KR20170018671A

KR20170018671A - Hybrid system of drone

Info

Publication number: KR20170018671A
Application number: KR1020150112597A
Authority: KR
Inventors: 곽승렬
Original assignee: 주식회사 성진에어로
Priority date: 2015-08-10
Filing date: 2015-08-10
Publication date: 2017-02-20
Also published as: KR101820420B1

Abstract

A hybrid drones system according to an embodiment of the present invention includes: a duct body having a duct structure; A rotor disposed at the center of the dragon body and rotated to generate lifting force and thrust; A turboshaft engine for generating rotational power to transmit the rotational power to the rotor; A generator for generating electrical energy using rotational power by the turboshaft engine; And a plurality of propellers disposed in a duct structure formed to be spaced apart from the outer periphery of the drone body and rotating in association with an electric motor driven by electric energy produced from the generator.

Description

[0001] HYBRID SYSTEM OF DRONE [0002]

BACKGROUND OF THE INVENTION Field of the Invention [0002] The present invention relates to an unmanned aerial vehicle, and more particularly, to a hybrid drones system capable of flying in a hybrid manner using an electric energy produced by a turbo shaft engine and its driving.

Generally, unmanned aerial vehicles include all flying objects, such as unmanned aerial vehicles and unmanned aerial vehicles, which are remotely controlled by persons, or fly according to prior information.

These unmanned aerial vehicles are put into operation in areas that are not accessible to humans such as jungle, ogres, volcanic area, natural disaster area, nuclear power plant accident area, and are developed and commercialized not only for military use but also as individual hobby activities.

These unmanned aerial vehicles can be largely classified into a fixed airfoil and a rotor blade.

Fixed airfoil is easy to operate but it is inefficient because it is necessary to turn the target area several times during the reconnaissance mission to acquire accurate information and to operate it according to the progress speed of the target during the tracking mission.

On the other hand, the flywheel type is capable of vertical takeoff and landing regardless of the range of the in-situ, side, and backward flight, and the place, but it has the disadvantage of losing lift when tilted.

Therefore, it is necessary to develop a multi - function compound unmanned aerial vehicle that has the advantages of the above two types of unmanned aerial vehicles and can overcome the drawbacks.

A related prior art is Korean Patent Registration No. 10-1451-6460000 entitled " Multifunctional Duct Type Unmanned Aerial Vehicle, Registered Date: October 10, 2014].

An embodiment of the present invention provides a hybrid drones system capable of supplying electric power in a hybrid manner by using electric energy produced by self-generation of a turboshaft engine and a generator associated therewith.

The problems to be solved by the present invention are not limited to the above-mentioned problem (s), and another problem (s) not mentioned can be clearly understood by those skilled in the art from the following description.

Wherein the rotor includes upper and lower rotors disposed in a vertical direction at a center of the drone and a plurality of blades coupled to the upper and lower rotors to generate the lift and thrust, The upper and lower rotors can rotate in different directions.

The plurality of propellers include upper and lower propellers disposed up and down in the duct structure, and the upper and lower propellers are connected to the plurality of electric motors, respectively, and rotate in different directions to generate lift and thrust have.

The hybrid drones system according to an embodiment of the present invention may further include a battery for storing electric energy produced from the generator, and the battery may supply the stored electric energy to the electric motor for rotation of the propeller.

The hybrid drones system according to an embodiment of the present invention may further include a grill installed on the drones for protecting the rotor, the turboshaft engine, and the generator by covering an upper portion of the duct structure of the drones .

The hybrid drones system according to an embodiment of the present invention further includes a landing gear installed to be inserted into a lower portion of the drones and equipped with a shock absorber for relieving an impact during landing, And can be inserted into the lower portion of the drone.

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

According to an embodiment of the present invention, electric power is supplied in a hybrid manner by using electric energy produced by self-power generation by the turboshaft engine and a generator associated therewith, so that the drone can be engaged for a long time have.

According to an embodiment of the present invention, the drone body is realized as a duct structure surrounding the rotor, thereby enhancing the stability of the system to provide constant and continuous power to the drone body.

According to an embodiment of the present invention, the rotary shaft formed in the rotor in the drone and the plurality of blades rotate in opposite directions to each other, so that the drone can be driven with high ascending, descending, and propelling capability.

According to an embodiment of the present invention, since a rotor having a coaxial inverting structure is provided, it is possible to exhibit a superior lift capability as compared with a thrust device having a single structure without a separate device for canceling the anti-torque.

According to an embodiment of the present invention, a plurality of propellers spaced apart from each other on the outer periphery of a drone body rotate in opposite directions to each other, so that the direction of the drone body can be controlled and a stable posture can be maintained.

1 is a perspective view illustrating a hybrid drones system according to an embodiment of the present invention.
2 is a side view illustrating a hybrid drones system according to an embodiment of the present invention.
3 is a view showing a hybrid drones in which a grill is separated, according to an embodiment of the present invention.

BRIEF DESCRIPTION OF THE DRAWINGS The advantages and / or features of the present invention, and how to accomplish them, will become apparent with reference to the embodiments described in detail below with reference to the accompanying drawings. It should be understood, however, that the invention is not limited to the disclosed embodiments, but is capable of many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, To fully disclose the scope of the invention to those skilled in the art, and the invention is only defined by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

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

FIG. 1 is a perspective view illustrating a hybrid drones system according to an embodiment of the present invention. FIG. 2 is a side view illustrating a hybrid drones system according to an embodiment of the present invention. In one embodiment of the invention, the grill is shown with a separated hybrid drones.

1 to 3, a hybrid drones 100 according to an embodiment of the present invention includes a drone body 110, a rotor 120, a turbo shaft engine 130, a generator 140, a plurality of propellers 150, a battery (not shown), a grill 170, and a landing gear 180.

The drone body 110 is formed in a duct structure, and the shape thereof may be a hollow circular shape.

At this time, the drone body 110 is formed in a structure in which the hollow circular ducts are disposed at the center, and a plurality of ducts having the same shape at the outer edge of the duct disposed at the center and smaller in size are spaced apart .

The rotor 120 to be described below may be disposed in the circular duct of the dragon body 110.

Here, since the circular duct is formed to surround the rotor 120, the dragon body 110 can secure safety according to the rotation of the rotor 120. In addition, the dragon body 110 can generate thrust due to the duct structure at the time of flying, thereby increasing the overall power efficiency.

For reference, the drone body 110 may be formed of a composite material of carbon fibers such as CFRP and GFRP having a high strength and high elasticity over the entire body.

As such, the dragon body 110 is provided with a duct structure that surrounds the rotor 120, thereby providing constant and continuous power to the dragon body 110, and through the hybrid drones system 100 ) Can be increased.

The rotor 120 is disposed at the center of the dragon body 110. That is, the rotor 120 may be formed in a hollow portion of the dragon body 110.

The rotor 120 may include upper and lower rotors (not shown). That is, the rotor 120 may be formed by coupling the upper and lower rotors disposed above and below with reference to the same vertical axis.

The upper and lower rotors may include upper and lower rotating shafts arranged vertically in the center of the drone body 110 and a plurality of blades coupled to the upper and lower rotating shafts to generate the lift force and the thrust force, have.

The upper and lower rotation shafts may be disposed on the same axis in a direction perpendicular to each other. That is, the upper rotation shaft may be coupled to the upper rotor, and the lower rotation shaft may be coupled to the lower rotor.

The plurality of blades may be formed so as to be spaced apart from the rim of each of the upper and lower rotation shafts. That is, a plurality of upper blades may be formed on the upper rotation shaft, and a plurality of lower blades may be formed on the lower rotation shaft.

In an embodiment of the present invention, two blades are formed on each of the rims of the upper and lower rotation shafts, but not limited thereto, three or more blades may be formed.

The rotor 120 rotates to generate lifting force and thrust force of the dragon body 110. That is, the rotor 120 can generate lifting force and thrust force of the dragon body 110 through rotation of the upper and lower rotors.

At this time, the upper and lower rotors may rotate in different directions. That is, as the upper and lower rotary shafts rotate in opposite directions with respect to the vertical axis, the upper and lower rotors can also rotate in different directions. Accordingly, the dragon body 110 can control take-off and landing operations.

For example, when the upper rotation shaft and the plurality of upper blades are clockwise, and the lower rotation shaft and the plurality of lower blades are rotated counterclockwise, the upper rotor is clockwise, Direction. On the other hand, when the upper rotation shaft and the plurality of upper blades rotate counterclockwise, and when the lower rotation shaft and the plurality of lower blades rotate clockwise, the upper rotor rotates counterclockwise and the lower rotor rotates clockwise It can be said to rotate.

Accordingly, the upper and lower rotors can be rotationally driven so as to be safeguarded from disturbances in all directions 360 degrees.

Thus, according to an embodiment of the present invention, the hybrid drones system 100 can be driven with a high ascending, descending, and propelling capability through a strong rotational force by the upper and lower rotors of the rotor 120. Therefore, according to the embodiment of the present invention, the hybrid drones system 100 can exhibit superior lift performance compared to a thrust device having a single structure without a separate device for canceling anti-torque.

The turboshaft engine 130 generates rotational power and transmits the rotational power to the rotor 120.

At this time, the turboshaft engine 130 can generate the rotational power by driving the free turbine with the thrust of the gas turbine. Also, the turboshaft engine 130 may generate the rotational power using fossil fuel.

The turbo shaft engine 130 can transmit the rotational power to the rotor 120 as the rotation shaft installed therein is rotated by the generated rotational power. Accordingly, the rotor 120 may rotate the upper and lower rotors due to the rotational power transmitted from the turboshaft engine 130.

In the embodiment of the present invention, the turbo shaft engine 130 is designed to be installed below the drone body 110. However, the present invention is not limited to this, and it may be installed on the upper or side surface of the drone body 110 Do.

The generator 140 generates electrical energy using the rotational power of the turboshaft engine 130. That is, the generator 140 can generate the electric energy by receiving and driving the rotational power from the turboshaft engine 130 through the rotational shaft.

As described above, according to an embodiment of the present invention, the generator 140 coupled to the turboshaft engine 130 mounted in the drone is self-powered by the rotational force of the turboshaft engine 130, 100) for a long period of time to perform the mission.

The plurality of propellers 150 are disposed in a duct structure 160 formed to be spaced from the outer circumference of the drone body 110.

At this time, the plurality of propellers 150 may include upper and lower propellers arranged up and down in the duct structure 160.

The upper and lower propellers may include an electric motor formed at the center of the duct structure 160 formed on the outer periphery of the drones 110. That is, the upper and lower propellers may include two electric motors (an upper electric motor and a lower electric motor) respectively disposed in accordance with the upper and lower positions.

The electric motor may include upper and lower power transmission shafts arranged in a vertical direction and a plurality of shafts coupled to the upper and lower power transmission shafts to generate the lift and thrust.

The upper and lower power transmission shafts may be disposed on the same axis in the vertical direction, wherein the upper power transmission shaft and the lower power transmission shaft may be respectively connected to the upper electric motor and the lower electric motor, respectively.

The plurality of shafts may be formed so as to be spaced apart from the rim of each of the upper and lower power transmission shafts. That is, a plurality of upper shafts may be formed on the upper power transmission shaft, and a plurality of lower shafts may be formed on the lower power transmission shaft.

The plurality of propellers 150 rotate in conjunction with the electric motor driven by the electric energy produced from the generator 140.

When the plurality of propellers 150 are provided with the electric energy produced from the generator 140, the upper and lower propellers may be connected to the plurality of electric motors, respectively, and may rotate according to the driving of the electric motors.

At this time, the upper and lower power transmission shafts may rotate in directions opposite to each other with respect to the vertical axis, so that the upper and lower propellers may rotate in different directions.

For example, when the upper power transmission shaft rotates in a clockwise direction and the lower power transmission shaft rotates in a counterclockwise direction, the upper propeller rotates in a clockwise direction and the lower propeller rotates in a counterclockwise direction. On the other hand, when the upper power transmission shaft rotates counterclockwise and the lower power transmission shaft rotates clockwise, the upper propeller rotates counterclockwise and the lower propeller rotates clockwise.

Accordingly, the upper and lower electric motors can be driven to enable delicate harboring and landing and landing. That is, by rotating the upper and lower electric motors in opposite directions, the drone body 110 can move in the air without moving in the air, and moreover, can be more accurately taken off or landed in the target direction .

As described above, according to the embodiment of the present invention, the plurality of propellers spaced apart from the outer periphery of the drones 110 can be rotated in opposite directions to control the direction of the drones 110 And it is possible to maintain a stable posture.

The battery may store electrical energy produced from the generator 140.

That is, the battery may store extra electrical energy other than electrical energy sufficient for the generator 140 to drive the drones 110.

Accordingly, the battery can provide sufficient electric power for the constant and continuous driving of the drone body 110 when the drone body 110 is held for a long time or when a large amount of electric energy is required .

The grill 170 may be installed on the drones 110. That is, the grill 170 may be formed in a net shape to cover the upper portion of the duct structure of the drone body.

Therefore, the grill 170 can protect the rotor 120, the turboshaft engine 130, and the generator 140 provided in the drone body 110 from external shocks.

In an embodiment of the present invention, the grill 170 may be installed on the upper part of the duct structure formed at the center of the drones 110, and on the upper part of the duct structure 160 where the plurality of propellers 150 are disposed Respectively.

The landing gear 180 may be installed to be inserted into the lower portion of the drone body 110.

The landing gear 180 may be inserted into the lower portion of the drone body 110 when taking off the flight. On the other hand, the landing gear 180 may protrude from the lower portion of the dragon body 110 so as to mitigate the impact caused by collision with the ground during flight landing.

For this purpose, the landing gear 180 may be provided with a shock absorber for relieving the shock during flight landing. In other words, the landing gear 180 can minimize collision with the ground during flight landing through a shock absorber formed of an elastic material to assist in shock absorption.

As described above, according to an embodiment of the present invention, by supplying electric power in a hybrid manner by using electric energy produced by self-power generation by the turboshaft engine and the generator connected thereto, the drones can be engaged for a long time, .

While the present invention has been described in connection with what is presently considered to be practical exemplary embodiments, it is to be understood that the invention is not limited to the disclosed embodiments. Therefore, the scope of the present invention should not be limited to the described embodiments, but should be determined by the scope of the appended claims and equivalents thereof.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed exemplary embodiments, but, on the contrary, Modification is possible. Accordingly, the spirit of the present invention should be understood only in accordance with the following claims, and all equivalents or equivalent variations thereof are included in the scope of the present invention.

110: Drones
120: Rotor
130: Turbo shaft engine
140: generator
150: Propeller
170: Grill
180: Landing gear

Claims

Drone body of duct structure;
A rotor disposed at the center of the dragon body and rotated to generate lifting force and thrust;
A turboshaft engine for generating rotational power to transmit the rotational power to the rotor;
A generator for generating electrical energy using rotational power by the turboshaft engine; And
A plurality of propellers arranged in a duct structure formed to be spaced apart from an outer periphery of the drone body and rotated in association with an electric motor driven by electric energy produced from the generator,
And a hybrid drones system.

The method according to claim 1,
The rotor
And a plurality of blades coupled to the upper and lower rotation shafts and the upper and lower rotation shafts, respectively, arranged vertically in the center of the drones for generating lift and thrust,
Lt; / RTI >
The upper and lower rotors
Wherein the rotor is rotated in different directions.

The method according to claim 1,
The plurality of propellers
And upper and lower propellers disposed up and down in the duct structure,
The upper and lower propellers
Wherein the plurality of electric motors are connected to the electric motors and rotate in different directions to generate lift and thrust forces.

The method according to claim 1,
A battery for storing electric energy produced from the generator
Further comprising:
The battery
And the electric energy stored in the electric motor is supplied to the electric motor for rotation of the propeller.

The method according to claim 1,
A grill for protecting the rotor, the turboshaft engine, and the generator by covering an upper portion of the duct structure of the drones;
The hybrid drones system further comprising:

The method according to claim 1,
A landing gear which is installed to be insertable in a lower portion of the dragon body and has a shock absorber for relieving an impact during landing,
Further comprising:
The landing gear
Is inserted into the lower portion of the drones when the flight is taken off.