KR20170072069A - Multi-purpose hybrid VTOL UAV with a detachable wings - Google Patents

Multi-purpose hybrid VTOL UAV with a detachable wings Download PDF

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Publication number
KR20170072069A
KR20170072069A KR1020150180462A KR20150180462A KR20170072069A KR 20170072069 A KR20170072069 A KR 20170072069A KR 1020150180462 A KR1020150180462 A KR 1020150180462A KR 20150180462 A KR20150180462 A KR 20150180462A KR 20170072069 A KR20170072069 A KR 20170072069A
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KR
South Korea
Prior art keywords
wing
landing
tail
wing portion
aerial vehicle
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KR1020150180462A
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Korean (ko)
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KR101776954B1 (en
Inventor
민경무
딥 카프레 마샬
버트라이 니케시
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주식회사 샘코
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Priority to KR1020150180462A priority Critical patent/KR101776954B1/en
Publication of KR20170072069A publication Critical patent/KR20170072069A/en
Application granted granted Critical
Publication of KR101776954B1 publication Critical patent/KR101776954B1/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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/02—Tailplanes
    • B64C2201/021—
    • B64C2201/022—
    • B64C2201/102—
    • B64C2201/108—

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

Abstract

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a vertical take-off and landing unmanned aerial vehicle, and more particularly, to a vertical take-off landing unmanned aerial vehicle having a detachable wing that can be easily changed in structure to perform both low-
The multipurpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention is characterized in that it comprises a body part provided in a streamline shape, a main wing part provided on both sides of the center part of the body part, A lift generating portion provided on the rotor supporting portion and generating a wind to vertically float the body portion on the ground, and a lift generating portion provided on the rear surface of the body portion so that the body can be moved in a horizontal direction A tail wing portion provided on a rear surface of the rotor supporting portion, and a landing portion provided on a lower portion of the body portion to support the ground surface.
The multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention is capable of mounting and detaching the main wing and the tail wing to effectively perform the fixed wing flight and the flywheel flight.

Description

 {Multi-purpose hybrid VTOL UAV with a detachable wings}

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a vertical take-off and landing unmanned aerial vehicle, and more particularly, to a vertical take-off landing unmanned aerial vehicle having a detachable wing that can be easily changed in structure to perform both low-

Generally, the unmanned airplane has a fixed structure in the form of a flywheel aircraft or a fixed wing aircraft, which is insufficient to perform various missions. In order to solve this problem, a hybrid vertical take-off and landing unmanned aerial vehicle has been developed which is composed of a fixed-wing aircraft type rotor and a rotor type rotor, both of which are characterized by a rotary wing aircraft and a fixed wing aircraft. There is a lack of a single wing structure in order to effectively perform all of them.

In this regard, in the related art, a vertical take-off and landing aircraft using a variable-type flywheel is disclosed in Korean Patent Laid-Open No. 10-2009-0057504. However, in order to alleviate the characteristics of a fixed-wing aircraft and a rotor- However, at the time of flight, the angle-controlled rotor may interfere with the generation of lifting force, and it is difficult to fly due to the weight of the rotor due to a large number of rotors.

Korean Registered Patent No. 10-2009-0057504 (2009.06.08)

SUMMARY OF THE INVENTION Accordingly, the present invention has been made keeping in mind the above problems occurring in the prior art, and an object of the present invention is to provide a vertical take-off and landing unmanned aerial vehicle capable of simultaneously performing flywheel flying and fixed wing flying through mounting and detachment of a main wing and a tail wing It has its purpose.

The problems to be solved by the present invention are not limited to the above-mentioned problems, and other problems to be solved by the present invention, which are not mentioned here, As will be appreciated by those skilled in the art.

The multipurpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention is characterized in that it comprises a body part provided in a streamline shape, a main wing part provided on both sides of the center part of the body part, A lift generating portion provided on the rotor supporting portion and generating a wind to vertically float the body portion on the ground surface, and a lift generating portion provided on the rear surface of the body portion to allow the body portion to move in a horizontal direction A tail wing portion provided on a rear surface of the rotor supporting portion, and a landing portion provided on a lower portion of the body portion to support the ground surface.

The multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention has an effect that the main wing and the tail wing can be mounted and detached so that the wing fly and the flywheel fly can be effectively performed.

1 is a perspective view of a multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having a detachable wing according to the present invention in a state where a long wing portion and a tail wing portion are mounted;
FIG. 2 is a plan view of a multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having a detachable wing according to the present invention, in a state where a long wing portion and a tail wing portion are mounted.
FIG. 3 is a plan view of the multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention in a state where the intestinal detachable wing portion and the tail wing portion are detached.
FIG. 4 is a perspective view of a multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having a detachable wing according to the present invention, in which landing wings and tail wings are mounted.
5 is a plan view of a multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having a detachable wing according to the present invention, in which landing wings and tail wings are mounted;
FIG. 6 is a front view of a multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having a detachable wing according to the present invention in a state where landing wings and tail wings are mounted.
FIG. 7 is a perspective view of a landing wing of a multipurpose hybrid vertical take-off and landing unmanned aerial vehicle having a detachable wing according to the present invention, with the tail wing detached.

The above and other objects, features and advantages of the present invention will be more apparent from the following detailed description taken in conjunction with the accompanying drawings, in which: FIG. BRIEF DESCRIPTION OF THE DRAWINGS The advantages and features of the present invention, and the manner of achieving them, will be apparent from and elucidated with reference to the embodiments described hereinafter in conjunction with the accompanying drawings.

As shown in FIG. 1, the multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention includes a body 10 provided in a streamlined form, a main wing 20 provided on both sides of the center of the body 10, A rotor supporting portion 30 formed in a shape of traversing the main wing portion 20 and parallel to both sides of the traveling direction of the moving body 10, A lift generating unit 40 provided on the rear of the body 10 for generating a wind so as to allow the body 10 to rise vertically on the ground surface so that the body 10 can move horizontally A tail wing portion 60 provided on a rear surface of the rotor supporting portion 30 and a landing portion 70 provided on a lower portion of the body portion 10 to support the ground surface, do.

First, it is preferable that the body 10 is a part which becomes a body of an airplane, and is provided in a streamlined form, and is provided in the form of a general aircraft body which is easy to slide by minimizing wind resistance.

Next, the main wing portion 20 is provided with main wing portions 20 on both sides with respect to the center axis of the body portion 10.

Specifically, the main wing 20 is provided on both sides of the center of the body 10, and serves as a main wing for lifting the wing during flight.

2 to 3, the main wings 20 are connected to both sides of the body 10, and are fixed to the wings and the rotor support 30, And a long wing blade (22) provided on the end of the stationary wing (21) so as to be attached and detached.

In the high-speed long-haul flight mode, the long-haul wing 22 can be mounted to perform effective flight in the form of a fixed-wing aircraft. In the low-speed short-haul flight mode, The long wing portion 22 may be detached and the size of the main wing portion 20 may be reduced so that an effective flying can be performed in the form of a rotorcraft airplane.

At this time, the fixed wing portion 21 has a first coupling groove 23 formed with two or three grooves on its end face, and is formed of a material having a magnetic force. On the end face of the long wing wing portion 22, As shown in FIG. 3, a coupling protrusion 24 of a type that can be coupled to the first coupling groove 23 is made of an iron material. This is for facilitating the mounting and detachment of the long blade 22, and it is possible to easily and stably mount and detach the same through the magnetic force.

4 to 6, at the end face of the fixed wing 21, a wing is provided upwardly and downwardly so as to assist a stable flywheel flight and to serve as a landing stand. In the low-speed short-distance flying mode, The landing wing portion 80 can be further mounted. When the flywheel is flying, it is easy to balance the flywheel through the landing wing 80, and it can serve as a landing stand when landing.

Next, the rotor supporting portion 30 is formed in a shape of a bar crossing the main wing portion 20 and provided in parallel to both sides with respect to the traveling direction of the body portion 10.

3, the rotor supporting portion 30 is a portion to which a rotor forming the below-described lift generating portion 40 is mounted, and is configured to cross the fixed wing portion 21 And is formed in a bar shape parallel to both sides with respect to the traveling direction of the body part 10, and a rotor may be provided on left and right sides of the front side and rear sides of the front side relative to the body part 10 .

At this time, it is preferable that the rear end portion of the rotor support portion 30 is made of steel and can be coupled to the second engagement groove 61 described below.

Next, the lift generating portion 40 is provided on the rotor supporting portion 30 to generate wind so that the body 10 can float vertically on the ground.

Rotor support is provided on left and right and right and left sides of the front portion of the rotor supporting portion 30 so that the body portion 10 is perpendicular to the ground It causes the wind to rise.

Through the lift generation unit 40, it is possible to fly in the form of a rotorcraft aircraft, and to perform a low-speed short-range flight mission.

Next, the propulsive force generating unit 50 is provided on the rear surface of the moving body 10 to wind the moving body 10 in a horizontal direction.

Specifically, the propulsive force generating unit 50 is provided in the form of a rotor on the rear surface of the body 10, and generates a propelling force through the rotation of the rotor.

Next, the tail wing portion 60 is provided on the rear surface of the rotor supporting portion 30. [

Specifically, the tail wing portion 60 is a portion for grasping the center of the body portion 10 and controlling its direction at the time of flight, and the tail wing portion 60 is made of a material having a magnetic force A second engaging groove 61 formed at both sides of the rotor supporting portion 30 so as to receive the lower end portion of the rotor supporting portion 30 and a second engaging groove 61 provided upwardly inclined toward the central axis of the body portion 10 from the second engaging groove 61 And a tail wing landing part 63 provided in a wing shape below the second defect groove so as to serve as a landing stand.

The tail wing 60 is also configured to be detachable for a flywheel flight in the low-speed short-haul flight mode, like the fixed wing 21 of the main wing 20, It is equipped for wing fly, and serves as a tail wing.

Next, the landing portion 70 is provided at a lower portion of the body 10 to support the ground.

Specifically, the landing unit 70 may be a part that serves as a landing stand capable of supporting the ground during landing, and may further be attached with a wheel.

Hereinafter, the operation of the invention constructed as described above will be described.

The multi-purpose hybrid vertical take-off and landing unmanned aerial vehicle having the detachable wing according to the present invention can mount and detach the main wing portion 20 and the tail wing portion 60 according to the low-speed short-distance flying mode and the high- It is an unmanned aircraft.

First, in a high-speed long-haul flight mode, as shown in FIG. 1, the main wing portion 20 and the tail wing portion 60 of the main wing portion 20 and the tail wing portion 60 are mounted, It is possible to fly at a high speed over a long distance by using the propulsive force generated in the generator 50 as a main driving force.

Next, in the low-speed short-distance flying mode, as shown in FIG. 4, the long wing portion 22 of the main wing portion 20 and the tail wing portion 60 are separated from each other, The low-speed short-distance flying mission can be easily performed by using the propulsive force generated in the lift generating unit 40 and the propulsive force generating unit 50 as the main driving force.

As described above, it is to be understood that the technical structure of the present invention can be embodied in other specific forms without departing from the spirit and essential characteristics of the present invention.

Therefore, it should be understood that the above-described embodiments are to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than the foregoing description, All changes or modifications that come within the scope of the equivalent concept are to be construed as being included within the scope of the present invention.

10: body part 20: main wing part
21: fixed wing portion 22:
23: first engaging groove 24: engaging projection
30: rotor supporting portion 40: lift generating portion
50: propulsion generating unit 60: tail wing
61: second engaging groove 62: tail lift section
63: tail wing landing part 70: landing part
80: landing wing

Claims (5)

A body portion provided in a streamlined manner;
A main wing portion provided on both sides of the central portion of the body portion;
A bar-shaped rotor support portion provided across the main wing portion and parallel to both sides with respect to a traveling direction of the body portion;
A lift generating unit provided on the rotor supporting unit and generating wind to float the body part vertically on the ground;
A propulsive force generating unit provided on a rear surface of the trunk unit to generate wind so that the trunk unit moves in a horizontal direction;
A tail wing provided on a rear surface of the rotor supporting portion; And
And a landing portion provided at a lower portion of the body portion to support a ground surface,
The main wing portion and the tail wing portion can be mounted and dismounted so that the main wing portion and the tail wing portion are mounted in the form of a fixed wing aircraft in high speed long distance flying mode,
Wherein the main wing portion and the tail wing portion are detached and fly in the form of a rotary wing aircraft when the vehicle is in the low-speed short-haul flight mode. The method according to claim 1,
The main wing portion
A fixed wing portion connected to both sides of the body portion and serving as a support for the wing and the rotor supporting portion; And
And a long-wing blade which is mounted and detachably attached to an end of the fixed blade,
Wherein the securing wings are separated during the low-speed short-haul flight mode. ≪ Desc / Clms Page number 19 > 3. The method of claim 2,
Wherein the fixed blade has a first coupling groove in which two or three grooves are formed on an end surface thereof,
Wherein the coupling protrusion is formed of iron material on the end surface of the long-width detachable wing portion so as to be coupled to the first coupling groove. The method according to claim 1,
The tail wing portion
A second coupling groove formed of a material having a magnetic force and provided on both sides in a form capable of receiving a lower end portion of the rotor supporting portion;
A plate-shaped tail lifting portion provided upwardly inclined from the second engagement groove toward the center axis of the body portion; And
And a tail wing landing portion provided in the form of a wing below the second defect groove to assist a stable wing flight and serve as a landing stand. 3. The method according to any one of claims 1 to 2,
In the low-speed short-range flight mode,
And a landing blade portion having a wing formed upwardly and downwardly so as to serve as a landing stand for assisting a stable rotation of the flywheel can be further mounted on the end face of the fixed wing portion. Take - off and landing unmanned aircraft.
KR1020150180462A 2015-12-16 2015-12-16 Multi-purpose hybrid VTOL UAV with a detachable wings KR101776954B1 (en)

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CN107600414A (en) * 2017-09-11 2018-01-19 珠海天晴航空航天科技有限公司 A kind of unmanned plane that can be taken off and quickly be assembled without instrument in case
CN107672779A (en) * 2017-10-16 2018-02-09 珠海天晴航空航天科技有限公司 A kind of combined type multi-rotor unmanned aerial vehicle
WO2019010554A1 (en) * 2017-07-10 2019-01-17 Rodrigues Tiago Giglio Remotely piloted aircraft
CN109319110A (en) * 2018-10-26 2019-02-12 安徽云翼航空技术有限公司 A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure
CN109720537A (en) * 2018-10-26 2019-05-07 深圳市科卫泰实业发展有限公司 A kind of combined type vertical take-off and landing drone easy to disassemble with vanning
CN109733599A (en) * 2019-02-27 2019-05-10 广西翼界科技有限公司 A kind of combined dual-purpose unmanned plane
CN110040261A (en) * 2019-04-17 2019-07-23 西安爱生技术集团公司 A kind of bracket and unmanned plane handling method of small and medium size unmanned aerial vehicles packed and transported
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KR20200080825A (en) * 2018-12-27 2020-07-07 건국대학교 산학협력단 Veryical takeoff and landing fixed wing unmanned aerial vehicle
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KR102355526B1 (en) * 2020-07-24 2022-02-07 주식회사 샘코 Unmanned Aerial Vehicle having folding type wings
CN114275157A (en) * 2021-12-31 2022-04-05 重庆交通大学绿色航空技术研究院 Composite wing unmanned aerial vehicle and pneumatic balancing method
KR20230006664A (en) * 2021-07-01 2023-01-11 주식회사 공간정보 unmaned air vehicle for multi-using
US11655023B2 (en) * 2018-01-30 2023-05-23 Ideaforge Technology Pvt. Ltd. Fixed-wing vertical take-off and landing hybrid UAV
RU221398U1 (en) * 2022-12-12 2023-11-03 Федеральное Государственное Автономное Образовательное Учреждение Высшего Образования "Самарский Национальный Исследовательский Университет Имени Академика С.П. Королева" (Самарский Университет) Unmanned aerial vehicle

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CN109720537A (en) * 2018-10-26 2019-05-07 深圳市科卫泰实业发展有限公司 A kind of combined type vertical take-off and landing drone easy to disassemble with vanning
KR20200080825A (en) * 2018-12-27 2020-07-07 건국대학교 산학협력단 Veryical takeoff and landing fixed wing unmanned aerial vehicle
CN109733599A (en) * 2019-02-27 2019-05-10 广西翼界科技有限公司 A kind of combined dual-purpose unmanned plane
CN110040261A (en) * 2019-04-17 2019-07-23 西安爱生技术集团公司 A kind of bracket and unmanned plane handling method of small and medium size unmanned aerial vehicles packed and transported
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KR102225256B1 (en) * 2019-09-30 2021-03-10 선문대학교 산학협력단 Drone with Variable Propulsion Units
KR102168842B1 (en) * 2020-07-22 2020-10-22 유콘시스템 주식회사 Emergency control device to respond in the event of a loss of communication or failure situation of a hybrid unmanned aerial vehicle
KR102355526B1 (en) * 2020-07-24 2022-02-07 주식회사 샘코 Unmanned Aerial Vehicle having folding type wings
KR20230006664A (en) * 2021-07-01 2023-01-11 주식회사 공간정보 unmaned air vehicle for multi-using
CN113697086B (en) * 2021-09-26 2023-12-19 北京海利天梦科技有限公司 Rotatable multifunctional unmanned aerial vehicle fin
CN113697086A (en) * 2021-09-26 2021-11-26 北京海利天梦科技有限公司 Rotatable multi-functional unmanned aerial vehicle fin
CN114275157A (en) * 2021-12-31 2022-04-05 重庆交通大学绿色航空技术研究院 Composite wing unmanned aerial vehicle and pneumatic balancing method
RU221398U1 (en) * 2022-12-12 2023-11-03 Федеральное Государственное Автономное Образовательное Учреждение Высшего Образования "Самарский Национальный Исследовательский Университет Имени Академика С.П. Королева" (Самарский Университет) Unmanned aerial vehicle

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