KR20210045005A - Takeoff and landing system for aircraft having fixed wing and method thereof - Google Patents

Abstract

According to the present invention, disclosed is a take-off and landing system of an aircraft having a fixed-wing, comprising: a lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connecting part supporting the hub to be able to rotate; a launcher disposed at a take-off site, and having a power generator and a rotating member rotated by the power generator and provided with a connection part which can be fitted with the coupling part to be able to slip; and a connecting line fixed to one side of the launcher or one side of the take-off site to be extended to the connecting part. The lift propeller is rotated by the rotating member in a state in which the coupling part and the connection part are fitted with each other. Moreover, the lift propeller is separated from the rotating member by lift, generated by the lift propeller, and rises in air to a height at which the connecting line is pulled taut to lift the aircraft having a fixed-wing or to capture the aircraft having a fixed-wing using the connecting line.

Description

Takeoff and landing system for fixed wing aircraft {TAKEOFF AND LANDING SYSTEM FOR AIRCRAFT HAVING FIXED WING AND METHOD THEREOF}

The present invention relates to a system and method for take-off and landing of a fixed-wing vehicle, and more particularly, to a system and method for take-off and landing of a fixed-wing vehicle capable of taking off and landing without a runway.

Aircraft, such as fixed-wing aircraft, perform many commercial, military and civilian tasks. Fixed-wing aircraft are efficient for long-distance cruising, and unmanned aerial vehicles have the advantage of being able to fly long distances with relatively little fuel compared to multi-rotor aircraft. However, fixed-wing aircraft typically require runway space long enough to accelerate for take-off and decelerate for landing.

In order to overcome the shortcomings of the fixed-wing aircraft, as disclosed in Patent Document 1, there is a method of taking off with a propulsion force such as a rubber belt, pneumatic, rocket, etc. from a rail launch pad when taking off. This is a method of shortening the take-off distance by giving the aircraft a rapid acceleration instantaneously to obtain a speed above the stall speed before the aircraft leaves the launch pad.

However, the method of using the rail launcher also requires a lot of space for installation of the rail launcher, and it is difficult to mount a vehicle.

Alternatively, Patent Document 2 discloses an aerial launch and/or recovery of an unmanned aerial vehicle having a structure for launching a fixed-wing unmanned aerial vehicle by installing a launch pad in a multi-rotor carrier aircraft, and a system and method related thereto. However, Patent Document 2 requires a multi-rotor transport aircraft for launching a fixed-wing unmanned aerial vehicle, so it is difficult to quickly take off the fixed-wing unmanned aerial vehicle from the ground.

Patent Document 1: Korean Registered Patent Publication No. 10-1013851 (2011.02.01) Patent Document 2: Korean Patent Publication No. 2017-0040103 (2017.04.12)

The present invention has been invented in consideration of the above problems, and an object of the present invention is to provide a system and method for take-off and landing of a fixed-wing vehicle having a structure capable of taking off a fixed-wing vehicle without a runway or a rail launch pad.

Another object of the present invention is to provide a system and method for take-off and landing of a fixed-wing vehicle capable of simplifying the structure of a fixed-wing vehicle and reducing its weight by arranging an engine for take-off at a take-off location.

Another object of the present invention is to provide a system and method for take-off and landing of a fixed-wing aircraft having a structure capable of improving the air stability of a lift propeller connected to a connecting line during take-off and landing of a fixed-wing aircraft.

In order to achieve the above object, the present invention provides a lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connection part rotatably supporting the hub; A launch device having a rotating member disposed at a take-off location, rotating by a power generator and the power generator, and provided with a connecting portion capable of being fitted with the coupling portion; And a connection line fixed to one side of the launch device or one side of the take-off location and extending to the connection part, wherein the lift propeller rotates by the rotation member in a state where the coupling part and the connection part are fitted with each other, and the A fixed wing vehicle, characterized in that the lift propeller is separated from the rotating member by the lift generated from the lift propeller and ascends into the air to a height at which the connection line is pulled tightly to lift the fixed wing vehicle or capture the fixed wing vehicle using the connection line. Provides a take-off and landing system.

The connection portion includes a radial bearing in which an upper end of the hub is fitted to an inner ring and fixedly disposed, a connecting ring fixed to an outer ring of the radial bearing, a support arm extending radially from the connecting ring, and an end of the support arm It may include a guard ring connected to and disposed outside the rotation path of the lift propeller, and a holder installed on the support arm and coupled to the fixed wing aircraft.

Semicircular swing wires are installed on both sides of the guard ring so as to be rotatable between a horizontal position and a vertical position, and the connecting wire may be connected to the swing wire.

In addition, it may further include a locking means that is installed so as to be caught on a part of the fixed wing vehicle or the connecting portion to selectively allow the take-off of the fixed wing vehicle when the jam is released.

According to another aspect of the present invention, (a) a lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connection part provided with a holder rotatably supporting the hub and capable of being coupled to a fixed-wing vehicle. Preparing; (b) preparing a launching device having a power generator and a rotating member provided with a connection part that rotates by the power generator and is fitted with the coupling part; (c) setting the lift propeller on the launching device so that the connecting portion and the coupling portion are fitted with each other, and connecting the connecting portion and the launching device to each other with a connecting line; (d) arranging a fixed wing vehicle on the connecting portion; (e) driving the launch device to rotate the lift propeller at high speed; (f) taking off into the air while the lift propeller is separated from the rotating member by the lift generated by the lift propeller; And (g) the fixed wing vehicle is separated from the lift propeller to fly with its own thrust and lift.

According to another aspect of the present invention, (1) preparing a lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connection part rotatably supporting the hub; (2) preparing a launching device having a power generator and a rotating member provided with a connection part that rotates by the power generator and is fitted with the coupling part; (3) setting the lift propeller on the launch device so that the connecting portion and the coupling portion are fitted with each other; (4) driving the launch device to rotate the lift propeller at high speed; (5) taking off into the air while the lift propeller is separated from the rotating member by the lift generated by the lift propeller, and disposing a connecting line vertically in the air between the lift propeller and the launch device; (6) capturing the fixed wing aircraft by manipulating the fixed wing aircraft so as to be caught on the connecting line; And (7) recovering the fixed wing vehicle.

In the step (6), the step of operating a parachute mounted on the lift propeller when the fixed wing aircraft is captured; may further include.

The take-off and landing system and method of a fixed wing vehicle according to the present invention has the following effects.

First, it is possible to vertically take off a fixed-wing vehicle without a runway or rail launch pad or take off in a short time in a diagonal direction toward the air, thus simplifying the take-off system, and it is possible to take off the fixed-wing vehicle even in a narrow place or in a poor environment.

Second, since the engine (power generator) for taking off the fixed wing aircraft is located at the take-off site, the total take-off weight of the lift propeller and the fixed wing aircraft can be reduced, and regardless of the take-off gross weight, the high-power energy required for the take-off of the fixed wing aircraft can be supplied. have.

Third, since the ends of the connecting line connecting the launch device and the lift propeller can be aligned in the center of the lift propeller by the swing wire, the posture of the lift propeller can be stably maintained during takeoff and landing of the fixed wing vehicle.

Fourth, since a separate flight control device is not required for the flight of the lift propeller, operation is convenient and system cost can be reduced.

Fifth, when the fixed wing vehicle is landed, the lift propeller can be launched to quickly place a connecting line for capturing the fixed wing vehicle in the air. In addition, after the fixed-wing vehicle is captured, it can be automatically recovered by natural descending according to the deceleration of the lift propeller, and the fixed-wing vehicle can be more stably descended and recovered by the parachute device deployed from the lift propeller.

The following drawings attached to the present specification illustrate preferred embodiments of the present invention, and serve to further understand the technical idea of the present invention together with the detailed description of the present invention to be described later. It is limited to and should not be interpreted.
1 is a partial cross-sectional view showing the configuration of a take-off and landing system of a fixed wing aircraft according to a preferred embodiment of the present invention.
It is a configuration diagram showing a modified example of FIG.
3 is a block diagram schematically showing a state in which the swing wire is rotated in FIG. 2.
4 is a front configuration diagram of the lift propeller in FIG. 3.
5 is a partial cross-sectional view illustrating a configuration in which a weight body is disposed on a hub in FIG. 1.
6 is a block diagram showing an example in which the locking means is installed in the launch device.
7 is a diagram schematically showing a process of taking off a fixed wing vehicle according to the present invention.
8 is a diagram illustrating a modified example of FIG. 7.
9 is a diagram schematically showing a process of capturing a fixed wing vehicle according to the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, terms or words used in the specification and claims should not be construed as being limited to their usual or dictionary meanings, and the inventors appropriately explain the concept of terms in order to explain their own invention in the best way. Based on the principle that it can be defined, it should be interpreted as a meaning and concept consistent with the technical idea of the present invention. Accordingly, the embodiments described in the present specification and the configurations shown in the drawings are only the most preferred embodiment of the present invention, and do not represent all the technical spirit of the present invention. It should be understood that there may be equivalents and variations.

1 is a block diagram of a take-off and landing system of a fixed wing vehicle according to a preferred embodiment of the present invention.

1, the take-off and landing system of a fixed wing vehicle according to a preferred embodiment of the present invention includes a lift propeller 10, a launch device 20 disposed at a take-off site to launch a lift propeller 10 into the air, and launch It includes a connecting line 40 that is fixed to one side of the device 20 or one side of the take-off site and extends to the lift propeller 10.

The lift propeller 10 includes a hub 12 provided with a coupling part 11, at least one blade 13 connected to the hub 12, and a holder connected to the hub 12 and capable of being combined with the fixed wing aircraft 1 It is provided with a connection part 14 with (19).

The hub 12 and the blade 13 may be integrally formed of a material such as synthetic resin, wood, or metal. Alternatively, the hub 12 and the blade 13 may be configured as separate members capable of being detachably assembled from each other.

The lift propeller 10 rotates the assembly of the hub 12 and the blade 13 by the rotational force provided from the launch device 20, and is launched by the lift generated accordingly to lift the fixed-wing vehicle 1 into the air. lift) or, as described later, it serves to support the connecting line 40 in the air so that the fixed-wing aircraft 1 can be captured using the connecting line 40 as described later.

The lift propeller 10 is arranged such that one side (upper part) of the connection part 14 supports at least one of a fuselage, a wing, and a center of gravity of a fixed-wing vehicle (see 1 in FIG. 7 ). Here, the fixed-wing vehicle 1 may correspond to an unmanned aerial vehicle (drone), an aircraft, a fighter, a toy airplane, etc. having a thrust generating unit 2 made of at least one rotor and a fixed wing 3. In addition, the fixed wing vehicle 1 may be a rocket or a missile having a cylindrical body with a fixed wing at the rear part. The thrust generating unit 2 provided in the fixed wing vehicle 1 may be composed of a jet engine or a rocket in addition to the rotor.

The coupling part 11 extends in the thickness (height) direction of the hub 12 and is formed in the shape of a groove or hole having a rectangular inner wall. Correspondingly, the connection part 23 provided in the launch device 20 is configured in a shape of a pin having a square cross section that is fitted to the coupling part 11 so as to be slipped in the longitudinal direction. Alternatively, the coupling part 11 may be configured in the form of at least two or more holes. In this case, the connection part 23 provided in the launching device is configured in the form of at least two rod-shaped pins (or projections) that are slipped into the coupling part 11 in the longitudinal direction. Alternatively, the groove/pin (protrusion) structure of the coupling portion 11 and the connection portion 23 may be interchanged with each other.

The connection part 14 includes a radial bearing 15 in which the upper end of the hub 12 is fitted to the inner ring and fixedly disposed, a connecting ring 16 fixed to the outer ring of the radial bearing 15, and a connecting ring 16 at one end. ) Connected to the plurality of support arms 17 extending radially from the connection ring 16, and a guard ring 18 connected to the other end of the support arm 17 and disposed outside the rotation path of the blade 13 , It includes a holder 19 coupled to the fixed wing vehicle (1). The connection part 14 supports the assembly of the hub 12 and the blade 13 and is coupled with the fixed wing aircraft 1.

The holder 19 holding the fixed wing vehicle 1 from the top of the lift propeller 10 may be implemented by a metal plate or a predetermined gripper mechanism having a substantially'U' or'V' shape in cross section. .

As shown in FIGS. 2 and 3, swing wires 41 made of hard metal are disposed on both sides of the guard ring 18 so as to be rotatable vertically between a horizontal position and a vertical position. As shown in Figure 4, the swing wire 41 is preferably configured in a semi-circular shape. The upper end of the connection line 40 to be described later is connected to the midpoint of the swing wire 41.

The swing wire 41 is arranged to be in contact with the side of the guard ring 18, and when the lift propeller 10 rises and the connecting line 40 is pulled tightly, the swing wire 41 is selectively rotated in the longitudinal direction. Thus, it is tilted downward as shown in FIGS. 3 and 4. According to this configuration, since the swing wire 41 is placed in a horizontal position at the beginning of launch of the lift propeller 10, the swing wire 41 and the connecting wire 40 are directly influenced by the downward wind of the lift propeller 10. Can be prevented from receiving. To prevent the swing wire 41 from unnecessarily rotating by maintaining the swing wire 41 in a horizontal position, a predetermined permanent magnet ( 43) can be deployed.

When the lift propeller 10 rises in the air to a height corresponding to the length of the connecting line 40 and the connecting line 40 is pulled taut, the swing wire 41 is bent and placed in the vertical direction, so the lift propeller 10 Can maintain a stable posture. That is, in a state in which the lift force is acting on the lift propeller 10, the part where the connecting line 40 and the swing wire 41 are connected to each other is located in the center of the lift propeller 10 and is prevented from being pulled to one side. It is possible to stably maintain the posture of the lift propeller 10 during takeoff and landing of 1).

5, the lift propeller 10 is mounted on the hub 12 and rotates integrally with the hub 12 to increase the rotational moment of inertia, thereby increasing the flight time of the lift propeller 10. ) May be added. The weight 54 may be made of a ring-shaped lead (Pb) material interposed between the inner ring of the radial bearing 15 and the hub 12. As a modified example, a method of configuring the hub 12 itself as a lead material may also be considered. However, if the hub 12 itself is made of lead material, the coupling portion 11 formed on the hub 12 may be easily worn, so the hub 12 is made of a material such as synthetic resin, wood, aluminum, etc. The weight 54 is more preferably made of a ring-shaped lead material interposed between the inner ring of the radial bearing 15 and the hub 12. Alternatively, the weight 54 is configured in a disk shape fixed to cover the upper surface of the hub 12, and it is also possible to rotate integrally with the hub 12.

As shown in Figure 6, the locking means 51 is configured in the form of a pin (pin) that can be fitted to a part of the connecting portion (14). The locking means 51 is installed to be selectively fitted to the connection part 14 through a frame 53 of a predetermined shape connected to the power generator 21. Accordingly, the locking means 51 can be easily separated from the connection portion 14 by an operation of pulling the string 52 connected to the locking means 51. The locking means 51 selectively permits take-off of the fixed-wing aircraft upon releasing the jam. Specifically, the locking means 51 restrains the take-off of the fixed-wing vehicle 1 by being caught by the connecting portion 14 in a state in which the connecting portion 23 and the coupling portion 11 are fitted together, and when released, the fixed-wing vehicle 1 Separated to allow fixed-wing aircraft to take off. Alternatively, the locking means 51 may be configured in the form of a predetermined bar or hook installed to be rotatable.

In addition, the pivot part for the rotation of the swing wire 41 is installed to be slidable up and down along a long hole (not shown) formed in the height direction of the guard ring 18, and the holder 19 is interlocked with the lowering of the pivot part. It can be configured so that the fixed wing aircraft (1) is separated.

Preferably, a parachute device 50 may be additionally installed on one side of the guard ring 18 of the lift propeller 10. Parachute device 50, as described later, in a state in which the fixed wing vehicle 1 is caught and captured by the connecting line 40, when the lift propeller 10 momentarily swings due to a sudden change in load, an acceleration sensor, etc. It detects and operates to open automatically to provide a function to safely recover the lift propeller 10 and the fixed wing vehicle 1. Alternatively, the parachute device 50 may be configured to be manually operated by a predetermined remote control device.

The launch device 20 is disposed on the support part 30 of the take-off site, rotates by the power generator 21 and the power generator 21, and can be fitted to the coupling part 11 so as to be slipped in the longitudinal direction. It includes a rotating member 22 provided with a connecting portion 23 made of a protruding structure as described above. The support part 30 may be the ground (or floor) itself, alternatively may be a frame structure of a predetermined shape placed on the ground (or floor). Alternatively, the support part 30 may be a frame structure of a predetermined shape mounted on a vehicle, ship, aircraft, or the like. Alternatively, the support 30 may be a metal plate of a predetermined size, a container, or a part of a carrier box of a predetermined size.

The power generator 21 may be made of a high-power motor that generates a high-speed rotational force of thousands to tens of thousands of rpm by a battery or a commercial power source. Alternatively, the power generator 21 may be made of an engine or a pneumatic generator using fuel such as gasoline. In the present invention, the power generator 21 providing the driving force to the lift propeller 10 is not mounted on the fixed wing aircraft 1 and is located at the take-off site, so the weight of the power generator 21 is the total takeoff of the fixed wing aircraft 1 Since it does not add to the weight, a large-capacity power unit (motor or engine) may be employed.

The rotating member 22 is a member that is connected to the rotating shaft of the power generator 21 and rotates, and may be preferably constituted by a circular block. The upper end of the rotating member 22 is provided with a pin-shaped connection part 23 that can be slipped into the coupling part 11 of the lift propeller 10 so as to be slipped in the longitudinal direction.

In a state in which the fixed-wing vehicle 1 is arranged (set) on the launch device 20 so that the connection part 23 and the coupling part 11 are fitted together, the rotation member 22 is rotated using the power generator 21 to lift The propeller 10 rotates at high speed. When the lift propeller 10 rotates and a sufficient lift force is generated in the lift propeller 10, the connection part 23 is removed from the coupling part 11, and the lift propeller 10 is separated from the rotating member 22, and the lift propeller 10 Together with the fixed wing aircraft (1) will take off into the air.

When the lower end of the connection line 40 is connected to the launch device 20, the connection line 40 passes through a predetermined mount on both sides of the power generator 21 in order to prevent the firing of the lift propeller 10 from being obstructed. Thus, a swing wire 42 having the same operation as the swing wire 41 described above may be disposed.

The connecting line 40 is fixed to one side of the launch device 20 or one side of the take-off site and extends to the swing wire 41 provided in the connection part 14. The connecting line 40 functions to separate the fixed wing vehicle 1 from the lift propeller 10 by inertia by limiting the elevation of the lift propeller 10 during takeoff and stopping the elevation of the lift propeller 10 at the same time. . In addition, the connecting line 40 is used to prevent the loss of the lift propeller 10 and to capture the fixed wing aircraft 1 when landing the fixed wing aircraft 1. An elastic member made of a spring or a rubber band is connected to at least a portion of the connection line 40 to provide elasticity in the longitudinal direction to the connection line. As a variant, the connection line 40 may be made of a material having elasticity.

7 schematically shows a process of taking off a fixed wing vehicle according to the present invention.

Referring to FIG. 7, the method of taking off and landing a fixed wing vehicle according to a preferred embodiment of the present invention includes a process of preparing a lift propeller 10 and a launch device 20 having the above-described configuration, and a lift propeller on the launch device 20. The process of setting (10), the process of arranging the fixed-wing vehicle (1) on the connection portion (14) of the lift propeller (10), the process of driving the launch device (20) to rotate the lift propeller (10) at high speed, and , As the lift propeller 10 is separated from the rotating member 22 of the launch device 20 by the lift generated in the lift propeller 10, the fixed wing vehicle 1 together with the lift propeller 10 take off into the air, and , When the connecting line 40 rises to the maximum point where it becomes taut, the fixed wing vehicle 1 is separated from the lift propeller 10 to fly with its own thrust and lift.

The process of taking off the fixed-wing vehicle 1 together with the lift propeller 10 in the air may be performed vertically by placing the launch device 20 in a vertical direction. Alternatively, it is also possible to take off the fixed-wing vehicle 2 along an oblique path as shown in FIG. 8 by firing the lift propeller 10 by tilting the launch device 20 at an inclined angle. In this case, there is an advantage that a predetermined lift force can be generated from the fixed wing vehicle 1 in the process of firing the fixed wing vehicle 1 together with the lift propeller 10.

9 shows an example of capturing the fixed wing vehicle 1 in the landing process of the fixed wing vehicle 1 according to the present invention.

9, the landing method of the fixed wing vehicle 1 is to launch the lift propeller 10 into the air using the launch device 20 in advance before the fixed wing vehicle 1 approaches, so that the connecting line 40 is perpendicular to the air. It is disposed, and during the flight time of the lift propeller 10, the fixed wing vehicle 1 is manipulated to pass the connecting line 4 so that the end of the fixed wing 3 is caught on the connecting line 40.

That is, the landing method of the fixed wing vehicle 1 is a process of setting the lift propeller 10 on the launch device 20 so that the connection part 23 and the coupling part 11 are fitted together, and driving the launch device 20 The lift propeller 10 is separated from the rotating member 22 by the process of rotating the lift propeller 10 at high speed, and the lift generated by the lift propeller 10 takes off into the air, and the lift propeller 10 and the launch device 20 ), the process of arranging the connecting line 40 vertically in the air between, and the process of capturing the fixed-wing vehicle 10 by controlling the fixed-wing vehicle 1 so that the end of the fixed wing 3 is caught on the connecting line 40, and , Including the process of recovering the fixed wing aircraft (10).

In the state where the fixed-wing vehicle 1 is caught by the connecting line 40 and captured, the lift propeller 10 momentarily swings through the connecting line 40 due to a sudden change in load. When the mounted parachute device 50 is operated, the lift propeller 10 and the fixed wing vehicle 1 can be more safely recovered.

The take-off operation of the lift propeller 10 for take-off and landing of the fixed-wing vehicle 1 can be selectively permitted by operating a locking means installed to be caught on a part of the fixed-wing vehicle 1 or the connecting part 14.

The present invention having the above configuration can simplify the take-off system since the fixed wing vehicle 1 can be taken off without a runway or a rail launch pad, and the power generator 21 for taking off the fixed wing vehicle is located at the take-off location, so the lift There is an effect of reducing the total take-off weight of the propeller 10 and the fixed wing aircraft (1).

In the above, although the present invention has been described by the limited embodiments and drawings, the present invention is not limited thereto, and within the scope of the technical idea of the present invention by those of ordinary skill in the art to which the present invention pertains. Of course, various modifications and variations are possible.

1: fixed wing vehicle 10: lift propeller
11: coupling part 12: hub
13: blade 14: connection
15: radial bearing 16: connecting ring
17: support arm 18: guard ring
19: holder 20: launch device
21: power generator 22: rotating member
23: connection part 30: support part
40: connecting cord 41, 42: swing wire
50: parachute device 51: locking means

Claims (7)

In the system for taking off and landing a fixed wing aircraft having a fixed wing and a thrust generating unit,
A lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connection part rotatably supporting the hub;
A launch device having a rotating member disposed at a take-off location, rotating by a power generator and the power generator, and provided with a connecting portion capable of being fitted with the coupling portion; And
Includes; a connection line fixed to one side of the launch device or one side of the take-off site and extending to the connection part,
The lift propeller is rotated by the rotating member while the coupling part and the connecting part are inserted into each other, and the lift propeller is separated from the rotating member by the lift generated by the lift propeller to a height at which the connecting line is pulled tightly. A take-off and landing system for a fixed-wing vehicle, characterized in that ascending into the air to lift a fixed-wing vehicle or capturing a fixed-wing vehicle using the connecting line. The method of claim 1, wherein the connection part,
A radial bearing in which the upper end of the hub is fitted to the inner ring and fixedly disposed, a connecting ring fixed to the outer ring of the radial bearing, a support arm extending radially from the connecting ring, and connected to an end of the support arm. A system for taking off and landing a fixed wing aircraft, comprising: a guard ring disposed outside a rotation path of a lift propeller, and a holder installed on the support arm and coupled to a fixed wing aircraft. The method of claim 2,
Semicircular swing wires are installed on both sides of the guard ring so as to be rotatable between a horizontal position and a vertical position,
Take-off and landing system of a fixed wing aircraft, characterized in that the connecting line is connected to the swing wire. The method of claim 3,
The fixed wing aircraft take-off and landing system further comprising a; locking means installed so as to be caught on a part of the fixed wing aircraft or the connecting portion to selectively allow the take-off of the fixed wing aircraft when the jam is released. (a) preparing a lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connecting part provided with a holder rotatably supporting the hub and capable of being coupled to a fixed-wing vehicle;
(b) preparing a launching device having a power generator and a rotating member provided with a connection part that rotates by the power generator and is fitted with the coupling part;
(c) setting the lift propeller on the launching device so that the connecting portion and the coupling portion are fitted with each other, and connecting the connecting portion and the launching device with a connecting line;
(d) arranging a fixed wing vehicle on the connecting portion;
(e) driving the launch device to rotate the lift propeller at high speed;
(f) taking off into the air while the lift propeller is separated from the rotating member by the lift generated by the lift propeller; And
(G) the fixed wing vehicle is separated from the lift propeller to fly with its own thrust and lift; the take-off and landing method of a fixed wing vehicle comprising. (1) preparing a lift propeller having a hub provided with a coupling part, a blade connected to the hub, and a connection part rotatably supporting the hub;
(2) preparing a launching device having a power generator and a rotating member provided with a connection part that rotates by the power generator and is fitted with the coupling part;
(3) setting the lift propeller on the launch device so that the connecting portion and the coupling portion are fitted with each other;
(4) installing a connecting line so as to extend from one side of the launch device or one side of the take-off site to the connecting portion of the lift propeller;
(5) driving the launch device to rotate the lift propeller at high speed;
(6) taking off into the air while the lift propeller is separated from the rotating member by the lift generated by the lift propeller, and disposing a connecting line vertically in the air between the lift propeller and the launch device;
(7) capturing the fixed wing vehicle by manipulating the fixed wing vehicle so as to be caught on the connecting line; And
(8) the step of recovering the fixed wing aircraft; the take-off and landing method of the fixed wing aircraft comprising a. The method of claim 6, wherein in step (7),
The step of operating a parachute mounted on the lift propeller when the fixed wing vehicle is captured; take-off and landing method of the fixed wing vehicle further comprising.

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