WO2018097359A1

WO2018097359A1 - Turbojet drone

Info

Publication number: WO2018097359A1
Application number: PCT/KR2016/013682
Authority: WO
Inventors: 김기태
Original assignee: 김기태
Priority date: 2016-11-25
Filing date: 2016-11-25
Publication date: 2018-05-31
Also published as: KR101775847B1

Abstract

The present technique relates to a drone and, more specifically, to a drone which flies by jetting compressed gas. According to one embodiment, a turbojet drone is disclosed. The turbojet drone comprises an engine part for intaking and discharging external gas. A propulsion part, in which the gas discharged from the engine part is compressed and discharged to the outside, is included. A turbo propulsion part, in which the gas discharged from the engine part is compressed and selectively discharged to the outside, is included. The turbojet drone disclosed in the present specification receives additional propulsion power, different from that of the propulsion part, provided by the turbo propulsion part, thereby enabling flight power to be improved. In addition, the size of a turbo discharge part is adjusted by a turbo adjustment unit such that the strength of the additional propulsion power is controlled, thereby controlling the direction of the turbojet drone. In addition, a much stronger air can be discharged by the engine part comprising a turbojet fan in which one or more fans overlap, thereby further improving flight power.

Description

Turbo jet drone

The present technology relates to a drone, and more particularly, to a drone that is injected by jetting the compressor body.

Commonly used drones are classified into wing type to give lift through propeller and jet type to give lift through strong wind.

Looking at the wing type drone, a main body, a plurality of arms provided on the circumference of the main body, a rotor provided on the arm and driven by a drive device is provided.

The drone of the wing type is to be flying by the lift generated by the rotor, it is disclosed in Republic of Korea Patent No. 10-1654799 (announced on September 06, 2016).

However, the wing type drone has a problem in that a plurality of rotors (wings) are easily broken from external impact.

Looking at the jet type drone, there is disclosed a drone composed of a main body, an inlet means, a wind guide and a connecting duct. In more detail, the inlet means is accommodated in the main body is configured to introduce the wind. One or more wind guides are spaced apart from the main body. The connection duct allows the wind flowing from the inlet means to move to the wind guide.

The jet type drone is configured to give a lift force for the wind guide portion to fly the main body by the wind discharged by the connecting duct, it is disclosed in Korean Patent No. 10-1607816 (announced on March 31, 2016) have.

However, the jet drone has a problem that it is difficult to control the direction of movement of the drone as the wind is distributed by one inflow means. In addition, the jet drone sucks and discharges the outside air by a conventional fan, which causes a problem of low output.

The technology disclosed herein is derived to solve the above problems of the prior art. The technique disclosed herein provides a wingless turbo jet drone with improved flight output for flight of the drone.

In one embodiment, a turbo jet drone is disclosed. The turbo jet drone includes an engine unit that sucks and discharges external gas. The gas discharged from the engine unit is compressed to include a propulsion unit discharged to the outside. The gas discharged from the engine unit includes a turbo propulsion unit is compressed and selectively discharged to the outside.

The propulsion unit includes a propulsion compression unit in which gas discharged from the engine unit is compressed. And a propulsion discharge portion communicating with the outside of the compression portion.

The turbo propulsion unit includes a turbo compression unit in which gas discharged from the engine unit is compressed. The turbo compression unit includes a turbo discharge unit in communication with the outside. It includes a turbo control unit for adjusting the size of the turbo discharge unit.

The turbo control unit may include a discharge cover part blocking the turbo discharge part and a cover moving part moving the discharge cover part.

The engine unit includes a turbojet fan in which one or more fans are overlapped.

The turbo jet drones disclosed herein may be provided with additional propulsion force other than the propulsion portion by the turbo propulsion portion to improve flight power.

In addition, the size of the turbo discharge unit is adjusted by the turbo control unit to control the strength of the additional propulsion force, thereby controlling the direction of the turbo jet drone.

In addition, the engine unit including the turbojet fan in which one or more fans are superimposed can discharge more powerful air, and thus the flight power can be further improved.

The foregoing provides only optional concepts in a simplified form for the details that follow. This disclosure is not intended to limit the main or essential features of the claims or to limit the scope of the claims.

1 illustrates a turbo jet drone according to an exemplary embodiment.

2 is a diagram illustrating a turbo jet drone according to another embodiment.

3 is a diagram illustrating a turbo jet drone according to another embodiment.

Hereinafter, exemplary embodiments disclosed herein will be described in detail with reference to the accompanying drawings. Unless otherwise indicated in the text, like reference numerals in the drawings indicate like elements. The illustrative embodiments described above in the detailed description, drawings, and claims are not meant to be limiting, other embodiments may be utilized, and other changes may be made without departing from the spirit or scope of the technology disclosed herein. Those skilled in the art may arrange, configure, combine, and designate the components of the present disclosure, that is, the components generally described herein and described in the figures, in a variety of different configurations, all of which are expressly devised and It will be readily understood that they form part. In order to clearly express various layers (or layers), regions, and shapes in the drawings, the width, length, thickness, or shape of the components may be exaggerated.

When one component is referred to as "placement" in another component, it may include a case in which one component is directly disposed in the other component, as well as a case in which additional components are interposed therebetween.

When one component is referred to as "connecting" to another component, it may include a case in which the one component is directly connected to the other component, as well as a case in which additional components are interposed therebetween.

When one component is referred to as "forming" in another component, it may include a case in which one component is directly formed in the other component, as well as a case in which additional components are interposed therebetween.

When one component is referred to as being "coupled" to another component, it may include a case in which the one component is directly coupled to the other component, as well as a case in which additional components are interposed therebetween.

Description of the disclosed technology is only an embodiment for structural or functional description, the scope of the disclosed technology should not be construed as limited by the embodiments described in the text. That is, the embodiments may be variously modified and may have various forms, and thus, the scope of the disclosed technology should be understood to include equivalents capable of realizing the technical idea.

Singular expressions should be understood to include plural expressions unless the context clearly indicates otherwise, and the terms “comprises” or “haves” include such features, numbers, steps, operations, components, and parts. Or combinations thereof, it is to be understood that they do not preclude the existence or addition of one or more other features or numbers, steps, actions, components, parts or combinations thereof.

Unless otherwise defined, all terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the disclosed technology belongs. The terms defined in the commonly used dictionaries should be interpreted to coincide with the meanings in the context of the related art, and should not be interpreted as having ideal or overly formal meanings unless explicitly defined in the present application.

1 illustrates a turbo jet drone according to an exemplary embodiment. 2 is a diagram illustrating a turbo jet drone according to another embodiment. 3 is a diagram illustrating a turbo jet drone according to another embodiment.

Referring to the drawings, the turbo jet drone disclosed in the present specification largely includes an engine unit 100, the propulsion unit 200 and the turbo propulsion unit 300. In some other embodiments, the turbo jet drone may optionally further include a coanda propulsion unit 400. The turbo jet drone disclosed in the present specification sucks and discharges outside air (gas) through the engine unit 100. The discharged air is compressed by the propulsion unit 200 to be strongly discharged toward the ground, thereby generating a propulsion force that can fly. The turbo propulsion unit 300 is compressed by the air discharged through the engine unit 100 is discharged to the outside, to generate additional propulsion force. And thrust force is increased through the coanda propulsion unit (400). That is, the turbo jet drone disclosed in the present disclosure may increase the direction and basic propulsion force by the additional propulsion force of the turbo propulsion unit 300 while flying at the basic propulsion force by the propulsion unit 200.

The engine unit 100 may be configured to suck and discharge external gas (air) by a fan rotated by a conventional internal combustion engine or an electric motor.

According to an embodiment of the present disclosure, the engine unit 100 may include a fan rotated by an electric motor, and the fan may be configured to suck the outside air (gas) from the upper portion and discharge the lower portion. The engine unit 100 may provide a driving force necessary for the flight of the turbo jet drone.

According to another embodiment, the engine unit 100 may include a turbojet fan 110 in which one or more fans are overlapped. The turbojet fan 110 may suck at least the outside air to discharge the compressed air to improve the driving force. The turbojet fan 110 may be disposed inside the tubular body and the tubular body, and may include a rotating shaft that is rotated by the driving device. At least one fan is disposed on the rotating shaft, and may be disposed to be closer to the inner surface of the tube. In the turbojet fan 110, air sucked into the tubular body is moved to the other side along the tubular body by the fan. The moving air is compressed and discharged as the inner surface of the fan and pipe becomes narrower. That is, the turbojet fan 110 may suck the outside air and discharge the compressed air to improve the propulsive force of the turbo jet drone.

The engine unit 100 including the turbojet fan 110 may be in accordance with the compression structure of a conventional jet engine excluding the combustion chamber. On the other hand, the engine unit 100 may implement the turbo jet drone disclosed herein even if it is replaced by a conventional compression device capable of compressing air by a piston operated by the internal combustion engine.

The propulsion unit 200 may be configured such that the gas (air) discharged from the engine unit 100 is compressed and discharged to the outside. The propulsion unit 200 generates the propulsion force of the turbo jet drone by discharging at least the air supplied from the engine unit 100 to the lower portion of the turbo jet drone.

According to one embodiment, the driving unit 200 is connected to the lower engine portion 100. The propulsion unit 200 includes a propulsion compression unit 210 in which gas discharged from the engine unit 100 is compressed. Propulsion compression unit 210 may be configured to include a propulsion discharge unit 220 in communication with the outside. The propulsion unit 200 discharges air compressed by the propulsion compression unit 210 through the propulsion discharge unit 220 to generate a propulsion force of the turbo jet drone. On the other hand, the propulsion unit 200 may implement a turbo jet drone disclosed herein even when connected to the engine unit 100.

In some other embodiments, the turbo jet drone may optionally further include a propulsion control unit 230. Propulsion control unit 230 is disposed corresponding to the propulsion discharge unit 220. The propulsion control unit 230 may control the propulsion force of the turbo jet drone by adjusting the amount of air discharged by adjusting the size of the propulsion discharge unit 220.

For example, the propulsion compression unit 210, the propulsion discharge unit 220 and the propulsion control unit 230 will be described in more detail, the propulsion compression unit 210 may be configured as a cylinder in which the space is compressed air is formed therein. have. The upper surface of the barrel may be configured to include a hole formed so that the air discharged from the engine unit 100 flows into the barrel. The propulsion compression unit 210 is connected to the engine unit 100. That is, the propulsion compression unit 210 is compressed by entering the outside air discharged by the engine unit 100 into the inside.

The propulsion discharge part 220 may include four holes spaced apart from each other on the lower surface of the propulsion compression part 210. Propulsion discharge unit 220 is preferably formed to face the ground. The propulsion discharge part 220 induces the compressed air from the propulsion compression part 210 to be discharged downward. The size of the propulsion discharge unit 220 is preferably formed to a size that can generate the propulsion force of the turbo jet drone while the air introduced by the engine unit 100 is sufficiently compressed in the propulsion compression unit 210.

On the other hand, the propulsion compression unit 210 may be subjected to the turbo jet drone disclosed herein even if only one propulsion discharge unit 220 is implemented. However, when it is desired to control the flight direction of the turbo jet drone through the propulsion discharge unit 220 it will be preferable to form at least two.

The propulsion control part 230 may include a discharge cover part 331 blocking the propulsion discharge part 220 and a cover moving part 332 for moving the discharge cover part 331. The propulsion control unit 230 is disposed corresponding to each of the propulsion discharge unit 220, the same operation is collectively. The propulsion control unit 230 may move the position of the discharge cover part 331 by the cover moving part 332 to cover the entire propulsion discharge unit 220, or to adjust the size of the opening and propulsion discharge unit 220. . That is, the propulsion force is generated when the propulsion discharge part 220 is opened by the propulsion control part 230. On the contrary, when the propulsion discharge part 220 is covered by the propulsion control part 230, the propulsion force is not generated. Furthermore, if the size of the propulsion discharge unit 220 is adjusted by the propulsion control unit 230, the amount of air discharged to the propulsion discharge unit 220 is adjusted to adjust the propulsion force according to Bernoulli's principle. In addition, when the propulsion control unit 230 is operated individually, it is possible to control the flight direction of the turbo jet drone.

For example, when the propulsion control unit 230 is described in more detail, the discharge cover part 331 is disposed to be freely moved inside the turbo compression unit 310, it may be configured as a plate formed larger than the turbo discharge unit 320. have. The cover moving part 332 may be configured as a cylinder which is disposed inside the turbo compression part 310 to move the cover moving part 332 to be dropped or blocked from the turbo discharge part 320. On the other hand, the propulsion control unit 230 may be configured to be driven by a motor and a rack gear structure in place of the cylinder.

The turbo propulsion unit 300 may be configured such that the gas discharged from the engine unit 100 is compressed and selectively discharged to the outside. The turbo propulsion unit 300 is at least a gas discharged from the engine unit 100 is compressed to generate additional propulsion force independent of the propulsion unit 200.

According to an embodiment, the turbo propulsion unit 300 is connected to the propulsion unit 200. The turbo propulsion unit 300 includes a turbo compression unit 310 in which air discharged from the engine unit 100 is compressed. And the turbo compression unit 310 includes a turbo discharge unit 320 in communication with the outside. In addition, it includes a turbo adjustment unit 330 for adjusting the size of the turbo discharge unit 320. In the turbo propulsion unit 300, at least air discharged from the engine unit 100 flows into the turbo compression unit 310 through the propulsion unit 200 and is compressed. In addition, the compressed air is discharged to the outside through the turbo discharge unit 320 to generate additional propulsion force, but when the entire turbo discharge unit 320 is closed by the turbo control unit 330, additional propulsion force may not be generated. have.

For example, the turbo compression unit 310, the turbo discharge unit 320 and the turbo control unit 330 will be described in more detail, the turbo compression unit 310 is configured in the same way as the propulsion compression unit 210, the compression compression It may be of a smaller size than the portion 210. The turbo discharge unit 320 may also be configured in the same manner as the propulsion discharge unit 220 and may operate in the same manner.

The turbo control unit 330 may include a discharge cover part 331 blocking the turbo discharge part 320 and a cover moving part 332 for moving the discharge cover part 331. The turbo control unit 330 may be moved by the cover cover 331, the cover moving part 332 is moved to cover the entire turbo discharge unit 320, or open. That is, when the turbo discharge unit 320 is opened by the turbo control unit 330, an additional propulsion force is generated. On the contrary, if the turbo discharge unit 320 is covered by the turbo control unit 330, no additional driving force is generated.

Further, the turbo adjustment unit 330 may be further disposed in the hole formed in the turbo compression unit 310 through which air is introduced through the propulsion compression unit 210. When the turbo adjuster 330 is compressed from the air pressure discharged from the engine unit 100 to a maximum value capable of compressing air in the turbo compressor 310, it operates to block the inflow of air. The turbo adjustment unit 330 may prevent the air discharged from the engine unit 100 from flowing into the turbo compression unit 310, thereby preventing the driving force from being weakened. In addition, the turbo adjusting unit 330 may prevent the air compressed in the turbo compression unit 310 from being lost to the propulsion compression unit 210 to store the compressed air for a long time. The compressed air stored for a long time may be discharged to the outside when necessary according to the turbo control unit 330 installed in the turbo discharge unit 320 to generate additional propulsion force.

For example, when the turbo control unit 330 is described in more detail, the discharge cover part 331 is disposed to be freely moved inside the turbo compression unit 310, but may be configured as a plate formed larger than the turbo discharge unit 320. have. The cover moving part 332 may be configured as a cylinder which is disposed inside the turbo compression part 310 to move the cover moving part 332 to be dropped or blocked from the turbo discharge part 320. On the other hand, the turbo adjustment unit 330 further disposed in the hole formed in the turbo compression unit 310 introduced through the propulsion compression unit 210 may be configured as a conventional check valve. On the other hand, the propulsion control unit 230 may be configured to be driven by a motor and a rack gear structure in place of the cylinder.

Coanda propulsion unit 400 may be of a structure that is applied to the principle of the Bernoulli and the Coanda effect of the air flowing in ('Dyson's wingless fan). The coanda propulsion unit 400 may increase a force (pulling force) from which the air introduced is discharged.

According to an embodiment, the coanda propulsion unit 400 includes a connection passage communicating with the propulsion discharge unit 220. One side of the connection passage includes a coanda supply unit for supplying air passing through the connection passage. And a coanda discharge unit configured to discharge air supplied from the coanda supply unit to the outside. Coanda propulsion unit 400 is the air discharged from the propulsion compression unit 210 is supplied to the coanda supply unit through the connection passage, the supplied air is discharged to the coanda discharge unit to generate a driving force.

For example, when the connection passage, the coanda supply unit and the coanda discharger are described in more detail, the coanda supply unit may be formed in a ring shape, and a space in which air may move may be formed. It is desirable that the length of the ring shape be shaped so that the Coanda effect can be achieved. The shape of the inner surface and the outer surface of the ring shape may also be formed to facilitate the Coanda effect as the outside air flows into the inside.

The coanda discharge portion is formed into a ring-shaped hole along the inner face of the coanda supply portion. The ring-shaped hole is formed to face the inner surface of the coanda supply portion.

The connection passage may be composed of conventional piping. It is connected to the other side of the coanda supply portion, the other side is connected to the propulsion compression unit (210).

On the other hand, the connecting passage is formed in a 'Y' shape, one side is connected to the propulsion compression unit 210, the other side is connected to the turbo compression unit 310, the other side may be connected to the coanda supply unit. The connecting passage guides the air introduced from the propulsion compression unit 210 to be moved to the coanda supply unit, and guides the air introduced from the turbo compression unit 310 to the coanda supply unit. That is, the air flowing from the propulsion unit 200 and the air flowing from the turbo propulsion unit 300 may overlap to increase the driving force generated by the coanda propulsion unit 400.

From the above, various embodiments of the present disclosure have been described for purposes of illustration, and it will be understood that various modifications are possible without departing from the scope and spirit of the present disclosure. And the various embodiments disclosed are not intended to limit the present disclosure, the true spirit and scope will be presented from the following claims.

Claims

In the drone,

An engine unit for sucking and discharging external gas;

A propulsion unit compressed with the gas discharged from the engine unit and discharged to the outside; And

And a turbo propulsion unit configured to discharge the gas discharged from the engine unit and selectively discharge the gas to the outside.
The method of claim 1,

The propulsion unit

A propulsion compressor 210 in which the gas discharged from the engine unit is compressed; And

Turbo jet drone including a propulsion discharge portion in communication with the outside in the propulsion compression.
The method of claim 1,

The turbo propulsion unit

A turbo compression unit configured to compress the gas discharged from the engine unit;

A turbo discharge unit communicating with an outside of the turbo compression unit; And

Turbo jet drone including a turbo control unit for adjusting the size of the turbo discharge unit.
The method of claim 3,

Turbo adjuster

A discharge cover part blocking the turbo discharge part; And

Turbo jet drone including a cover moving portion for moving the discharge cover.
The method according to any one of claims 1 to 4,

An engine unit includes a turbojet fan in which at least one fan is superimposed.