KR20170061883A - Unmanned aerial vehicle with pusher propeller and free flap fixed wing - Google Patents

Unmanned aerial vehicle with pusher propeller and free flap fixed wing Download PDF

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Publication number
KR20170061883A
KR20170061883A KR1020150167019A KR20150167019A KR20170061883A KR 20170061883 A KR20170061883 A KR 20170061883A KR 1020150167019 A KR1020150167019 A KR 1020150167019A KR 20150167019 A KR20150167019 A KR 20150167019A KR 20170061883 A KR20170061883 A KR 20170061883A
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KR
South Korea
Prior art keywords
driving
thrust
lifting
motor
wing
Prior art date
Application number
KR1020150167019A
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Korean (ko)
Inventor
이승우
Original Assignee
(주)지이에스
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Priority to KR1020150167019A priority Critical patent/KR20170061883A/en
Publication of KR20170061883A publication Critical patent/KR20170061883A/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C2201/021—
    • B64C2201/024—
    • B64C2201/104—
    • B64C2201/108—

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Toys (AREA)

Abstract

The present invention is intended to be used for surveillance, reconnaissance, and communication relaying, and is capable of vertical landing and hovering through a lifting portion by advancing through a thrust portion at the rear. The present invention relates to an unmanned aerial vehicle having a rear propeller, comprising: a body part having a fixed wing formed on the left and right sides and a vertical tail wing formed on the rear side; A plurality of lifting portions fixedly installed in a direction perpendicular to the forward and backward directions of the left and right fixed wings of the body portion, and a thrust portion formed at the rear of the body portion to generate a thrust force, wherein the body portion moves up and down, And is turned forward and backward through a thrust portion formed at the back of the trunk portion. The trunk portion is laterally reversed when the trunk portion is advanced and retracted through a vertical tail wing formed behind the trunk portion.

Description

Unmanned aerial vehicle with propeller and free flap fixed wing,

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an unmanned aerial vehicle having a flap-less fixed wing and a rear propeller, and more particularly, to an unmanned aerial vehicle having a flap and a rear propeller, The present invention relates to an unmanned aerial vehicle having a flap-free fixed wing and a rear propeller capable of flying by a floating wing of a fixed wing, hovering, and vertical takeoff and landing.

Generally, the unmanned airplane used for reconnaissance or communication relay is required to have an air time and speed, so it is common to use an aircraft having a wing.

Of course, you can use a quad copter such as a drones, but it is often necessary to use fixed wing unmanned airplanes because it is necessary to travel remotely and reconnaissance or communication relay.

These conventional aircraft generate thrust backward through the propulsion unit and continuously fly through the flaps formed on the wing. The aircraft propelled by the propulsion unit requires a runway to start the flight.

 All of the above-described configurations have flaps formed on the wings of an aircraft to change the direction thereof.

Patent Document 1 discloses a configuration in which a generator is connected to a rotor and a power source is charged in a battery to rotate the rotor.

1. Korean Patent Publication No. 10-2013-0095167 (Aug. 27, 2013)

The present invention is intended to be used for surveillance and reconnaissance, communication relay, and the like, and can be vertically landed and hovered through a lifting portion through a rear thrust portion. Thus, And an unmanned aircraft having a vertical tail wing and a rear propeller.

According to another aspect of the present invention, there is provided an unmanned aerial vehicle having a flap-less fixed wing and a rear propeller, the wing having a wing on the left and right sides and a vertical tail wing on the rear side; A plurality of lifting portions fixedly installed in a direction perpendicular to the forward and backward directions of the left and right fixed wings of the body portion, and a thrust portion formed at the rear of the body portion to generate a thrust force, wherein the body portion moves up and down, And is advanced through a thrust section formed at the rear of the trunk section. When the trunk section is advanced through the vertical tail wing formed behind the trunk section, the trunk section is laterally reversed.

Wherein the body part comprises: a control part for controlling the lifting part, the thrust part and the vertical tail wing; A first communication module connected to the controller to receive a control signal of the external controller and transmit the control signal to the controller; A driving unit configured by a first driving unit for driving the lifting unit, a second driving unit for driving the thrust unit, and a third driving unit for operating the vertical rudder of the vertical tail wing, and a power generator for generating electricity by driving the driving unit .

The lifting portion is formed in the front and rear direction of the left and right fixed wings of the body portion, the driving portion is coupled through the connecting rod so as to be perpendicular to the front and rear directions of the both side fixed wings, and the propeller is coupled to the upper end of the driving portion.

The yaw phenomenon of the body part caused by the rotation of the thrust part is prevented by the right and left rotation of the vertical rudder formed on the vertical tail wing, and the pitch, roll, Is adjusted through the lifting portion.

The present invention is characterized in that a buoyant portion is formed in the fore and aft direction of a fixed wing formed on the body portion and a thrust portion is formed in the rear of the body portion so that the buoyant portion can be hovered and lifted up and down through the buoyant portion, Excellent performance and low fuel consumption.

In addition, since the air-surface performance and fuel consumption are small, it can be used in an unmanned reconnaissance device or a communication repeater that requires a long flight time.

1 is a perspective view showing an unmanned aircraft having a flap-less fixed wing and a rear propeller according to an embodiment of the present invention.
2 is a view showing a configuration of a UAV having a flap-less fixed wing and a rear propeller according to the present invention.
3 is a plan view of an unmanned aerial vehicle having a flap-less fixed wing and a rear propeller according to the present invention.
4 is a side view of a UAV having a flap-less fixed wing and a rear propeller according to the present invention.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are not intended to limit the invention to the particular forms disclosed. And shall not interpret it.

1 is a view showing a configuration of an unmanned aircraft having a flap-less fixed wing and a rear propeller according to an embodiment of the present invention. The wing unit 10 has a fixed wing 11 on the right and left sides and a vertical tail wing 50 on the rear side. A plurality of lifting portions 20 fixedly installed in the front and rear direction of the fixed wing 11 and a thrusting portion 40 coupled to the rear of the moving body 10 to advance the moving body 10.

The body 10 is formed in the shape of a streamlined airplane body, and the fixed wings 11 are formed on both sides of the stop, and the vertical tail wing 50 is formed on the rear side.

A lifting portion 20 is formed in the front and rear direction of the left and right fixed wings 11 on the fixed wing 11 of the body 10.

The vertical tail wing 50 of the body part 10 is formed with a vertical rudder 51 so that it can change its direction when the body 10 is advanced and is inclined by the thrust part 40 yaw phenomenon can be prevented.

The fixed wing 11 of the body 10 is formed with no flap and is capable of generating lifting force when the body 10 is advanced through the thrust section 40. [

A lifting portion 20 is formed in the front and rear direction of the left and right fixed wings 11 so that the body 10 can be lifted and landed vertically and the body 10 can be hobbled in place. Pitch, top, bottom, left, right roll and front, rear, left and right sliding.

FIG. 2 is a view showing a configuration of a UAV having a flap-less fixed wing and a rear propeller according to the present invention, FIG. 3 is a plan view of an unmanned airplane having a flap-less fixed wing and a rear propeller according to the present invention, Is a side view of an unmanned aerial vehicle having a flap-less fixed wing and a rear propeller according to the present invention.

The lifting portion 20 has a structure in which a first driving body 31 of the driving portion 30 is coupled to a connecting rod connected to the fixed wing 11 and a propeller 21 is attached to the upper end of the first driving body 31 .

The first driving body 31 includes a first motor 31a and a second motor 31b formed on the front and rear sides of the left fixed wing 11 and a third motor 31b formed on the front and rear sides of the right fixed wing 11, A first motor 31c and a fourth motor 31d.

The driving body 30 further includes a second driving body 32 for driving the thrust section 40 at the rear of the body 10 and a second driving body 32 for driving the vertical tail wing 50, And a third driving body 33 for adjusting the driving force.

The second driving body 32 in the body 10 comprises a driving motor or a driving engine and is operated through electricity or fuel to rotate the thrust part 40.

The vertical rudder 51 of the vertical tail wing 50 is operated through an electric motor.

The lifting portion 20 includes a first motor 31a, a second motor 31b and a third motor 31c of the first driving body 31 provided on the front and rear sides of the left and right fixed wings 11, And a fourth motor 31d.

A propeller 21 is coupled to the upper side of the first motor 31a, the second motor 31b, the third motor 31c and the fourth motor 31d to generate a buoyant force by driving the propeller.

A duct for protecting the propeller 21 from being damaged by colliding with an external object may be coupled to the outside of the propeller 21 of the lifting unit 20.

The rotation speed of the first motor 31a to the fourth motor 31d of the lifting unit 20 is controlled by the control signal of the controller 60 so that the body 10 can be moved forward, backward, And so on.

A method of adjusting the direction through the lifting portion 20 is as follows.

The first motor 31a to the fourth motor 31d coupled to the front, back, right, and left four sides of the lifting unit 20 are controlled to change direction, rotate in place, and adjust sliding of the body 10.

The speed of the first motor 31a and the third motor 31c located on the front side of the fixed blade 11 is reduced and the speed of the fixed blade 11 is reduced. The speed of the second motor 31b and the fourth motor 31d installed at the rear side is increased to advance the body 10 in a forward inclined state.

The speed of the first motor 31a and the speed of the third motor 31c is increased while the speed of the second motor 31b and the speed of the fourth motor 31d is reduced to increase the speed of the moving body 10, So that it can be moved upward while being inclined upward.

The first motor 31a and the second motor 31b are decelerated and the third motor 31c and the fourth motor 31d are accelerated to be tilted to the left when the body 10 is moved to the left The first motor 31a and the second motor are accelerated and the third motor 31c and the fourth motor 31d are decelerated to be tilted to the right when the body 10 is moved to the right The lower body 10 moves to the right.

The vertical rudder 51 of the vertical tail wing 50 is adjusted when the body 10 is shifted in the lateral direction during the forward movement.

When the direction of the moving body 10 is rapidly shifted while the moving body 10 is moving in the front and left and right directions, when the opposite side lifting portion 20 in the corresponding direction is accelerated to be inclined in the direction to rotate the moving body 10, So that the moving body 10 can swing rapidly.

When the body 10 is rotated in place during hovering, two diagonal motors are accelerated and rotated.

The first motor 31a and the third motor 31c are operated to increase the speed of the second motor 31b and the fourth motor in order to cause the body 10 to turn to the left, It can be increased.

The reason why the second motor 31b can rotate in the above-described manner is that the second motor 31b and the fourth motor 31d are rotated in the same clockwise direction and the first motor 31a and the third motor 31c rotate in the counterclockwise direction .

Each motor of the first driving body 31 of the lifting unit 20 may be rotated in the opposite direction, and in this case, the motor is rotated in the opposite direction.

When the body 10 slides in any one of the forward, backward, and leftward directions, the motor in the sliding direction is accelerated and hovered in place.

The attitude control such as moving and hovering of the body 10 is performed through a flight control computer using position information measured by a three-axis acceleration sensor, a three-axis gyroscope, an air pressure sensor, a ground sensor, and a GPS sensor.

The first driving body 31 of the lifting portion 20 may be operated using the power source of the battery 63 of the power portion and the motor may be constituted of the engine and operated through the fuel of the fuel tank.

The thrust section 40 is formed behind the moving body 10 and is driven by the second driving body 32. The thrust propeller 21 is formed so as to move the moving body 10 forward or backward.

The vertical rudder 51 formed on the vertical tail wing 50 of the body part 10 is rotated in the left and right direction through the third drive body 33 to control the yaw phenomenon of the body part 10, And controls the direction change of the moving body 10 at the time of advancing.

The third driving body 33 may be an electric motor or an engine.

The control unit 60 is connected to the driving unit 30 that drives the lifting unit 20, the vertical rudder 51 and the thrust unit 40 to control the operation of the driving unit 30.

The control unit 60 is connected to the first communication module 61 so that the control unit 60 can control the driving unit 30 through the steering signal transmitted from the external manipulator 70. The state of the driving unit 30 Information is transmitted to the external manipulator 70 for display.

The power generation unit 62 is connected to the driving unit 30 to generate power and the power generated by the power generation unit 62 is stored in the battery 63 to apply power to the control unit 60 and the driving unit 30 . Power generation of the power generation unit 62 is performed by transmitting a rotational force between the engine rotation shaft and the rotation shaft of the generator through a chain or a gear when the engine is used as thrust.

The external manipulator 70 that transmits the manipulation signal through the wireless communication to the first communication module 61 includes an input means input by the user and an input signal of the input means 72 for manipulating the body 10, A control unit 71 that receives the control signal and wirelessly transmits the control signal through the second communication module 74; a driving unit 30 that is transmitted from the control unit 60 of the moving body 10 through the first communication module 61; And a second communication module 74 for wirelessly transmitting the control signal of the control unit 71 to the first communication module 61. [

When the operation of the body 10 is controlled by the external controller 70 through the input means 72, the input signal inputted through the input means 72 is displayed on the display unit 73, The display unit 73 receives the status signal of the display unit 30 and displays the status signal.

According to the present invention, as described above, according to the present invention, a buoyant portion is formed in the fore and aft direction of a fixed wing formed on a body portion, and a thrust portion is formed in the rear of the body portion to fly by the buoyant force of the wing, It is possible to achieve excellent air-tightness performance and low fuel consumption.

In addition, since the performance and the fuel consumption are small, it can be used in surveillance and reconnaissance or communication relaying that requires a long flight.

The unmanned aircraft having the flap-less fixed wing and the rear propeller as described above is not limited to the configuration and the manner of operation of the embodiments described above. The above embodiments may be configured so that all or some of the embodiments may be selectively combined to make various modifications.

10: body part 11: fixed wing
20: lifting part 21: propeller
30: driving unit 31: first driving unit
31a: first motor 31b: second motor
31c: third motor 31d: fourth motor
32: second driving body 33: third driving body
40: Thrust section 41: Thrust propeller
50: vertical tail wing 51: vertical rudder
60: control unit 61: first communication module
62: power generator 63: battery
70; External controller 71:
72: input means 73: display
74: Second communication module

Claims (4)

A body part having a fixed wing formed on the left and right sides and a vertical tail wing formed on the rear side;
A plurality of lifting portions provided on both sides of the fixed wings in forward and backward directions,
And a thrust section formed at the rear of the trunk section to generate a thrust force,
When the body part moves forward and backward through the vertical tail wing formed at the rear of the body part, the body part moves forward and backward through the lifting, Wherein the unmanned aircraft has a flap-free fixed wing and a rear propeller. The method according to claim 1,
The body part,
A control unit for controlling the lifting unit, the thrust unit, and the vertical tail wing;
A first communication module connected to the controller to receive a control signal of the external controller and transmit the control signal to the controller;
A driving unit configured by a first driving body for driving the lifting portion, a second driving body for driving the thrust portion, and a third driving body for driving a vertical rudder of the vertical tail wing,
And a power generating unit that generates power through driving of the driving unit. The method according to claim 1,
Wherein the lifting portion is coupled to the driving portion through a connecting rod so that the lifting portion is directed in a direction perpendicular to the longitudinal direction of the both side fixed wings, and a propeller is coupled to the upper end of the driving portion. The method according to claim 1,
The yaw phenomenon in one direction of the trunk portion generated by the rotation of the thrust portion is prevented through a leftward and rightward rotation of a vertical rudder formed on the vertical tail wing and the pitch, Wherein the sliding in the front, rear, and left directions is controlled through a lifting portion, and the unmanned aircraft having a flap-free fixed wing and a rear propeller.
KR1020150167019A 2015-11-27 2015-11-27 Unmanned aerial vehicle with pusher propeller and free flap fixed wing KR20170061883A (en)

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KR1020150167019A KR20170061883A (en) 2015-11-27 2015-11-27 Unmanned aerial vehicle with pusher propeller and free flap fixed wing

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KR1020150167019A KR20170061883A (en) 2015-11-27 2015-11-27 Unmanned aerial vehicle with pusher propeller and free flap fixed wing

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KR20170061883A true KR20170061883A (en) 2017-06-07

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019190263A1 (en) * 2018-03-29 2019-10-03 이호형 Improved hybrid drone
CN113353270A (en) * 2021-08-11 2021-09-07 西安羚控电子科技有限公司 Power system and flight device with same
JP2022016568A (en) * 2020-02-27 2022-01-21 義郎 中松 Wing rotation vertical takeoff/landing long distance aircraft
CN114056542A (en) * 2021-08-13 2022-02-18 南京晓飞智能科技有限公司 Many rotor unmanned aerial vehicle of combined type
KR20230032404A (en) * 2021-08-31 2023-03-07 (주)넥스컴스 VTOL Unmanned Aerial Vehicle

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019190263A1 (en) * 2018-03-29 2019-10-03 이호형 Improved hybrid drone
JP2022016568A (en) * 2020-02-27 2022-01-21 義郎 中松 Wing rotation vertical takeoff/landing long distance aircraft
CN113353270A (en) * 2021-08-11 2021-09-07 西安羚控电子科技有限公司 Power system and flight device with same
CN114056542A (en) * 2021-08-13 2022-02-18 南京晓飞智能科技有限公司 Many rotor unmanned aerial vehicle of combined type
KR20230032404A (en) * 2021-08-31 2023-03-07 (주)넥스컴스 VTOL Unmanned Aerial Vehicle

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