KR102250356B1 - Improved drone - Google Patents

Abstract

An object of the present invention is to provide an improved unmanned aerial vehicle that is easy to carry and can reduce the weight of the vehicle and increase the flight time by using a folding and folding structure frame and a tube-shaped float. To this end, the present invention comprises a body part of an unmanned aerial vehicle; A plurality of float frames disposed around the body at regular intervals and having a hollow inside; A flotation body installed in the hollow of the flotation frame to lift the body portion by the lift of the gas injected therein; A rotor portion installed at an end of the float frame to lift or move the body portion by the lift of the blade; And a control module installed on the body to receive a control signal including flight posture and location information stored in advance or transmitted from an external terminal to control the body to fly. Therefore, the present invention is advantageous in that it is easy to carry the vehicle, can significantly reduce the weight of the vehicle, reduce the driving force for levitation of the vehicle and reduce noise generation, and increase the flight time of the vehicle. have.

Description

Improved unmanned aerial vehicle {IMPROVED DRONE}

The present invention relates to an improved unmanned aerial vehicle, and more particularly, to an improved unmanned aerial vehicle that is easy to carry and can reduce the weight of the vehicle and increase flight time by using a folding and folding structure frame and a tube-shaped float. will be.

An unmanned aerial vehicle refers to a vehicle that can be automatically operated by remote control from a distance without a pilot on board.

Unlike general aircraft, these unmanned aerial vehicles do not have a space for pilots and safety devices, so they can be miniaturized and lightweight, and for reconnaissance for collecting and reconnaissance of information in places where human access is difficult, and for attacking with mini-bombs. It is being developed and utilized in a variety of ways, such as for chemicals equipped with biochemical sensors, and for electronic use that paralyzes communication of enemy forces.

In addition, Korean Registered Patent Publication No. 10-1252080 (Name of the invention: transmission tower insulator crack inspection apparatus and method through a quadrotor type flight robot), and Korean Registered Patent Publication No. 10-1373038 (Name of the invention: Rescue of the recipient's name) Various technologies using an unmanned flight assembly have been proposed in a levitation flying robot equipped with an airbag and an airbag dropping device for the purpose.

1 is a perspective view showing a general unmanned aerial vehicle assembly, in which a conventional unmanned aerial vehicle 10 includes a body 11 constituting a skeleton of an air vehicle, a frame 12 connected to the body 11 to support a motor, A drive module 13 comprising a motor that is directly connected to the frame 12 to move a propeller and a propeller that moves by the motor, and a control module 14.

Since such a conventional unmanned flight assembly 10 is provided with a lifting force from the rotational force of the driving module 13, there is a problem that serious noise is generated in order to generate a strong rotational force when floating or moving in the air.

In addition, since the conventional unmanned flight assembly 10 is provided with buoyancy through the driving module 13, there is a problem in that it cannot perform a long flight if sufficient power is not supplied.

In addition, in the conventional unmanned flight assembly 10, the body 11 is configured to maintain a certain size or shape, so there are restrictions on miniaturization and weight reduction, and also, due to the shape and size of the body 11, the user can carry and move. There is a problem that it is inconvenient to do.

Korean Patent Publication No. 10-1252080 (Name of invention: Transmission tower insulator crack inspection apparatus and method through a quadrotor type flying robot). Korean Registered Patent Publication No. 10-1373038 (Title of invention: levitation flying robot equipped with airbag and airbag dropping device for the rescue of aquatic life).

In order to solve this problem, the present invention aims to provide an improved unmanned aerial vehicle that is easy to carry and can reduce the weight of the vehicle and increase the flight time by using a folding and folding structure frame and a tube-shaped float. .

In order to achieve the above object, the present invention is an unmanned aerial vehicle, the body portion; A plurality of float frames arranged at regular intervals around the body portion; A rotation coupling portion supporting the float frame to be folded and folded with the body portion; A rotor unit installed at an end of the float frame to lift or move the aircraft by the lift of the blade; And a control module installed on the body to receive a control signal including flight posture and location information stored in advance or transmitted from an external terminal to control the aircraft to fly.

In addition, the improved unmanned aerial vehicle according to the present invention is characterized in that it further comprises a float installed on the float frame to lift the air vehicle with the lift of the gas injected therein.

In addition, the rotational coupling portion according to the present invention a body coupling portion connected to the body portion; A frame coupling portion spaced apart from the body coupling portion and connected to the float frame; And a rolling portion installed between the body coupling portion and the frame coupling portion to rotatably connect the body coupling portion and the frame coupling portion.

In addition, the float frame according to the present invention is characterized in that it further comprises a rotor frame for protecting the rotor part.

In addition, the improved unmanned aerial vehicle according to the present invention is characterized in that it further comprises a camera installed on the body to take an image.

The present invention has the advantage of being easy to carry by configuring the body of the unmanned aerial vehicle as a frame of a folding and folding structure.

In addition, the present invention has the advantage of being able to significantly reduce the weight of the vehicle by configuring a tube-shaped floating body on the unmanned aerial vehicle.

In addition, the present invention has the advantage of reducing the weight of the unmanned aerial vehicle, reducing driving force for levitation of the vehicle and remarkably reducing noise generation.

In addition, the present invention has the advantage of increasing the flight time of the vehicle by reducing the weight of the unmanned aerial vehicle.

1 is a perspective view showing a general unmanned flight assembly.
Figure 2 is a perspective view showing an improved unmanned aerial vehicle according to the present invention.
Figure 3 is an exploded perspective view showing the configuration of an improved unmanned aerial vehicle according to the present invention.
Figure 4 is a cross-sectional view showing the structure of the improved unmanned aerial vehicle according to the present invention.
Figure 5 is a front view showing a folded state of the improved unmanned aerial vehicle according to the present invention.
Figure 6 is a block diagram showing the configuration of the control module of the improved unmanned aerial vehicle according to the present invention.

Hereinafter, a preferred embodiment of an improved unmanned aerial vehicle according to the present invention will be described in detail with reference to the accompanying drawings.

Figure 2 is a perspective view showing an improved unmanned aerial vehicle according to the present invention, Figure 3 is an exploded perspective view showing the configuration of the improved unmanned aerial vehicle according to the present invention, Figure 4 is a cross-sectional view showing the structure of the improved unmanned aerial vehicle according to the present invention, Figure 5 is a front view showing a folded state of the improved unmanned aerial vehicle according to the present invention, Figure 6 is a block diagram showing the configuration of the control module of the improved unmanned aerial vehicle according to the present invention.

2 to 6, the improved unmanned aerial vehicle 100 according to the present invention includes a body portion 110 of an unmanned aerial vehicle, a plurality of float frames 120, a rotation coupling portion 130, and a rotor A frame 140, a float 150, a rotor unit 160, a control module 170, and a camera 180 are included.

The body portion 110 of the unmanned aerial vehicle is a spherical, hemispherical, or polyhedral housing having a storage space therein, and the float frame 120, the control module 170, and the camera 180 ), etc. to be installed, and comprises a body flange 111 and a gas control valve 112.

In addition, the body portion 110 is made of a light material such as carbon fiber, glass fiber, so as not to limit flight, and a control module 170 is installed inside the body portion 110, and the body portion Outside of 110, a camera 180 and the like are installed.

The body portion flange 111 is formed to protrude a predetermined length along the circumference of the body portion 110, and the body portion flange 111 has a float frame 120 installed at regular intervals to be fixed.

The gas control valve 112 is installed under the body portion 110 to control the gas supplied from the outside to be injected into the floatation body 150 to provide a lift of the aircraft 100, and in the control module 170 It may be operated according to the output control signal so that the gas injected into the floater 150 is discharged.

The float frame 120 is disposed at regular intervals along the circumference of the body portion 110, and forms a hollow 120a inside, so that the weight due to the float frame 120 can be reduced.

In addition, a float 150 is installed in the hollow 120a formed in the float frame 120 to provide a lift force to the aircraft 100.

In addition, a rotor frame 140 for protecting the rotor unit 160 is additionally installed at one end of the float frame 120.

The rotation coupling part 130 is a structure that allows the float frame 120 to be folded and folded with the body part 110, and the body coupling part 131, the frame coupling part 132 and the rolling It is configured to include a section 133.

The body coupling portion 131 is a configuration such that one side of the rotation coupling portion 130 is connected to the body portion 110, and the cross-sectional shape is formed in'⊃' and is coupled to the body portion flange 111 to provide a support pin ( 134).

In addition, the body coupling portion 131 may be rotatably coupled to a certain range around the support pin 134, and when rotated through the support pin 134, the rotation range of the body coupling portion 131 A stopper (not shown) to limit the, and a locking means (not shown) for supporting the body coupling portion 131 to be more rigidly fixed to the body portion flange 111 may be additionally configured.

The frame coupling portion 132 is arranged to be spaced apart from the body coupling portion 131 by a predetermined distance, and the other side of the rotation coupling portion 130 is connected to the float frame 120, and the cross-sectional shape is'⊃' It is formed of the float frame 120 is coupled to the support pin 134 to be fixed rotatably.

In addition, the frame coupling portion 132 may be rotatably coupled to a certain range around the support pin 134, and when rotated through the support pin 134, the rotation range of the frame coupling portion 132 A stopper (not shown) for limiting and a locking means (not shown) for supporting the frame coupling portion 132 to be more rigidly fixed to the float frame 120 may be additionally configured.

The rolling part 133 is installed between the body coupling part 131 and the frame coupling part 132 to connect the body coupling part 131 and the frame coupling part 132, preferably the body coupling The part 131 and the frame coupling part 132 are rotatably connected on a concentric shaft.

The rotor frame 140 is installed on one side of the float frame 120, and a hollow 140a is formed in the inner side so that the rotor unit 160 is disposed so that the rotor unit 160 is fixed together with the blade 162 To be protected.

The float 150 is a configuration that is installed in the hollow 120a of the float frame 120 to lift the aircraft 100 by the lift of the gas injected therein, and is a balloon made of rubber or synthetic resin having excellent elasticity. , On one side, a gas connection part 151 connected to the gas control valve 112 is installed.

That is, the float 150 is installed in a contracted state on the float frame 120, and when gas (for example, helium gas, hydrogen gas, etc.) is supplied from the outside through the gas control valve 112, the volume is reduced. It expands so that the buoyancy force by the supplied gas can be provided.

In addition, the gas supplied to the floater 150 may be discharged to the outside through the gas control valve 112.

The rotor unit 160 is installed at the end of the float frame 120 to lift or move the aircraft 100 by the lift of the blade 162, and includes a motor unit 161 and a blade 162 It is composed of.

That is, the rotor unit 160 is a configuration that operates on a principle similar to that of the blades of a helicopter, so that the vehicle 100 is raised and lowered by the lifting force generated by the blade 162 through the rotation of the motor unit 161. Allows the vehicle 100 to fly safely, and when the vehicle 100 moves to an arbitrary position, the direction of the vehicle 100 is controlled so that the vehicle 100 can be moved to a desired location. do.

In the present embodiment, the four rotor units 160 have been described as examples, but the present invention is not limited thereto, and the rotor units may be variously changed, such as two, six or more, as necessary.

The control module 170 is a configuration that controls the flight vehicle 100 to fly by receiving a control signal including flight posture and location information that is installed in the body portion 110 and stored in advance or transmitted from an external terminal. 171, a control unit 172, a motor driving unit 173, a position receiving unit 174, and a power supply unit 175.

The data communication unit 171 is a configuration that transmits and receives a control signal including flight posture and location information with an external terminal (not shown) for controlling the aircraft 100 from a remote location, RF communication, wireless Internet communication, short-range data communication Control signals are transmitted and received using at least one communication format.

In addition, the data communication unit 171 may transmit an image signal captured by the camera 180 to an external terminal.

The control unit 172 analyzes the control signal received through the data communication unit 171 and controls the vehicle 100 to be operated according to the flight posture or location information, and the motor driving unit 173 ) To output operation signals of the first motor unit 161a, the second motor unit 161b, the third motor unit 161c, and the fourth motor unit 161d.

In addition, the control unit 172, when a preset flight posture or arbitrary location information is stored in a memory (not shown), outputs an operation signal so that the aircraft 100 may fly or move according to the stored flight posture or location information. May be.

In addition, the control unit 172 outputs an on/off signal of the gas control valve 112 so that the gas injected into the float 150 is forcibly discharged, so that the aircraft 100 that has risen above a certain height can descend. To be there.

In addition, the control unit 172 controls the on/off signal for the camera 180 to operate and the image signal captured by the camera 180 to be stored in a memory or transmitted to an external terminal through the data communication unit 171 do.

The motor driving unit 173 includes a first motor unit 161a, a second motor unit 161b, and a third motor unit 161c installed in the four rotor units 160 according to an operation signal output from the control unit 172. And the operation of the fourth motor unit 161d is controlled.

The location receiving unit 174 is a configuration configured to receive the location information of the aircraft 100 and output it to the control unit 172, preferably made of a GPS terminal.

The power supply unit 175 is a component that supplies power so that the aircraft 100 can fly, and includes at least one of a battery module and a solar cell module.

The camera 180 is installed outside the body portion 110 and operates according to an on/off signal output from the control module 170, and transmits an image signal photographing the surrounding environment to the control module 170. .

In addition, the camera 180 is configured to include at least one sensor of a CCD sensor, a CMOS sensor, or any image sensor that converts and outputs an image into an electrical signal, and includes an infrared sensor or a filter for night photography, etc. You may.

The following describes the operation process of the improved unmanned aerial vehicle according to the present invention.

The aircraft 100 according to the present invention is in a state in which the float frame 120 is folded around the body portion 110, as shown in FIG. 5, and is contracted in the hollow 120a of the folded float frame 120 The flotation body 150 is disposed in a state of being.

As shown in FIG. 5, when the gas for generating the buoyancy force is injected through the gas control valve 112 in the folded state of the flotation frame 120, that is, in the closed state of the flotation frame 120, the aircraft 100 is in a vertical direction. You can ascend quickly.

However, when gas is injected while the float frame 120 is closed, it may be difficult to control the flight posture for flight and to move according to the location information, but the aircraft 100 quickly moves without the operation of the rotor unit 160 You can perform an ascending operation.

In addition, depending on the amount of gas to be injected, it may be controlled to rise only to an appropriate height.

On the other hand, when the vehicle 100 performs a normal flight, the two floating body frames 120 in a folded state are rotated upwardly around the support pins 134b installed on the frame coupling part 132, respectively. The frame coupling part 132 is in a horizontal state with the body part 110.

When the float frame 120 is opened, the rolling part 133 is rotated so that the float frame 120 is in a state as shown in FIG. 2.

Thereafter, the gas is connected to a helium gas tank (not shown) through the gas control valve 112 so that gas such as helium gas is supplied to each of the floaters 150 through the gas connection unit 151.

When a certain amount of gas is supplied to the flotation body 150, the aircraft 100 rises into the air by the buoyancy force generated from the gas supplied to the flotation body 150.

The flying vehicle 100 ascended into the air rises without the buoyancy of the rotor 160, so that the rotor 160 does not need to provide a buoyancy through high-speed rotation.

That is, the airborne vehicle 100 only needs an operation for movement, such as a flight posture or a direction change to move to an arbitrary position due to the buoyancy provided through the float 150, and the rotor unit 160 has a lifting force. It is not necessary to operate at high speed to provide

Therefore, since the rotor unit 160 does not rotate at high speed, only a small amount of power is required for the operation of the rotor unit 160 along with a reduction in noise generation, so that the aircraft 100 is front/rear/left/rear at low power. You can move in the right/up/down direction.

The flight vehicle 100 is to fly or move according to the flight posture or location information transmitted from an external terminal (not shown), and the flight vehicle 100 analyzes the location information received from the location receiving unit 174 and receives the received location. Check whether you are moving according to the information.

Thereafter, when the flight of the aircraft 100 is finished, the gas supplied to the float 150 is discharged through the gas control valve 112, and the float frame ( 120) is folded so that the volume of the aircraft 100 can be minimized.

Therefore, by configuring the body of the vehicle with a folding and folding frame, it is easy to carry, and by configuring a tube-shaped float on the unmanned aerial vehicle, the weight of the vehicle can be drastically reduced, and the weight of the vehicle can be reduced and Through the provision of buoyancy through the vehicle, it is possible to significantly reduce the driving force for levitation of the vehicle and significantly reduce noise generation, and increase the flight time of the vehicle.

As described above, although it has been described with reference to a preferred embodiment of the present invention, those skilled in the art will variously modify and change the present invention within the scope not departing from the spirit and scope of the present invention described in the following claims. You will understand that you can do it.

In addition, in the process of describing an embodiment of the present invention, the thickness of the lines or the size of components shown in the drawings may be exaggerated for clarity and convenience of description, and the above-described terms take into account functions in the present invention. These terms are defined as such and may vary depending on the intention or custom of users or operators, and thus interpretations of these terms should be made based on the contents throughout the present specification.

100: aircraft 110: body
111: body flange 111a: through hole
112: gas control valve 120: float frame
130: rotation coupling portion 131: body coupling portion
132: frame coupling portion 133: rolling portion
134: support pin 140: rotor frame
150: float 151: gas connection
160: rotor unit 161: motor unit
162: blade 170: control module
171: data communication unit 172: control unit
173: motor drive unit 174: position receiving unit
175: power supply unit 180: camera

Claims (5)

As an unmanned aerial vehicle,
Body portion 110;
A plurality of float frames 120 arranged at regular intervals around the body portion 110;
The support frame 120 is supported to be folded and folded with the body portion 110, but the body coupling portion 131 connected to the body portion 110, and the body coupling portion 131 ) And the frame coupling portion 132 connected to the float frame 120 by a certain distance, and the body coupling portion 131 and the frame coupling portion 132 installed between the body coupling portion 131 and the frame A rotation coupling part 130 having a rolling part 133 rotatably connecting the coupling part 132 to each other;
A rotor unit 160 installed at the end of the float frame 120 to lift or move the aircraft with the lift of the blade 162; And
An improved unmanned aerial vehicle comprising a control module 170 installed on the body 110 to control the vehicle to fly by receiving a control signal including flight posture and location information stored in advance or transmitted from an external terminal.
The method of claim 1,
The improved unmanned aerial vehicle is an improved unmanned aerial vehicle, characterized in that it further comprises a float 150 installed on the float frame 120 to lift the air vehicle with the lift of the gas injected therein.
delete The method of claim 1,
The float frame 120 is an improved unmanned aerial vehicle, characterized in that it further comprises a rotor frame 140 for protecting the rotor unit 160.
The method of claim 1,
The improved unmanned aerial vehicle is an improved unmanned aerial vehicle, characterized in that it further comprises a camera 180 for photographing an image installed on the body portion (110).

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