KR102044416B1 - Unmanned Aerial Vehicle and Control System - Google Patents

Abstract

The present invention relates to a hybrid unmanned aerial vehicle capable of changing the shape and a control system thereof, the hybrid unmanned aerial vehicle capable of changing the shape according to the embodiments of the present invention, the fuselage unit is provided with a first propeller portion for generating a propulsion force at the bottom, A second propeller support part provided with a main wing part provided in a direction perpendicular to the fuselage part in the center of the fuselage part, a second propeller part provided on each main wing part and generating a flotation force for supporting the fuselage part, and the second propeller An auxiliary wing formed while connecting the respective second propeller portion at both ends below the support portion, and a second propeller distance adjuster formed at the bottom of the main wing portion to adjust the distance between the respective second propeller support.

Description

Hybrid unmanned aerial vehicle capable of changing shape and its control system {Unmanned Aerial Vehicle and Control System}

The present invention relates to an unmanned aerial vehicle, and more particularly, to a hybrid unmanned aerial vehicle capable of changing a shape and a control system thereof.

Unmanned Aerial Vehicles (UAVs) are crafted to perform a given mission without a pilot. Unmanned vehicles are also called "drones" because of the sound of propellers that resemble buzzing bees.

Existing UAV (Unmanned Aerial Vehicle) is a small gas produced by reducing the actual gas to a predetermined scale or designed in its own form, and is used for various purposes, such as for industrial purposes such as aerial photography or pesticide spraying, as well as for leisure and education. It is becoming.

As the unmanned aerial vehicle is used for various industries such as aerial photography or pesticide spraying as well as for recreational or educational purposes, flight performance requirements for the unmanned aerial vehicle are increasing, thereby increasing the size and volume of the unmanned aerial vehicle.

However, it is difficult to manufacture an unmanned aerial vehicle individually according to its performance for a variety of industries such as aerial photography or pesticide spraying as well as for leisure and educational use. Difficult to store

Korean Patent Publication No. 10-2016-0125249 (Multiple drone control system and its control method) Korean Registered Patent No. 10-1776954 (Multipurpose Hybrid Resin Landing and Unmanned Aerial Vehicle with Separate Wings)

Therefore, the present invention has been proposed in consideration of the above-described matters, and the present invention is intended to provide an unmanned aerial vehicle capable of changing performance for various industries such as aerial photography or pesticide spraying, as well as leisure and educational use.

In addition, the present invention is to provide an unmanned aerial vehicle that is easy to transport and storage while changing the shape or size of the unmanned aerial vehicle according to the flight performance requirements.

Hybrid unmanned aerial vehicle capable of changing the shape according to the embodiments of the present invention is a fuselage having a first propeller portion for generating a propulsion force at the bottom, the main wing portion provided in the direction perpendicular to the fuselage in the center of the fuselage, A second propeller support portion provided on each main wing portion and having a second propeller portion for generating a flotation force for supporting the fuselage portion, and an auxiliary portion formed while interconnecting the respective second propeller portions under both ends of the second propeller support portion. It is formed on the wing and the lower end of the main wing comprises a second propeller distance adjuster for adjusting the distance between the respective second propeller support.

Hybrid unmanned aerial vehicle capable of changing the shape according to the present invention by controlling the flight performance of the unmanned aerial vehicle by changing the spacing between the propeller and the shape of the auxiliary wing, flying performance for a variety of uses, such as aerial photography or pesticide spraying, as well as leisure or educational use It can provide an unmanned aerial vehicle having a.

In addition, the hybrid drone capable of changing the shape according to the present invention can increase the carrying and storage effect of the drone by reducing the spacing between the propellers or reducing the shape or size of the auxiliary wing.

1 is a plan view showing a state of the hybrid drone capable of changing the shape according to an embodiment of the present invention.
FIG. 2 is an operation diagram illustrating a distance control between second propeller supports of the unmanned aerial vehicle according to FIG. 1.
3 is a front view showing a state of the unmanned aerial vehicle according to FIG.
4 is a plan view showing the detailed configuration and operation of the second propeller distance control unit of the unmanned aerial vehicle according to FIG.
5 to 7 are reference views showing the shape and width of the auxiliary wing portion of the unmanned aerial vehicle according to FIG.
8 is a reference diagram showing a control system of a hybrid drone capable of changing a shape according to a preferred embodiment of the present invention.

Before describing the embodiments according to the present invention in detail, the present invention is not limited to the configuration shown in the following detailed description or the accompanying drawings, and may be used or performed in various ways.

Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

That is, as used herein, the expressions "mounted", "installed", "connected", "connected", "supported", "coupled", and the like, do not indicate or limit the other. It is used in a wide variety of terms, including both direct and indirect mounting, installation, connection, connection, support, and coupling. The expressions "connected", "connected" and "coupled" are not limited to physical or mechanical connections, connections or couplings.

In the present specification, terms indicating directions, such as top, bottom, downward, upward, rearward, bottom, front, rear, and the like, are used to describe the drawings, but these terms are referred to relative to the drawings for convenience (normally viewed). When). Terms indicating this direction should not be taken as limiting or limiting the present invention in any form.

In addition, the terms "first", "second", "third", and the like as used herein are for illustrative purposes only and should not be considered as meaning relative importance.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

First, the unmanned aerial vehicle 100 has a body portion 110 having a first propeller portion 320 generating a propulsion force at a lower end as shown in FIG. 1, and a direction perpendicular to the body portion in the center of the body portion 110. A second propeller support part provided in the main wing part 200 provided in each of the main wing parts 210 and 212 and having a second propeller part 310 for generating a flotation force supporting the fuselage part 110 ( 302 and 304, an auxiliary wing 330 and a main wing lower portion 210 formed while interconnecting the respective second propeller support 302 and 304 at both ends of the second propeller support 302 and 304, respectively. And a second propeller distance adjuster 230 formed at 212 to adjust the distance between each of the second propeller supports 302 and 304.

The second propeller distance adjusting unit 230 is provided with sliding rails 220 and 221 and sliding rails 220 and 221 respectively formed on the main blades at both ends of the fuselage 110. It is rotatably provided on the support parts 302 and 304, the motor 250 and the rotating shaft 240 of the motor 250, and both ends thereof are coupled through the second propeller support parts 302 and 304 and the link member 232, respectively. The rotating unit 260 is provided.

Next, the auxiliary wing 330 is configured such that the wing shape or the width varies in conjunction with the distance control between each of the second propeller support portions 302 and 304 of the second propeller distance adjuster 230.

That is, in FIG. 5, the auxiliary wing 330 is formed of link members 354 and 356 connecting the plurality of support shafts 350 and the plurality of support shafts 350 to form a gap between the second propeller supports 302 and 304. As the distance changes, the auxiliary wing 330 is changed to have a steep trapezoidal shape or a long trapezoidal shape.

For this form, the outer surface of the auxiliary wing 330 may be formed of a material having elasticity.

And when the auxiliary wing 330 is provided in the form of a sliding rail as shown in Figure 6 as the distance between the second propeller support (302, 304) is linked to change the width and length of the auxiliary wing 330 It is configured to be.

And the auxiliary wing 330 is rotatable through the link portion 309 formed in the rear end of each of the second propeller support (302, 304), as shown in Figure 7 or movable in the Y direction, or separate It can be provided to be movable in the Z direction by providing a vertical movement means of.

Therefore, the auxiliary wing 330 is slidably moved in the forward direction of the fuselage 110 during storage to reduce the volume and size of the unmanned aerial vehicle 100 to facilitate storage and movement, and second propeller supports 302 and 304. As the distance between the) increases to move in the forward direction of the fuselage unit 110 can be configured to improve flight stability and flight performance.

In addition, as the shape and size of the auxiliary wing 330 is changed in accordance with the distance change between the second propeller support parts 302 and 304, the position is also rotated at an angle around the second propeller support parts 302 and 304 or up and down. This is to move to (Z) to control the flight performance according to the cost performance requirements of the unmanned aerial vehicle (100).

That is, as the length of the second propeller support parts 302 and 304 supporting the fuselage 110 and the second propeller 310 of the unmanned aerial vehicle 100 increases, the moment of inertia of the entire unmanned aerial vehicle 100 increases and disturbs. The attitude stability of the vehicle increases, and the torque (T = L * F) of the floating force of the second propeller 310 is increased by the lever principle, thereby improving rotation and functionality of the unmanned aerial vehicle 100.

However, when the length of the second propeller support parts 302 and 304 is increased, the entire volume of the unmanned aerial vehicle 100 is increased, which causes a problem that requires a lot of space in storage, and also damage due to external impact when moving or carrying. There is a problem that increases the risk.

However, by changing the distance between the second propeller support (302, 304) as in the present invention, it is possible to improve the functionality of the unmanned aerial vehicle 100 and the convenience of carrying and storage.

In addition, when the distance between the second propeller support parts 302 and 304 changes and the width and length of the auxiliary wing 330 change, flight characteristics of the unmanned aerial vehicle 100 are changed. That is, it is preferable to shorten the distance between the second propeller support parts 302 and 304 for a faster flight, and to increase the distance between the second propeller support parts 302 and 304 for a stable flight.

Therefore, the user may widen the distance between the second propeller support parts 302 and 304 for a stable flight, such as transporting a heavy package, and shorten the distance between the second propeller support parts 302 and 304 during a long flight.

In addition, according to the distance between the second propeller support (302, 304), it is preferable to control the output, etc. differently during flight control of the unmanned aerial vehicle (100).

However, when the plurality of unmanned aerial vehicles 100 fly, the control system 10 according to the preferred embodiment of the present invention is between the second propeller support portions 302 and 304 adjusted by the second propeller distance adjusting unit 230. The plurality of unmanned aerial vehicles 100 may be classified into separate group groups according to distance intervals, and a group identification code for identifying the classified group groups may be assigned to facilitate flight control of the plurality of unmanned aerial vehicles 100. .

That is, the group group having a narrow distance between the second propeller support parts 302 and 304 and the group group having a large distance between the second propeller support parts 302 and 304 are separately provided with a group identification code to control flight accordingly. .

This has the effect of further improving the control effect of the plurality of unmanned aerial vehicles (100).

In the control system 10 according to the present invention, in the grouping of the plurality of unmanned aerial vehicles 100 and the group identification code, the shapes, weights, utilization forms, flight distances, altitudes, and times of the plurality of unmanned aerial vehicles 100 are provided. Grouping according to the group to give a group identification code for the group and set the propeller output conditions of the unmanned vehicle 100 for each group identification code, and then the flight of the unmanned vehicle 100 according to the conditions set by the group identification code. Can be controlled.

Although the preferred embodiment of the present invention has been described above, the present invention may use various changes, modifications, and equivalents. It is clear that the present invention can be applied in the same manner by appropriately modifying the above embodiments. Accordingly, the above description does not limit the scope of the invention as defined by the limitations of the following claims.

100: unmanned aerial vehicle 200: main wing 300: auxiliary wing
302 and 304: second propeller support

Claims (5)

A fuselage portion having a first propeller portion generating a propulsion force at a lower end thereof;
A main wing part provided in the center of the fuselage part in a direction perpendicular to the fuselage part;
A second propeller support part provided on each of the main wing parts and provided with a second propeller part generating flotation force for supporting the fuselage part;
Auxiliary wings formed on both ends of the second propeller support while interconnecting the respective second propellers; And
And a second propeller distance adjuster formed at a lower end of the main wing to adjust the distance between the respective second propeller supports.
The second propeller distance adjusting unit,
A sliding rail formed at each of the main wing parts of the fuselage part, each of the second propeller support parts provided to be slidably movable on the sliding rail, and rotatable parts rotatably connected to the respective second propeller support parts; Equipped,
The auxiliary wing unit is a hybrid unmanned aerial vehicle capable of changing the shape of the wing shape or the width is changed in conjunction with the distance control between the second propeller support portion of the second propeller distance adjuster. delete delete Hybrid unmanned aerial vehicle capable of changing a plurality of shapes according to claim 1; And
And a controller configured to control the plurality of shapeless hybrid drones through a communication module and the plurality of shapeless hybrid planes.
The control unit changes according to any one of the shape, weight, flight distance, flight altitude, flight time and flight purpose of the hybrid unmanned aerial vehicle capable of changing the plurality of shapes, and gives a group identification code to the grouped group. This hybrid drone control system is available. The method of claim 4, wherein
The control unit;
According to the distance between each of the second propeller support adjusted by the second propeller distance adjuster classifies a plurality of unmanned vehicles into a separate group group and the shape change to give a group identification code for identifying the classified group group Possible hybrid unmanned aerial vehicle control system.

Images