KR101654507B1 - Variable pitch type drone using a belt structure - Google Patents

Variable pitch type drone using a belt structure Download PDF

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Publication number
KR101654507B1
KR101654507B1 KR1020160038303A KR20160038303A KR101654507B1 KR 101654507 B1 KR101654507 B1 KR 101654507B1 KR 1020160038303 A KR1020160038303 A KR 1020160038303A KR 20160038303 A KR20160038303 A KR 20160038303A KR 101654507 B1 KR101654507 B1 KR 101654507B1
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KR
South Korea
Prior art keywords
unit
rotational force
rotation
rotor
driving
Prior art date
Application number
KR1020160038303A
Other languages
Korean (ko)
Inventor
김무선
Original Assignee
(주)한국유에이브이
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Publication date
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Priority to KR1020160038303A priority Critical patent/KR101654507B1/en
Application granted granted Critical
Publication of KR101654507B1 publication Critical patent/KR101654507B1/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
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/32—Blade pitch-changing mechanisms mechanical
    • 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
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H7/00—Gearings for conveying rotary motion by endless flexible members
    • F16H7/02—Gearings for conveying rotary motion by endless flexible members with belts; with V-belts
    • B64C2201/024—
    • B64C2201/04—
    • B64C2201/108—
    • B64C2201/165—
    • B64C2700/628—
    • B64C2700/6284—

Abstract

The present invention relates to a variable pitch unmanned aerial vehicle using a belt structure, and more particularly, to a variable pitch unmanned aerial vehicle using a belt structure, comprising: driving means for providing a turning force for flight of an unmanned aerial vehicle; a fan driving portion for driving a cooling fan for cooling each cylinder of the driving means; An engine part including a drive control part for controlling whether or not the part is driven; At least two or more of the power transmitting members are connected to the outer circumferential surface of the transmission shaft so that the rotational force of the transmission shaft is transmitted to the rotor, A thrust regulating portion including a rotational force providing means for respectively providing the subordinate side and the subordinate side; A rotor unit that rotates the propeller of the unmanned air vehicle using the rotational force transmitted through the thrust control unit and controls the pitch angle of the propeller; And a flying body formed of an engine main body in which the engine unit is embedded and in which a lower surface of the rotor unit is embedded and an upper main body unit coupled to an upper portion of the engine main body and receiving the thrust control unit and the rotor unit .

Description

[0001] The present invention relates to a variable pitch type unmanned vehicle using a belt structure,

The present invention relates to a variable pitch unmanned aerial vehicle using a belt structure. More particularly, the present invention relates to a variable pitch unmanned vehicle having a belt structure capable of flying a unmanned aerial vehicle having various structures by using only one engine, by converting the axial direction of the rotational force to a rotating belt that transmits rotational force, It is about flying.

Generally, unmanned aerial vehicles, also called "drones", are helicopter-shaped unmanned aerial vehicles that fly by induction of radio waves without people burning, but they have recently been used for military use, .

In particular, the need for unmanned aerial vehicles is increasing in an environment where people can not work in recent years. Unmanned aerial vehicles (UAVs) are increasingly required to provide information on enemy cloaking in aerial image acquisition, aerial photographing, powerline inspection or battlefield situations in disaster / disaster areas, or to carry out reconnaissance missions and surveillance missions through unmanned aerial vehicles .

The conventional unmanned airplane is disclosed in Korean Patent No. 10-1366208. This allows the user to conveniently move, assemble, and disassemble the air vehicle, and the first and second fixing members formed on the lower fixing member can be used for the landing gear unit And the landing gear is firmly fixed to the lower fixing part, thereby preventing further shaking or distortion when the airplane is in flight.

Also, it has been disclosed in Korean Patent No. 10-1100401. The above-mentioned prior art relates to an apparatus for adjusting the pitch of a rotor blade in a tiltrotor aircraft, wherein a variable rotor is used to optimally adjust the pitch according to a flight condition such as a cruising condition or an altitude in a tiltrotor aircraft having both advantages of a fixed- .

The tiltrotor aircraft has the advantage of maximizing flight efficiency in each flight mode through such a conventional pitch control device. However, such a pitch adjustment device is not limited to a plurality of components such as an actuator, an actuator link and a gearbox Because it is composed, the airframe and the rotor have to be formed over a certain size.

Therefore, it has disadvantages that it can be used only for medium and large sized aircraft due to the limitation of load and size. In addition, maintenance was difficult because several components were used. In recent years, the demand for small aircraft has been increasing, and since the unmanned aerial vehicle is used in various fields, it can be miniaturized to have a simplified component than the components used in the prior art, and can be used for a small or unmanned aircraft, There is a need for an increased blade pitch adjusting device.

Particularly, when the unmanned aerial vehicle performs translational motion, there is a problem that an unwanted rotational motion is inevitably generated.

For example, in the case of adjusting the distance and height of unmanned aerial vehicles located at front, rear, top, bottom, left, and right sides of a cluster flight with several parties, there is a risk of collision with each other due to the occurrence of rotational movement, When docking, it takes much time to dock due to rotational movement, or there is a risk of collision with each other, or when performing various tasks or tasks between the public grounds such as image shooting, And problems such as difficulty and long working time.

delete

Korean Patent No. 10-1366208

In order to solve such problems, it is an object of the present invention to provide a variable pitch unmanned aerial vehicle using a gasoline engine having a cooling system or a belt structure that can be driven for a long time by using a driving motor or the like.

In addition, the present invention provides a variable pitch type belt structure capable of flying a unmanned aerial vehicle having various structures by using only one engine by converting the axial direction of the rotational force to a rotating belt that transmits rotational force, It is intended to provide unmanned aerial vehicles.

According to an aspect of the present invention, there is provided a control method for an air conditioner, comprising: driving means for providing a rotational force for flight of an unmanned air vehicle; a fan driving portion for driving a cooling fan for cooling each cylinder of the driving means; An engine unit including a drive control unit; At least two or more of the power transmitting members are connected to the outer circumferential surface of the transmission shaft so that the rotational force of the transmission shaft is transmitted to the rotor, A thrust regulating portion including a rotational force providing means for respectively providing the subordinate side and the subordinate side; A rotor unit that rotates the propeller of the unmanned air vehicle using the rotational force transmitted through the thrust control unit and controls the pitch angle of the propeller; And a flying body formed of an engine main body in which the engine unit is embedded and in which a lower surface of the rotor unit is embedded and an upper main body unit coupled to an upper portion of the engine main body and receiving the thrust control unit and the rotor unit .

In addition, the present invention is characterized in that the transmission shaft is further coupled to the rotational force providing means on an outer circumferential surface thereof, and further comprises a rotation shaft for transmitting a rotational force of the transmission shaft.

In addition, the present invention is characterized in that the rotating shaft and the rotational force providing means simultaneously rotate the propeller of the unmanned aerial vehicle including the quadcopter, the hexacopter, and the octocopter, which are classified according to the number of the propellers.

The power transmitting member may include a connecting member that is formed on one surface of the transmission shaft and transmits the rotational force of the driving unit, a rotation driving unit that is provided at an end of the driving unit and provides rotational force of the driving unit, A transmission belt connecting the connection member and the rotation drive unit to transmit the rotation force of the rotation drive unit to the connection member, and a clutch member formed on one surface of the rotation drive unit and controlling the rotation speed of the rotation drive unit.

Further, in the present invention, the connecting member is installed at the front end of the transmission shaft, on one side of the outer circumference or at the center of the center of gravity of the unmanned air vehicle.

Further, the present invention is characterized in that the rotation force providing means includes a rotation support portion coupled to the transmission shaft, and a rotation belt connecting the rotation support portion and the rotor portion to transmit the rotation force of the transmission shaft to the rotor portion side to rotate the plurality of propellers .

Further, the present invention is characterized in that the rotation belt is provided with a twist portion which is twisted by a certain angle in order to convert an axial rotational force in the rotational direction of the transmission shaft and transmit the rotational force to the propeller driving shaft of the rotor portion.

Further, the present invention is characterized in that the rotation belt further comprises a tension holding member for preventing the tension of the twist portion from lowering.

In addition, the drive control unit is configured such that the rotational speed and the pitch angle of the propeller can be simultaneously controlled while the thrust control unit and the rotor unit are simultaneously driven.

According to the present invention, a gasoline engine or a drive motor having a cooling system can be used, and combustion with high efficiency can be performed even with a small amount of fuel, so that the vehicle can be operated for a long time.

In addition, according to the present invention, since the axial direction of the rotational force is changed on the rotating belt for transmitting the rotational force to transmit the power more easily, it is possible to fly the unmanned air vehicle having various structures with only one engine, Can be maximized.

1 is a perspective view schematically showing a variable pitch unmanned aerial vehicle according to the present invention,
2 is a schematic view of a thrust control unit of the unmanned aerial vehicle according to the present invention,
3 is a perspective view schematically showing a rotational force providing means of the thrust adjusting portion of the present invention,
4 is an exemplary view schematically showing the structure of each type of torque providing means of the present invention,
5 and 6 are views showing a rotating operation state of the rotor part of the unmanned aerial vehicle according to the present invention,
7 is a view showing an engine unit of the unmanned aerial vehicle according to the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the drawings, the same reference numerals are used to designate the same or similar components throughout the drawings. In the following description of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear.

FIG. 1 is a perspective view schematically showing a variable pitch unmanned aerial vehicle according to the present invention, FIG. 2 is a schematic view of a thrust control unit of an unmanned aerial vehicle of the present invention, and FIG. 3 is a schematic view of a torque- FIG. 5 is a perspective view of the unmanned aerial vehicle according to the first embodiment of the present invention. FIG. 5 is a perspective view of the unmanned aerial vehicle according to the present invention. Fig.

As shown in the figure, the unmanned aerial vehicle of the present invention includes a flight main body 100, a thrust control unit 200, a rotor unit 300, and an engine unit 400.

The engine 100 includes an engine main body 110 in which a driving means 410 is installed at a lower portion and a fuel storage tank 420 in which fuel required for driving a unmanned air vehicle such as gasoline is stored is coupled, And an upper main body 120 detachably coupled to an upper portion of the main body 110 and having a thrust regulating portion 200 for driving the rotor portion 300 therein.

The driving unit 410 includes a driving unit 410 for driving the rotor unit 300 by rotating the thrust adjusting unit 200. The driving unit 410 drives the driving unit 410, And a power supply unit for supplying power to the cooling fan 412 configured in the power supply unit 410.

The engine body 110 has a top surface shape corresponding to a lower surface of the upper body 120 and is configured to accommodate a rotor arm 310 of a rotor unit 300 to be described later.

The upper body portion 120 functions as a lid for sealing the upper portion of the engine body portion 110 and is mounted with a thrust force control portion 200. The thrust force control portion 200 and the rotor portion of the rotor portion 300 The arm portion 310 is connected to the rotor arm portion 310 so that rotation and pitch of the propeller can be adjusted.

In addition, the upper body portion 120 of the present invention includes an operation means (not shown) for providing a rotational force for adjusting a pitch angle of a propeller provided in a rotor portion 300, which will be described later, 300, the number of which is at least two.

The upper body 120 of the present invention further includes an electronic controller (not shown) for controlling the operation of the rotor unit 300 and the driving unit 410 to control the flight of the unmanned aerial vehicle It is preferable that the pitch angle of the propeller is controlled while the signals are transmitted and received, and the electronic control unit is controlled under the control of the drive control unit 450.

The thrust adjusting unit 200 controls the rotational speed of the propeller so that the rotational operation of the rotor unit 300 is performed. The thrust adjusting unit 200 includes a transmission shaft 210 connected to the driving unit 410 to provide a predetermined rotational force, At least two or more of the power transmission members 220 are connected to the outer circumferential surface of the transmission shaft 210 so that the rotational force of the transmission shaft 210 is transmitted to the rotor arm 310 side And a rotational force providing means (320) for providing the rotational force.

One side of the transmission shaft 210 is connected to the driving means 410 through the power transmitting member 220 and is a component for transmitting the rotational force of the driving means 410 to the rotational force providing means 230 side.

The transmission shaft 210 is coupled to the rotation support portion 232 of the rotation force providing means 230 on the outer circumferential surface thereof and a rotation shaft 212 for transmitting the rotation force of the transmission shaft 210 to the rotation support portion 232 side is formed.

That is, the rotation support portion 232 is coupled to the outer circumferential surface of the rotation shaft 212, and the rotation support portion 232 rotates in the same direction as the rotation shaft 212 and transmits the rotation force of the transmission shaft 210 to the rotation belt 234 .

As shown in FIGS. 2 and 4, the rotating shaft 212 can operate a unmanned flight such as a quad copter, a hexacopter, and an octopus, which is classified according to the number of propellers by only one driving unit 410 For example, the rotary shaft 212 is formed on the outer circumferential surface of the transmission shaft 210 in two, four, eight, or the like, And configured to rotate the propellers individually.

The power transmitting member 220 is connected to the driving unit 410 so that the connecting member 222 is configured to rotate in one direction when the driving unit 410 is driven.

The connecting member 222 is a component that connects the transmission shaft 210 to the driving means 410 by being installed at the front end of the transmission shaft 210 or at one side or the center of the outer circumference along the center of gravity of the UAV.

The connecting member 222 may be a pulley or the like to be coupled to the transmission belt 224 for transmitting the rotational force of the driving means 410. However, the present invention is not limited thereto, and when the transmission belt 224 is gear- And a gear structure corresponding thereto.

The power transmitting member 220 is connected to an end of the driving unit 410 to constitute a rotation driving unit 226 that provides the rotational force of the driving unit 410 to the transmission belt 224 side.

The rotation drive unit 226 is configured to be axially coupled to the drive unit 410 and may be a pulley or a gear structure for transmitting the rotational force of the drive unit 410 to the transfer belt 224.

The power transmitting member 220 is provided with a clutch member (not shown) for controlling the rotational speed of the rotational driving unit 226 and the rotational transmitting force of the transmitting belt 224 to control the rotational speed of the propeller through the transmitting shaft 210 228).

In this case, it is needless to say that the clutch member 228 controls the rotation of the rotation driving unit 226 so that the rotational force provided from the driving unit 410 can be transmitted or intercepted.

This clutch member 228 can be controlled by an electronic control unit and can be made of a hydraulic clutch.

The transmission belt 224 of the power transmitting member 220 of the present invention connects the rotation driving unit 226 and the connecting member 222 to transmit the rotational force of the driving unit 410 to the transmission shaft 210 And may be a conventional belt structure or a gear structure.

The rotational force providing means 230 of the present invention is rotatably coupled to the transmission shaft 210 to transmit the rotational force of the transmission shaft 210 to the propeller driving shaft 320 of the rotor unit 300.

The rotational force providing means 230 includes a rotation support portion 232 coupled to the rotation shaft 212 of the transmission shaft 210 and a rotation support portion 232 rotatably coupled to the rotation support portion 232, And a rotary belt 234 for transmitting the rotation to the side of the roller 320.

As shown in FIG. 3, the rotary belt 234 transmits the rotation direction transmitted from the horizontal transmission shaft 210 to the propeller drive shaft 320 having a vertical structure to rotate the propeller And a twist portion is formed at a predetermined angle.

That is, the rotary belt 234 of the present invention is installed in the flight main body 100 in the X-axis direction in which the transmission shaft 210 is horizontal and when a predetermined rotational force is transmitted from the driving means 410, The propeller drive shaft 320 is mounted in the Y'-axis direction so as to perform a rotary operation on the lower portion of the propeller, and the rotary operation in the X'-axis direction must be performed.

In order to transmit rotation force of the transmission shaft 210 to the propeller drive shaft 320, the rotation belt 234 rotates the Z axis rotation direction of the transmission shaft 210 orthogonal to the X axis of the propeller drive shaft 320 Direction, and are configured to rotate in different axial directions.

That is, the twisted portion formed on the rotary belt 234 is configured to convert the axial rotational force of the transmission shaft 210 to the axial rotational force of the propeller driving shaft 320 to transmit the power.

On the other hand, in the rotating belt 234 of the present invention, a tension holding member 240 is further provided to prevent the tension of the twist portion, which changes the rotating direction of the rotating belt 234, from lowering, It will be possible.

At this time, the tension holding member 240 can be constituted of a component that can prevent the tension from being lowered in the section where the twisting is performed while supporting the rotation operation of the rotation belt 234 such as a roller, a shaft member, and the like.

The rotor unit 300 is a component that connects the propeller and the thrust regulating unit 200 so as to rotate the propeller through the rotational force transmitted from the thrust regulating unit 200 and to adjust the pitch angle of the propeller .

The rotor portion 300 includes a propeller driving shaft 234 which is connected to an end portion of the rotary belt 234 and rotates the propeller by the rotational force of the rotary belt 234, And a pitch adjusting unit 340 coupled to the rotor arm 310 and the propeller driving shaft 320 to adjust the pitch angle of the propeller.

The rotor arm unit 310 of the present invention supports the forward and reverse rotational forces by the operation of the rotary belt 234 and allows the propeller drive shaft 320 to rotate by a certain angle in the circumferential direction, The second rotation supporting portion 322 may be configured to attenuate the rotation and minimize the loss of lifting force.

The propeller drive shaft 320 is connected to the upper end of the propeller drive shaft 320 to form a connection coupler 330 that drives the propeller by the rotation of the propeller drive shaft 320.

Here, the connection coupler 330 is connected to the pitch housing 348 of the pitch control unit 340, which will be described later. When the pitch housing 348 is operated, the connection coupler 330 rotates by a certain angle in the axial direction of the connection coupler 330, So that the pitch angle can be adjusted.

The pitch adjusting unit 340 is a component for changing the pitch of the propeller rotating at the same speed to generate different thrusts. The pitch adjusting unit 340 includes a cylinder member or a servo motor so that the pitch of each propeller can be independently controlled. (Not shown) are individually constructed.

The pitch adjusting unit 340 operates the pitch adjusting unit 346 while the guide member 344 is rotated by the driving force generated in one direction by the electronic control unit or the driving control unit 450 So that the pitch housing 348 combined with the pitch adjusting means 346 is lifted or lowered.

At this time, the pitch housing 348 is operated to move up and down the upper part of the pitch housing 348 to rotate the connecting coupler 330 to adjust the pitch angle of the propeller.

The engine unit 400 includes the air-cooling type driving unit 410, and the cooling fan 412 is installed in each cylinder to prevent a failure due to overheating of the engine.

The engine unit 400 includes a drive means 410 for driving the drive shaft 202, a fuel storage tank 420 for supplying fuel to the drive means 410 side, A fan driving unit 430 for driving the cooling fan 412 and a drive control unit 450 for controlling whether the engine 400 is driven or not.

The driving unit 410 provides a predetermined power source for flying the unmanned aerial vehicle, and is configured to simultaneously drive the plurality of rotor units 300 constituted by the engine main unit 110.

In other words, conventionally, the number of drive units 410 corresponding to the rotor unit 300 is required to individually control each of the rotor units 300, so that the flight efficiency is deteriorated due to the consumption of the fuel and the weight of the unmanned aerial vehicle However, the present invention can overcome the problems of the related art by simultaneously rotating the plurality of the rotor units 300 using one driving unit 410.

The fan driving unit 430 of the present invention is configured such that the pulley and the belt 432 and the cooling shaft 434 are connected to the driving shaft 202 connected to the driving unit 410, And the fan 412 is driven.

In addition, the fan driving unit 430 may further include a cylinder cooling cover 436 for cooling the cylinder, thereby maximizing the cooling efficiency of the cylinder by increasing the flow speed of the wind.

The foregoing description is merely illustrative of the technical idea of the present invention and various changes and modifications may be made by those skilled in the art without departing from the essential characteristics of the present invention. Therefore, the embodiments disclosed in the present invention are intended to illustrate rather than limit the scope of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.

100: flying main body 110: engine main body
120: upper body part 200: thrust force adjusting part
210: transmission shaft 220: power transmission member
230: rotational force providing means 300:
310: rotor arm portion 320: propeller drive shaft
330: connecting coupler 340: pitch adjusting section
400: engine unit 410: driving means
420: Fuel storage tank 430: Fan drive unit
450:

Claims (9)

An engine unit including driving means for providing a rotational force for flight of the unmanned aerial vehicle, a fan driving unit for driving a cooling fan for cooling each cylinder of the driving means, and a drive control unit for controlling whether the engine is driven or not;
At least two or more of the power transmitting members are connected to the outer circumferential surface of the transmission shaft so that the rotational force of the transmission shaft is transmitted to the rotor, A thrust regulating portion including a rotational force providing means for respectively providing the subordinate side and the subordinate side;
A rotor unit that rotates the propeller of the unmanned air vehicle using the rotational force transmitted through the thrust control unit and controls the pitch angle of the propeller;
And a flight main body including an engine main body in which the engine part is embedded and in which a lower surface of the rotor part is embedded, and an upper main body part coupled to an upper part of the engine main body part and receiving the thrust control part and the rotor part,
The power transmitting member includes:
A connecting member that is formed on one surface of the transmission shaft and transmits a rotational force of the driving unit,
A rotation driving unit provided at an end of the driving unit and providing a rotational force of the driving unit;
A transmission belt connecting the connection member and the rotation drive unit to transmit the rotation force of the rotation drive unit to the connection member,
And a clutch member provided on one surface of the rotation driving unit for controlling the rotation speed of the rotation driving unit,
The variable pitch type driving means unmanned vehicle using the belt structure according to claim 1,
The method according to claim 1,
The transfer shaft
Wherein the rotational force providing means is coupled to the outer circumferential surface and further comprises a rotational shaft for transmitting the rotational force of the transmitting shaft.
3. The method of claim 2,
Wherein the rotating shaft and the rotational force providing means simultaneously rotate the propeller of the unmanned aerial vehicle including the quad copter, the hexacopter, and the octocopter, which are classified according to the number of the propellers.
delete The method according to claim 1,
Wherein the connecting member is installed at a front end of the transmission shaft along one side of the center of gravity of the unmanned aerial vehicle, or on one side of the outer circumference or on the center side of the unmanned air vehicle.
The method according to claim 1,
The rotational force providing means
A rotation support unit coupled to the transmission shaft,
And a plurality of propellers for rotating the plurality of propellers by connecting rotation support portions and the rotor portions to transmit rotation forces of the transmission shafts to the rotor portions,
The variable pitch unmanned aerial vehicle using the belt structure according to claim 1,
The method according to claim 6,
Wherein the rotation belt is formed with a twist portion which is twisted by a predetermined angle to convert an axial rotational force in the rotational direction of the transmission shaft and transmit the rotational force to the propeller driving shaft of the rotor portion.
8. The method of claim 7,
Wherein the rotating belt further comprises a tension holding member for preventing the tension of the twist portion from being lowered.
The method according to claim 1,
Wherein the drive control unit is configured to simultaneously control the rotation speed and the pitch angle of the propeller while the thrust control unit and the rotor unit are simultaneously driven.
KR1020160038303A 2016-03-30 2016-03-30 Variable pitch type drone using a belt structure KR101654507B1 (en)

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Application Number Priority Date Filing Date Title
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108202872A (en) * 2018-02-09 2018-06-26 云南优航无人机科技有限公司 A kind of driving mechanism of multi-rotor unmanned aerial vehicle
CN110382356A (en) * 2018-04-23 2019-10-25 深圳市大疆创新科技有限公司 The Power Component and unmanned plane of unmanned plane

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100812755B1 (en) * 2006-11-13 2008-03-12 한국생산기술연구원 Quadro copter
KR101366310B1 (en) * 2012-09-03 2014-02-21 한국항공대학교산학협력단 Multi-copter
KR101366208B1 (en) 2013-05-02 2014-02-25 주식회사 네스앤텍 Multi-rotor type small aircraft

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100812755B1 (en) * 2006-11-13 2008-03-12 한국생산기술연구원 Quadro copter
KR101366310B1 (en) * 2012-09-03 2014-02-21 한국항공대학교산학협력단 Multi-copter
KR101366208B1 (en) 2013-05-02 2014-02-25 주식회사 네스앤텍 Multi-rotor type small aircraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108202872A (en) * 2018-02-09 2018-06-26 云南优航无人机科技有限公司 A kind of driving mechanism of multi-rotor unmanned aerial vehicle
CN110382356A (en) * 2018-04-23 2019-10-25 深圳市大疆创新科技有限公司 The Power Component and unmanned plane of unmanned plane
WO2019204956A1 (en) * 2018-04-23 2019-10-31 深圳市大疆创新科技有限公司 Power component of unmanned aerial vehicle, and unmanned aerial vehicle
CN110382356B (en) * 2018-04-23 2022-04-08 深圳市大疆创新科技有限公司 Unmanned aerial vehicle's power component and unmanned aerial vehicle

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