the airplane to adjust the direction of the drag against the wind.

14. The method of claim 13,
The air-
Further comprising an adjustment wire for rotating the flying object to position the horizontal blade in an inclined manner.

14. The method of claim 13,
The air-
An adjusting wire including a first adjusting wire and a second adjusting wire respectively connected to the left and right sides of the airplane;
And a control unit for controlling the lengths of the first control wire and the second control wire.