WO2020145677A1

WO2020145677A1 - Drone

Info

Publication number: WO2020145677A1
Application number: PCT/KR2020/000381
Authority: WO
Inventors: 최영준; 김종성
Original assignee: 최영준
Priority date: 2019-01-11
Filing date: 2020-01-09
Publication date: 2020-07-16
Also published as: KR101967249B1

Abstract

A drone according to an embodiment of the present invention includes a flywheel (26) and a vane (28) in a gyro rotor unit (20), wherein the flywheel (26) is rotated to generate a lift in a direction perpendicular to a travelling direction of the drone so as to implement the Magnus effect, and thus reinforce the lift, and the flywheel (26) and the vane (28) are rotated together so as to implement the gyroscopic effect, whereby a horizontal orientation can be restored so as to implement stable flight. With the drone according to an embodiment of the present invention, when it is determined that battery power is lower than or equal to a set level, the flywheel is rotated so as to forcibly implement the gyroscopic effect and the Magnus effect, so as to prevent the drone from falling suddenly.

Description

drone

The present invention relates to drones or airplanes that increase lift and restore and stabilize flight posture.

In general, the drone can be arranged in the horizontal direction of the propeller rotation axis like an airplane, and the propeller rotation axis can be arranged in the vertical direction like a helicopter, so that the runway can be vertically taken off and landed.

The drone can be configured to include an electric motor and a battery, the electric motor can operate the propeller with battery power, and the drone can stably fly when the battery power is available.

However, drones can quickly consume battery power, which can lead to very short drone flight times and slow flight speeds.

In addition, the drone may suddenly fall because the battery power is suddenly lowered, and thus the thrust or lift by the propeller is not sufficiently implemented.

When a drone is flying and suddenly falls freely and falls, the drone itself can become a dangerous object, for example, it can cause damage such as injuries or damage to objects.

[Advanced technical literature]

(Patent Document 1) KR 10-0747082 B1

Therefore, the technical problem to be achieved by the present invention is to install a flywheel in the form of a disk on one side of the drone, and implement a Magnus effect by rotating the flywheel so that the drone receives force in the upward direction to reinforce lift. The purpose of this is to provide a drone that can significantly reduce the fall rate in the event of an emergency such as a malfunction or battery exhaustion.

Another object of the present invention is to provide a drone that can increase the flight time of the drone by reinforcing lift with the Magnus effect.

The drone according to an embodiment of the present invention for achieving the above technical problem is fixed to the left and right symmetrically with respect to the vertical center line (a) and is formed in a wide direction in the left or right direction or rear; And a drone according to an embodiment of the present invention for achieving the above technical problem in the fixed wing (2), the left and right symmetrical with respect to the vertical center line (a) and fixed wing (2) formed wide in the left or right direction; And a gyro rotor unit 20 symmetrical to the left and right of the fixed center 2 based on the vertical center line a or disposed on the vertical center line a.

The gyro rotor unit 20 includes a bracket 22 installed on the fixed wing 2; A shaft axle 24 installed in the bracket 22 such that the vertical center line (a) and the rotation axis (c) form a right angle; A flywheel 26 installed on the shaft axle 24 and implementing lift in a vertical direction with respect to the traveling direction of the vehicle according to rotation, and restoring to a horizontal posture; And a vane 28 installed on the shaft axle 24 and rotating to rotate the flywheel 26 under the influence of ambient airflow.

In addition, the drone according to an embodiment of the present invention, the flywheel 26 is provided in a plurality, the vane 28 is disposed between any one flywheel 26 and the other flywheel 26; includes can do.

In addition, in the drone according to an embodiment of the present invention, when the vane 28 is formed with a part of the outer edge inclined, the vane 28 is rotated to form a cone shape when a rotating body is realized.

In addition, the drone according to an embodiment of the present invention, one flywheel 26 may have a larger diameter or a larger circumferential surface area (w) than the other flywheel 26.

In addition, the drone according to an embodiment of the present invention, the first magnetic 52 is arranged in a circular arrangement in which the polarity is uniformly arranged in the flywheel 26; A magnetic driver 50 installed on the fixed wing 2 to rotate the rotor by an electric motor; And the polarities of the magnetic driver 50 are aligned and arranged in a circular arrangement, and when the magnetic driver 50 is operated, magnetic force is applied to the first magnetic 52 so that the flywheel 26 rotates. It may include; a second magnetic (54) acting.

In addition, the drone according to an embodiment of the present invention, the drone control unit 10 disposed on the vertical center line (a) in the main body (1); includes,

The drone control unit 10 may provide electric magnetic energy of the battery to the magnetic driver 50 in preference to other electronic devices when the remaining battery detection value is equal to or less than a reference value.

In addition, the drone according to an embodiment of the present invention, the horizontal length (width) is the same as the length of the shaft axle 24 or formed within a range of about 5%, the gyro rotor unit 20 in the fixed wing 2 It may include; an extended fixed wing (4) disposed at the back of the installed portion.

Specific details of other embodiments are included in the detailed description and drawings.

The drone according to the embodiment of the present invention made as described above may reinforce the lift by implementing the Magnus effect during the cruise flight, thereby increasing the flight time.

In addition, the drone according to the embodiment of the present invention can restore the posture of the vehicle by implementing the gyro effect by rotating the flywheel.

In addition, the drone according to the embodiment of the present invention can force the Magnus effect by rotating the flywheel when the battery power is determined to be below the set level, thereby preventing the drone from suddenly falling without being controlled. This allows the drone to descend at a slower speed, like a parachute, so that it can land safely.

In addition, the drone according to an embodiment of the present invention can achieve stable flight by rotating the flywheel when flying regardless of the battery level.

1 and 2 FIGS. 1 and 2 are front and plan views for explaining a drone according to an embodiment of the present invention.

3 is a view for explaining the configuration of a gyro rotor unit in a drone according to an embodiment of the present invention.

4 is a view for explaining the configuration of another example gyro rotor unit in a drone according to an embodiment of the present invention.

5 is a view for explaining the installation configuration of a gyro rotor unit in a drone according to an embodiment of the present invention.

6 to 11 are views for explaining a drone according to another embodiment of the present invention.

12 is a view for explaining the concept of a drone for electricity generation according to another embodiment of the present invention.

Advantages and features of the present invention, and methods for achieving them will be clarified with reference to embodiments described below in detail together with the accompanying drawings.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the embodiments described below are illustratively shown to help understanding of the present invention, and that the present invention can be implemented in various ways different from the embodiments described herein. However, when it is determined that the detailed description of the known functions or components related to the present invention may unnecessarily obscure the subject matter of the present invention, the detailed description and specific illustration will be omitted. In addition, the accompanying drawings may not be drawn to scale in order to aid the understanding of the invention, but the size of some components may be exaggerated.

Meanwhile, terms such as first and second may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from other components. For example, the first component may be referred to as a second component without departing from the scope of the present invention, and similarly, the second component may be referred to as a first component.

On the other hand, terms that will be described later are terms that are set in consideration of functions in the present invention, which may vary depending on the intention or custom of the producer, so the definition should be made based on the contents throughout the present specification.

The same reference numerals refer to the same components throughout the specification.

[Description of codes]

1: main body 2: fixed wing

3: Steering wing 4: Extended fixed wing

10: drone control

20: gyro rotor unit 22: bracket

24: shaft axle 26: flywheel

28: vane 30: tilt rotor

40: helium balloon 42: wind generator

43: power generation department

50: magnetic driver 52, 54: first and second magnetic

60: power transmission connection

Hereinafter, a drone according to an embodiment of the present invention will be described with reference to FIGS. 1 and 2. 1 and 2 are a front view and a plan view for explaining a drone according to an embodiment of the present invention.

The drone according to the embodiment of the present invention may include a main body 1, a fixed wing 2, and a gyro rotor unit 20.

The main body 1 may be provided in various ways depending on the shape of the aircraft, and the main body 1 may be equipped with electronic equipment for controlling the drone. Electronic equipment is, for example, batteries, electric motors, camera modules, communication modules, and the like.

The fixed wing 2 is symmetrical to the left and right based on the vertical center line (a) of the main body 1 in the main body 1 and can be formed wide in the left or right direction or rearward. That is, the shape of the stator blade 2 may be provided in any shape as long as it is a shape symmetrical with respect to the vertical center line a of the main body 1, which shows various examples from FIGS. 2 and 6 to 10 Did.

The fixed wing 2 may have a cross-sectional shape of an airfoil shape, and may have a plate shape having a constant thickness.

In addition, the fixed wing 2 may be a design factor in which the area ratio of the gyro unit to the fixed wing area is important. Here, the area of the gyro unit may be an area obtained by combining the circumferential surface area of the flywheel 26 and the surface area of the vane 28. In the fixed wing 2, the larger the area of the gyro unit with respect to the fixed wing area, the greater the gyro effect.

In addition, the fixed wing 2, as shown in Figure 1, may have an upper half angle (d). When the drone's posture is tilted, the upper half angle d may increase the amount of air reaching the fixed wing of the descending side to increase lift, and decrease the amount of lift by decreasing the amount of air reaching the fixed wing of the climbed side. That is, by forming the upper half (d) on the fixed wing (2) it is possible to quickly and easily restore the drone's flight posture to a stable posture.

The gyro rotor unit 20 may be symmetrical to the left and right of the fixed center 2 based on the vertical center line a, or may be disposed on the vertical center line a.

The drone according to the embodiment of the present invention configured as described above can implement a Magnus effect by the gyro rotor unit 20 to reinforce lift, and restore a posture by the gyro effect.

Hereinafter, the gyro rotor unit 20 will be described with reference to FIGS. 3 to 5. 3 is a view for explaining the configuration of a gyro rotor unit in a drone according to an embodiment of the present invention. 4 is a view for explaining the configuration of another example gyro rotor unit in a drone according to an embodiment of the present invention. 5 is a view for explaining the installation configuration of a gyro rotor unit in a drone according to an embodiment of the present invention.

The gyro rotor unit 20 may include a bracket 22, a shaft axle 24, a flywheel 26, and a vane 28.

The bracket 22 may be installed on the fixed wing (2). The bracket 22 may be installed on the upper side of the fixed wing 2 according to the shape of the vehicle or may be integrally formed in front of the main body 1.

If the bracket 22 is installed on the upper side of the fixed wing 2, as shown in FIG. 5, it can be installed obliquely toward the front upward direction toward the traveling direction of the vehicle. The angle at which the bracket 22 is inclined forward can form an angle of approximately 45 to 50 degrees from the horizontal reference line, whereby the natural wind flow avoids interference with the bracket 22 as much as possible, while the air flow of the natural wind is with the flywheel 26. It can interact with the vane (28).

On the other hand, the vane 28 of the gyro rotor unit 20 installed to face the front side can be fixed at a specific angle, through which, the vane 28 and the fixed wing 2 can achieve a bilobal shape (not shown). have.

The shaft axle 24 may be installed such that the horizontal reference line b and the rotation axis c of the main body 1 are parallel to the bracket 22. In other words, the shaft axle 24 may be installed such that the vertical center line (a) and the rotation axis (c) form a right angle.

Meanwhile, FIGS. 3 and 4 show that the bracket 22 is positioned at the end of the shaft axle 24, but the present invention is not limited thereto, and the bracket 22 is vane 28-first bracket 22. -Flywheel 26-second bracket 22-vane 28 can be configured in order (not shown).

By limiting the arrangement direction of the shaft axle 24, when the lift force is reinforced according to the rotation of the flywheel 26, the lift force can act in a direction in which the main body 1 maintains a posture and rises.

In addition, by limiting the arrangement direction of the shaft axle 24, when the gyro effect is realized according to the rotation of the flywheel 26, a restoring force is generated by the gyro effect and the restoring force acts in a direction to restore the body 1 posture. Can.

The flywheel 26 may be provided in the form of a disc, may be installed on the shaft axle 24, and may have rotational inertia by applying kinetic energy to the mass.

In addition, the rotation of the flywheel 26 and the vane 28 can realize lift in the vertical direction with respect to the traveling direction of the vehicle, and it is expected to enhance the gyro effect according to the high-speed rotation of the flywheel 26.

The vane 28 may be installed on the shaft axle 24 and rotated under the influence of the surrounding airflow to rotate the flywheel 26.

When the vane 28 rotates at a high speed, a Magnus effect is realized, and thus lift force can be generated.

On the other hand, the vane 28 can be fixed so that the cross-sectional shape maintains a horizontal posture according to the user's will, or can remove the load so that the vane 28 can rotate freely.

This may be a mutually switchable biplane having both functions of a gyro rotor unit 20 applied aircraft and a biplane, so that the gyro rotor unit 20 to be described later is accommodated in a fixed wing, so that the aircraft enters the high altitude stability zone. After that, it is possible to implement a flight like a conventional biplane in order to increase the flight speed.

The rotation control of the vane 28 can be implemented by interrupting the shaft axle 24, and more specifically, a braking device can be installed to suppress or cancel the rotation of the shaft axle 24. The braking device uses known technology such as friction and adhesion pressure, and detailed description is omitted.

The drone according to the embodiment of the present invention made as described above, rotates the gyro rotor unit 20 during a cruising flight to implement a Magnus effect, thereby enhancing lift and thus increasing flight time.

In addition, the drone according to an embodiment of the present invention can rotate the vane by an external air flow, thereby realizing a gyro effect by rotating the flywheel to restore the attitude of the air vehicle.

On the other hand, the drone according to an embodiment of the present invention, as shown in FIG. 3, the flywheel 26 may be provided in plural, whereby the Magnus effect and the gyro effect are more reliably implemented to increase the lift effect and Posture restoration effect can be increased.

A vane 28 may be disposed between any one flywheel 26 and the other flywheel 26, whereby a plurality of vanes 28 are provided to realize the Magnus effect and the gyro effect more reliably, thereby restoring the posture. Can increase.

The vanes 28 and flywheel 26 need to be provided in suitable sizes, and aspect ratio can be an important design factor. The circumferential surface area of the flywheel 26 may be 1.4 times or more with respect to the area of the vane 28, and in this case, the flywheel 26 may rotate in a normal rotational direction at an appropriate rotational speed.

On the other hand, if the circumferential surface area of the flywheel 26 is provided to be less than 1.4 times the area of the vane 28, the flywheel 26 is likely to rotate in reverse, and in this case, the drone may fall due to reverse lifting force. As described above, it is important that the circumferential surface area of the flywheel 26 is designed to be 1.4 times or more with respect to the area of the vane 28.

The vane 28, as shown in FIG. 4, may be formed such that a portion of the outer edge is inclined to form a cone when the vane 28 is rotated to form a rotating body.

Thus, when the gyro rotor unit 20 is placed on the vertical center line a of the main body 1 on the drone and is installed higher than the main body 1 or the fixed wing 2, the vane 28 is the main body 1 or the fixed wing ( 2) By minimizing interference and preventing abnormal air flow due to rotation of the vane 28, it can contribute to maintaining a stable flight posture of the vehicle.

In addition, the vane 28 may be provided in a symmetrical shape such as an oval shape, a rhombus shape, a rectangle, and the like, and may be concavely formed in a bucket shape on one side so as to be sensitive to the influence of airflow, and the bucket shape is rotated. It is formed symmetrically and can rotate in one direction.

However, the vane 28 is not limited to a bucket shape, and can be formed into a flat plate shape, and in this case, an initial rotation starting device may be required. The plate-shaped vane 28 may be required for conversion to the above-described biplane.

On the other hand, one flywheel 26 may have a larger diameter than the other flywheel 26, or may have a large circumferential surface area w.

The Magnus effect is that when an object moves while rotating, a force acts in a direction perpendicular to the direction of movement. The larger the area that interacts with the airflow, the larger the pressure difference may be, and the larger the pressure difference, the greater the lift. .

On the other hand, the gyro rotor unit 20 can be operated by power, which will be described with reference to FIG. 5. 5 is a view for explaining the installation configuration of the gyro rotor unit 20 in a drone according to an embodiment of the present invention.

A first magnetic 52 may be disposed on the flywheel 26. The first magnetic 52 may be arranged in a circular arrangement close to the surface of the flywheel 26, as shown in FIG. 5, and may be arranged with a constant polarity. The polarity is one in which the N pole and the S pole are aligned in one direction.

A magnetic driver 50 may be installed on the fixed wing 2, and the magnetic driver 50 may rotate by a rotor by an electric motor. The electric motor may receive electric energy from a battery mounted on the main body 1 and may be operated under the control of the drone control unit 10.

The second magnet 54 may be arranged in a circular arrangement on the rotor of the magnetic driver 50 as shown in FIG. 5. The polarity of the second magnetic 54 may be uniformly aligned, and the polarity is arranged such that the N pole and the S pole have one direction.

Thus, when the magnetic driver 50 is operated, the second magnetic 54 rotates, and the second magnetic 54 exerts a magnetic force effect on the first magnetic 52 of the flywheel 26. The flywheel 26 can be rotated.

That is, the flywheel 26 may be forcibly rotated according to the user's control will, and may be forcibly rotated under the control of the drone control unit 10.

Therefore, the drone according to the embodiment of the present invention can reinforce the lift by forcibly rotating the flywheel 26 at a time when the Magnus effect is required.

In addition, by not installing a separate drive motor for rotating the flywheel 26 or the vane 28 outside the main body 1, the propulsion force of the vehicle is weakened by not adding an air resistance generating factor to the propulsion of the vehicle. Can be prevented.

On the other hand, the drone according to the embodiment of the present invention may be configured by including the drone control unit 10 on the vertical center line (a) in the main body (1), and the center of gravity is biased to either side. You can balance without hitting and contribute to stable flight.

The drone control unit 10 may be equipped with a control unit, a battery, an electric motor, camera equipment, communication equipment, and the like, and a propeller may be installed outside the main body 1. The camera equipment can take images, and the communication equipment can communicate with the drone operator's remote controller, thereby allowing the drone operator to remotely control the drone.

On the other hand, the drone control unit 10 may provide the magnetic driver 50 with priority over other electronic devices when the remaining battery detection value is less than or equal to a reference value.

The drone control unit 10 may continuously monitor the state of the battery to detect the remaining battery capacity, and determine whether the detected value reaches or falls below a reference value.

That is, the drone according to the embodiment of the present invention can force the flywheel 26 to be rotated at high speed when the battery power is determined to be lower than or equal to the set level, thereby forcibly implementing the gyro effect and the Magnus effect, thereby preventing the drone from being controlled. It can be prevented from falling suddenly when not in use.

More specifically, when the battery level is low, the drone may continue to be difficult to fly, the drone may not reach the target landing point, and the drone may even face an emergency that cannot be controlled normally. When such an emergency occurs, the drone control unit 10 may operate the magnetic driver 50 to reinforce the lift force as described above, thereby delaying the drone from rapidly falling when the drone cannot be normally controlled. .

Therefore, the drone according to the embodiment of the present invention can minimize the personal injury or property damage that may be caused by a drone crash by slowing down the drone's fall rate.

The drone according to an embodiment of the present invention can be implemented in various forms, which will be described with reference to FIGS. 2 and 6 to 10. 6 to 10 are views for explaining a drone according to another embodiment of the present invention.

2 is an example in which the drone is implemented in a glider type, and the drone shown in FIG. 2 may have a steering wing 3 at a tail portion. The gyro rotor unit 20 may be disposed at positions symmetrical to both sides with respect to the vertical center line a.

6 is an example in which the drone has no body 1 or minimizes the size of the body 1 in a board wing form. The gyro rotor unit 20 may be disposed at positions symmetrical to both sides with respect to the vertical center line a. The drone control unit 10 may be disposed on the vertical center line (a).

7 is an example in which the drone is implemented in the form of a triangular wing. The gyro rotor unit 20 may be disposed at positions symmetrical to both sides with respect to the vertical center line a. The drone control unit 10 may be disposed on the vertical center line (a).

8 is an example in which the drone is implemented in the form of a shell wing. The gyro rotor unit 20 may be disposed on the vertical center line (a). The drone control unit 10 may be disposed on the vertical center line (a).

9A is an example in which the drone is implemented in the form of an apron wing. The gyro rotor unit 20 may be disposed on the vertical center line (a). The drone control unit 10 may be disposed on the vertical center line (a). Also, the drone shown in FIG. 9A may further include a tilt rotor 30. Tilt rotor 30 may be operated to take off and land the drone in the vertical direction. In addition, the tilt rotor 30 can safely implement dangerous tilt rotor operation by the gyro effect of the gyro rotor unit 20.

FIG. 9B is an example in which the drone is implemented in a circle wing form. As a modification of FIG. 9A, the main body 1 or the fixed wing 2 may be provided in a circular shape.

9C is an example in which the drone is implemented in a heart wing form, and as a modification of FIG. 9A, the main body 1 or the fixed wing 2 may be provided in a heart shape.

10 is an example in which the drone is carried out in the form of a helium balloon. In addition, the helium balloon 40 may be disposed at a symmetrical position with respect to the vertical center line (a), and the drone control unit 10 and the gyro rotor unit 20 may be arranged over the vertical center line (a), and the main body A steering wheel 3 may be provided at the rear side of (1), and a wind power generator 42 may be installed under the helium balloon 40.

The steering wheel 3 of the drone shown in FIG. 10 can be used as a wind vane or when changing the direction of the drone, the helium balloon 40 allows floating at high altitude, and the wind generator 42 is wind power Can produce electricity.

In the embodiment of the present invention, an example of using helium in a helium balloon is shown, but is not limited thereto, and a gas having a specific gravity smaller than that in the atmosphere may be used.

The drone shown in FIG. 10 can continuously recharge the electricity consumed by the drone by producing electricity with the wind generator 42, thereby allowing the drone to remain at high altitude for a long time and perform a predetermined purpose or function.

A given purpose or a given function can be used, for example, to perform climate observation, security, forest fire monitoring, logistics, pesticide spraying, rescue activities, reconnaissance, remote communication communication, internet signal relay, and the like.

The drone shown in FIG. 10 can take off as power, enter power at high altitude, turn off power, and operate with only sunlight and wind energy to generate and accumulate electric energy, and can have an on/off sensor system in the drone, at night or When there is no wind, the high altitude flight can be continued without landing without using the accumulated energy described above. Drones according to embodiments of the present invention may be evolved in the form of a high altitude (High Altitude) wind power airplane.

The altitude may be a stratosphere, the height may range from approximately 14 km to 18.5 km, and a height of 18 km or more may be a height that can fly according to the operator's plan without the instructions of the ground controller and a predetermined route. The stratosphere has a very low air density and temperature, making it difficult for ordinary aircraft to fly, but because it has no clouds, it can be advantageous for long-term flight by utilizing sunlight as a power source.

Referring to the drone shown in FIG. 11, the drone according to the embodiment of the present invention may be configured to include an upper half-angle extended fixed wing 4. The extended stator blade 4 may have a horizontal area (width) equal to the length of the shaft axle 24 or similar within a range of about 5% and may have a predetermined area. The extended stator blade 4 may be formed in a form that extends to the rear just behind the stator blade 2 in which the gyro rotor unit 20 is fixed (in the opposite direction to the moving direction of the vehicle). The extended fixed wing 4 can contribute to a drone or a vehicle to realize a more stable flight effect.

On the other hand, the drone according to the embodiment of the present invention, the gyro rotor unit 20 may be designed and modified to be accommodated in the fixed wing (2). More specifically, a storage space is formed in the fixed wing 2, and the gyro rotor unit 20 can appear and go out of the storage space. The gyro rotor unit 20 may operate linearly using a device such as an LM guide, or folded or unfolded using a white paper device.

The power to bring the gyro rotor unit 20 up and down can be operated by a known actuator such as a linear motor or cylinder.

That is, the drone according to the embodiment of the present invention, while cruising, the gyro rotor unit 20 can operate in a hidden state without protruding outside the main body 1 or the fixed wing 2, thereby reducing air resistance By doing this, you can increase the speed of your drone's flight.

Thereafter, when the drone enters the desired high altitude stabilization zone, the gyro rotor unit 20 can be accommodated inside the main body 1 or the fixed wing 2 to reduce air resistance, thereby increasing the flying speed of the drone.

On the other hand, the drone according to the embodiment of the present invention, if equipped with gyro rotor units 20 on both sides with respect to the vertical center line (a), it is possible to switch the flight direction of the aircraft while suppressing the rotation of the shaft axle 24 have.

For example, if the rotational motion of one shaft axle 24 is braked and the other shaft axle 24 is freely rotated, a resistance is generated on the side where the rotation of the shaft axle 24 is braked. The flight direction of can be switched.

That is, the drone according to the embodiment of the present invention can switch the flight direction of the drone even if the steering wheel 3 previously equipped in the vehicle is not used or the steering wheel 3 is not used.

On the other hand, a conventional vehicle using a solar cell to charge and fly may have a narrow aspect and a large aspect ratio (Aspect ratio), ultra-light weight, and robust wing production may be a technical problem. According to the drone, it is possible to provide the fixed wing 2 with a long wing in the form of a flat plate rather than an airfoil, and by installing the gyro rotor unit 20 on the long wing, it is possible to simplify the construction of the drone, and is lightweight and durable It has the advantage of being able to be fabricated.

On the other hand, the drone according to the embodiment of the present invention, by installing a solar panel on the surface of the fixed wing (2) can fly high with only solar energy, thereby continuing to take strong wind energy at high altitude, It can be used as a public radio base station to replace high-altitude wind-powered aircraft or satellites.

On the other hand, in the drone according to an embodiment of the present invention, a drone control unit 10 may be provided with a seat for a person to board, and in this case, the drone can directly control the drone. For example, the present invention can be applied to a Personal Air Vehicle (PAV).

In addition, the drone according to the present invention can be applied to a ship that can move at high speed by floating about 1 m above the sea.

Other embodiments of the present invention are considered. 12 is a view for explaining the concept of a drone for electricity generation according to another embodiment of the present invention.

A flywheel 26 is disposed to be rotatable on the fixed wing 2, and a power generation unit 43 may be connected to one side of the shaft axle 24 of the flywheel 26, and the power generation unit 43 may be provided with the fixed wing (2) can be installed. The power generation unit 43 may convert the rotational energy of the flywheel 26 into electrical energy. A power transmission connection part 60 may be connected to the power generation part 43. The transmission connection unit 60 may transmit electric energy to the ground or the inside of the drone.

The transmission connection unit 60 may be connected to equipment on the ground through a cable to supply power, or may be used to charge through a power storage device provided in the drone.

Through this, the present invention can stably fly over high altitude while supplying the power generated through rotation of the flywheel 66 to the ground, thereby generating a greater amount of energy than a wind turbine installed on the ground.

Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art to which the present invention pertains understand that the present invention may be implemented in other specific forms without changing its technical spirit or essential features. Will be able to.

Therefore, the embodiments described above are illustrative in all respects and should be understood as non-limiting, and the scope of the present invention is indicated by the following claims, and is derived from the meaning and scope of the claims and equivalent concepts thereof. It is to be understood that all altered or modified forms are included within the scope of the present invention.

The drone according to an embodiment of the present invention can be used to prevent the drone from suddenly falling into an uncontrolled state or to restore the flying attitude of the drone.

Claims

A fixed wing 2 symmetrically left and right with respect to the vertical center line a and formed wide in the left or right direction or rearward; And

Including the; gyro rotor unit 20 symmetrically left and right relative to the vertical center line (a) in the fixed wing (2) or disposed on the vertical center line (a);

The gyro rotor unit 20,

A bracket 22 installed on the fixed wing 2;

A shaft axle 24 installed in the bracket 22 such that the vertical center line (a) and the rotation axis (c) form a right angle;

A flywheel 26 installed on the shaft axle 24 and implementing lift in a vertical direction with respect to the traveling direction of the vehicle according to rotation, and restoring to a horizontal posture; And

A vane (28) installed on the shaft axle (24) to rotate the flywheel (26) by rotating under the influence of ambient air flow;

Drone containing.
According to claim 1,

The flywheel 26 is provided in plural, and a vane 28 is disposed between one flywheel 26 and the other flywheel 26.
According to claim 2,

The vane 28, a part of the outer edge is formed to be inclined so that the vane 28 is rotated to form a cone shape when a rotating body is implemented.
According to claim 2,

Drone containing; any one of the flywheel 26 is formed to have a larger diameter than the other flywheel 26.
According to claim 2,

A drone comprising a; one flywheel 26 is formed with a larger circumferential surface area (w) than the other flywheel 26.
The method according to any one of claims 1 to 5,

A first magnet 52 having polarities constantly arranged in a circular arrangement on the flywheel 26;

A magnetic driver 50 installed on the fixed wing 2 to rotate the rotor by an electric motor; And

The magnetic driver 50 has a polarity arranged in a circular arrangement in a uniform arrangement. When the magnetic driver 50 is operated, a magnetic force is applied to the first magnetic 52 so that the flywheel 26 rotates. A second magnetic 54 to be made;

Drone containing.
The method of claim 6,

Included in the drone control unit 10 disposed on the vertical center line (a) in the body (1),

The drone control unit 10,

Providing the electric driver of the battery to the magnetic driver 50 in preference to other electronic devices when the remaining battery detection value is equal to or less than a reference value;

Drone containing.
According to claim 1,

The horizontal fixed length (width) is the same as the length of the shaft axle 24 or is formed within a range of about 5%, and the extended fixed wing 4 is disposed at the rear of the portion where the gyro rotor unit 20 is installed in the fixed wing 2 );

Drone containing.
According to claim 1,

Drones in which vanes 28 are disposed on both sides of the flywheel 26, respectively.