KR101423680B1 - Unmanned Aerial Vehicle having joined wings - Google Patents

Unmanned Aerial Vehicle having joined wings Download PDF

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KR101423680B1
KR101423680B1 KR1020130029654A KR20130029654A KR101423680B1 KR 101423680 B1 KR101423680 B1 KR 101423680B1 KR 1020130029654 A KR1020130029654 A KR 1020130029654A KR 20130029654 A KR20130029654 A KR 20130029654A KR 101423680 B1 KR101423680 B1 KR 101423680B1
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wing
joining
trusses
wings
unmanned aerial
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KR1020130029654A
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Korean (ko)
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이희우
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한국전기비행 (주)
이희우
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/30—Aircraft characterised by electric power plants
    • B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
    • B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft

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

Abstract

The present invention relates to an unmanned aerial vehicle of joined wings. In order to simplify, strengthen and lighten a fuselage while improving flying efficiency, capability of short take-off and landing and remaining performance in the air for a long time, a fuselage connected with joined wings comprises one pair of trusses; and front, lower, and upper wings connecting the trusses while the rear end parts of the trusses have vertical wings including rudders.

Description

조인드윙형 무인항공기 {Unmanned Aerial Vehicle having joined wings } [0001] The present invention relates to an unmanned aerial vehicle having joined wings,

본 발명은 조인드윙형 무인항공기에 관한 것으로서, 보다 구체적으로는 조인드윙(joined wings)을 포함하는 무인항공기에 있어서 동체의 초경량화를 도모함과 아울러서 상기 초경량 동체에서도 양력이 발생 되도록 함으로써 비행의 효율이 매우 우수하며 단거리 이착륙(STOL; Short Take-Off and Landing)성능이 매우 우수한 조인드윙형 무인항공기에 관한 것이다. More particularly, the present invention relates to a joining-type wing-type unmanned airplane, and more particularly, to an unmanned airplane including joining wings, which is capable of reducing the weight of a fuselage and generating lifting force in the ultra- The present invention relates to a joining-wing type unmanned aerial vehicle which is very excellent and has a short take-off and landing (STOL) performance.

무인항공기(UAV; Unmaned Aerial Vehicle)는 세계적으로 군수용목적과 민수용목적으로 연구개발이 활발하게 진행되고 있으며 정찰 또는 탐사위성과 상호보완적인 장비인 동시에 유인기를 대체하고 있는 추세에 있다. Unmanned Aerial Vehicle (UAV) has been actively researched and developed for military and civil purposes in the world, and it is a complementary equipment with reconnaissance or exploration satellites, and it is in the trend of replacing popularity.

조인드윙은 일반적인 날개에 비하여 비행중 날개 끝단에서 발생하는 익단와류(vortex)에 의한 유도항력을 제거하여 전체항력을 약 15~20% 정도 감소시켜줌으로써 양항비율 등 항공기의 공기역학적인 효율을 증가시켜주는 것으로 알려져 있다. The joining dwind reduces the total drag by about 15 ~ 20% by removing the induced drag caused by the tip vortex at the wing tip during flight compared to the normal wing, thereby increasing the aerodynamic efficiency of the aircraft such as the drag ratio It is known to give.

그리고, 조인드윙을 포함하는 항공기는 날개구조가 연결되어 일반적인 항공기에 비하여 구조적 강성을 높일 수 있으며, 이로 인한 기체무게의 경량화가 가능하고, 일반적인 항공기 형상보다 큰 가로세로비를 갖는 날개형상설계가 가능하므로 특히, 고고도장기체공항공기에 유리한 것으로 알려져 있다. In addition, the aircraft including the joining dowel can increase the structural stiffness compared to a general airplane due to the connection of the wing structure, thereby making it possible to reduce the weight of the airframe, and to design a wing shape having a larger aspect ratio than a general aircraft shape Especially, it is known that it is advantageous for high-altitude air to air of airport.

미국특허 제 5,899,410호에 개시되어 있는 조인드윙을 가진 항공기는 세로로연장된 동체(lengthwise extending fuselage)와 같은 평면에 결합된 조인드윙의 전방날개와 후방날개에서 발생하는 양력으로 비행하는 것으로서, 상기 동체에서는 양력을 얻을 수 없는 것이므로 비행의 효율을 크게 향상시켜줄 수 없었으며, 큰 양력이 요구되는 단거리이착륙성능을 기대할 수 없는 것이었다. An aircraft having a joining ding as disclosed in U.S. Patent No. 5,899,410 is flying with a front wing of a joining ding coupled to a plane such as a lengthwise extending fuselage and lift generated from the rear wing, , It was impossible to improve the efficiency of the flight because the lift was not obtained and the short-distance takeoff and landing performance requiring a large lift was not expected.

그리고, 동체와 떨어져있는 조인드윙의 전방날개와 후방날개에 에이러론, 엘리베이터와 같은 조종면들(control surfaces)을 가진 것이어서 상기 조종면들을 작동시켜주는 엑츄에이터들을 상기 전방날개와 후방날개에 설치해주어야만 하는 것이므로 날개의 구조가 복잡해지고, 날개의 중량을 증가시키며, 중량이 증가 된 날개는 동체와의 보다 견고한 결합구조를 필요로 하게 되어서 항공기의 전체중량이 증가 되었으며, 이로 인하여 보다 큰 추력이 요구되고, 이는 곧 추진장치의 대형화와 효율성저하로 이어지게 되었었을 뿐만 아니라 전장에서 운용될 때 피탄에 의한 비행조종불능을 초래할 우려가 많은 등의 문제점도 있었다. In addition, the front wings and the rear wings of the joining dinges remote from the body have control surfaces such as elevators, so that actuators for operating the control surfaces must be installed on the front wing and the rear wing The structure of the wing is complicated, the weight of the wing is increased, and the wing having increased weight requires a more rigid coupling structure with the fuselage, so that the total weight of the aircraft is increased, which requires a larger thrust, This not only led to the enlargement of the propulsion system and the deterioration of the efficiency, but also there were many problems such as the possibility of flying control by the pilots when operated on the battlefield.

따라서, 상기한 바와 같은 종래의 조인드윙을 가진 항공기는 유인기처럼 긴 활주로에서 이착륙하는 중·고고도용 무인항공기용으로는 적합하지만 긴 활주로를 확보하기가 곤란한 야전이나 산악지형에서 주로 운용되는 저고도 정찰용 무인항공기용으로는 적합하지 못한 것이었다. Therefore, the conventional aircraft having the above-described joining ding is suitable for unmanned aerial vehicles for middle and high altitude takeoff and landing on a long runway, but it is difficult to secure a long runway, and low-altitude reconnaissance It was not suitable for unmanned aerial vehicles.

본 발명의 목적은 조인드윙이 결합되는 동체의 단순화와 고강도화 및 초경량화를 도모함과 아울러서 상기 동체에서도 양력이 발생되도록 함으로써 비행효율과 단거리이착륙성능이 매우 우수하여 긴 활주로를 확보하기 어려운 야전이나 산악지형 그리고 함상에서 운용되는 저고도 정찰용으로 적합한 조인드윙형 무인항공기를 제공하는데 있다. The object of the present invention is to provide a hull structure which can simplify the body to which the joining dow is joined, enhance the strength and weight of the hull, and generate lifting force in the hull so that the flight efficiency and the short- And to provide a joining-wing type unmanned aerial vehicle suitable for low-altitude reconnaissance operations in a shipyard.

본 발명은 조인드윙형 무인항공기에 관한 것으로, 한쌍의 조인드윙과 연결되는 동체가 한쌍의 트러스와, 상기 트러스들의 전방쪽 상부, 중반부쪽하부, 후방쪽 상부를 각각 연결해주는 전방날개, 하부날개, 상부날개로 이루어져 있으며, 상기 트러스의 후방단부에는 방향타를 포함하는 수직날개를 구비하여서 된 것을 특징으로 한다. [0001] The present invention relates to a joining-wing type UAV, in which a body connected to a pair of joining dies includes a pair of trusses, a front wing for connecting the upper, middle, and rear upper portions of the trusses, And a vertical blade including a rudder is provided at a rear end of the truss.

또한, 본 발명에 따른 상기 트러스의 전방수직부재에 추진기관이 구비되어 있는 것을 특징으로 한다. Further, the present invention is characterized in that the propulsion engine is provided in the front vertical member of the truss according to the present invention.

또한, 본 발명에 따른 상기 조인드윙과 상기 전방날개, 하부날개, 상부날개에 태양전지판이 구비되어 있는 것을 특징으로 한다. In addition, a solar panel is provided on the joining ding and the front wing, the lower wing, and the upper wing according to the present invention.

또한, 본 발명에 따른 상기 전방날개가 가동형카나드로 되어 있는 것을 특징으로 한다. Further, the front wing according to the present invention is a movable canard.

본 발명은 조인드윙과 연결되는 동체가 한쌍의 트러스와, 이 트러스들을 연결해주며 양력을 발생시켜주는 전방날개, 하부날개, 상부날개로 이루어진 것이어서 동체의 단순화와 고강도화 및 초경량화를 도모하여 보다 저렴한 비용으로 품질이 균일하고 유지보수가 용이하며 운반과 취급이 손쉽고 내구성이 우수한 무인항공기를 제공할 수 있으며, 우수한 비행효율과 단거리 이착륙성능을 발휘하여 긴 활주로를 확보하기 어려운 야전이나 산악지형 그리고 함상에서도 운용하기에 적합하고, 특히 동체로부터도 양력을 얻을 수 있는 것이어서 임무수행중 추진력을 상실하거나 주날개를 이루는 조인드윙이 피탄되어 양력이 감소 되더라도 활공비행성능이 우수하여 소프트랜딩이 가능한 것이므로 임무완수율을 크게 향상시켜줄 수 있어 매우 우수한 신뢰성을 발휘하는 등의 장점이 있다. The present invention is characterized in that the body connected to the joining ding is composed of a pair of trusses, a front wing, a lower wing, and an upper wing for connecting the trusses and generating a lift force, simplifying the body, It is possible to provide unmanned aircraft with uniform quality, easy maintenance and easy transportation and handling, excellent flight efficiency and short-range takeoff and landing performance, and can be operated in fields, mountainous terrain, and shipyards where it is difficult to secure long runways. In particular, it is possible to obtain lift from the fuselage, so that even if the propulsion force is lost during the mission or the joining ding that forms the main wing is piled and the lift is reduced, the smooth flying performance is excellent and the soft landing is possible. Excellent reliability that can be improved And the like.

도 1은 본 발명의 바람직한 실시예에 따른 조인드윙형 무인항공기의 사시도.
도 2는 도 1에서 보인 조인드윙형 무인항공기의 분해 사시도.BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view of a join-and-drag unmanned aerial vehicle according to a preferred embodiment of the present invention; FIG.
FIG. 2 is an exploded perspective view of the joining-wing-type UAV shown in FIG. 1. FIG.

본 발명에 따른 조인드윙형 무인항공기는 도 1과 도 2에 예시한 바와 같이 동체(10)와 연결되는 한 쌍의 조인드윙(12,14)을 가진 조인드윙형 무인항공기에 있어서, 상기 동체(10)가 한 쌍의 트러스(truss)(16,18)와 적어도 3개 이상의 수평날개(20,22,24) 그리고 방향타를 포함하는 수직날개(26)로 이루어진 것을 특징으로 한다. The joining-dragging type unmanned aerial vehicle according to the present invention is a join-wing-type unmanned aerial vehicle having a pair of joining dies 12, 14 connected to a moving body 10 as illustrated in Figs. 1 and 2, 10 comprises a pair of trusses 16, 18, a vertical blade 26 comprising at least three horizontal blades 20, 22, 24 and a rudder.

상기 날개(20,22,24)는 상기 트러스(16,18)의 전방 쪽 상부를 연결해주는 전방날개(20)와, 상기 트러스(16,18)의 중반부 쪽 하부를 연결해주는 하부날개(22)와, 상기 트러스(16,18)의 후방 쪽 상부를 연결해주는 상부날개(24)로 되어 있다. The wings 20, 22 and 24 include a front wing 20 for connecting the front upper portion of the trusses 16 and 18 and a lower wing 22 for connecting the lower half of the trusses 16 and 18, And an upper blade 24 connecting the upper portion of the rear side of the trusses 16 and 18.

상기 수직날개(26)는 상기 트러스(16,18)의 후방 단부에 구비되어 있다. The vertical vanes 26 are provided at the rear ends of the trusses 16 and 18.

상기 트러스(16,18)의 전방 하부에는 주랜딩기어(27,28)가 구비되어 있으며, 상기 트러스(16,18)의 후방 하부에는 보조랜딩기어(30)가 구비되어 있다. Main landing gears 27 and 28 are provided at the front lower portion of the trusses 16 and 18 and auxiliary landing gears 30 are provided at the rear lower portions of the trusses 16 and 18.

상기 보조랜딩기어(30)는 예를 들어 상기 트러스(16,18)의 후방 하부를 연결해주는 보강부재(32)의 중앙에 설치해주는 것이 바람직한데 그 이유는 착륙시 내충격성과 안전성을 확보할 수 있기 때문이다. It is preferable that the auxiliary landing gear 30 is installed at the center of the reinforcing member 32 connecting the rear lower portion of the trusses 16 and 18 because the impact resistance and safety can be secured Because.

본 발명에 있어서, 예를 들어 전기모터, 피스턴 왕복엔진 등으로 이루어질 수 있는 추진기관(34,36)은 상기 트러스(16,18)를 이루는 전방수직부재(38,40)의 전방 또는 후방에 설치하는 것이 상기 추진기관(34,36)을 보호할 수 있어 바람직하며, 더욱 바람직하기로는 상기 추진기관(34,36)을 상기 전방수직부재(38,40)의 후방에 설치하는 것이 좋다. In the present invention, for example, propulsion engines 34 and 36, which can be composed of an electric motor, a piston reciprocating engine or the like, are installed forward or rearward of the front vertical members 38 and 40 constituting the trusses 16 and 18 It is preferable that the propelling tubes 34 and 36 are installed behind the front vertical members 38 and 40 because the propelling tubes 34 and 36 can be protected.

그리고, 상기 하부날개(22)의 내부에는 예시도면에 구체적인 표현이 생략되어 있으나 예를 들어 항공전자장비, 비행제어장비, 각종 관측장비 등을 비롯한 내부탑재물이 탑재되어 있다. In the meantime, although the detailed description is omitted in the illustration of the inside of the lower blade 22, for example, an inside mount including an avion electronic equipment, a flight control equipment, various observation equipment and the like is mounted.

또한,상기 조인드윙(12,14)과, 상기 날개(20,22,24)에는 통상의 태양전지판 (42)들을 설치하여서 상기 추진기관(34,36)의 동력과 내부탑재물에 필요한 전원을 공급시켜 줄 수 있도록 해줄 수도 있다. Conventional solar panels 42 are installed in the joining downds 12 and 14 and the vanes 20 and 22 and 24 so that the power of the propulsion engines 34 and 36 and the power required for the internal mountings You can also make them available.

또한, 상기 조인드윙(12,14)과, 상기 날개(20,22,24)에는 예시도면에 구체적인 표현이 생략되어 있으나, 예를 들어 에이러론이나 엘리베이터 등과 같은 조종면을 구비할 수도 있다. The joining downds 12, 14 and the vanes 20, 22, 24 are not shown in the drawings, but may include a steering surface such as an iron or an elevator.

또한, 상기 트러스(16,18)는 저항감소와 강도유지 및 전기배선 등을 고려하여 원형파이프로 만들어주는 것이 바람직하다. In addition, the trusses 16 and 18 are preferably made of a circular pipe in consideration of resistance reduction, strength maintenance, electric wiring, and the like.

이와 같이 구성된 본 발명에 따른 조인드윙형 무인항공기는 도 2에 예시한 바와 같이 동체(10)를 이루는 트러스(16,18)와 날개(20,22,24) 그리고 주날개를 이루는 조인드윙(12,14)이 상기 트러스(16,18)를 골격으로 하여서 분리하거나 조립할 수 있도록 된 것이어서 동체의 단순화와 고강도화 및 초경량화를 도모할 수 있고, 특히, 운반과 취급이 손쉬워서 야전에서 분해, 조립하여 운용하기가 매우 용이 하다. As shown in FIG. 2, the joining-wing type UAV according to the present invention includes the trusses 16 and 18, the wings 20, 22 and 24, and the joining dowel 12 , 14) can be separated or assembled with the trusses (16, 18) as a skeleton, so that the body can be simplified, strengthened and lightened, and particularly, it is easy to carry and handle, It is very easy to operate.

또한, 동체(10)를 이루는 날개(20,22,24)는 동체(10) 자체가 양력을 가질 수 있도록 해주는 것이므로 비행중 각종 사고나 대공화기에 피탄되어서 추진력을 잃거나 조인드윙(12,14)으로부터 충분한 양력을 얻지 못하는 상태에서도 항공기가 낙엽이 떨어지는 것과 유사한 형태로 활공하면서 소프트랜딩 할 수 있도록 해주게 된다. Since the wings 20, 22 and 24 constituting the moving body 10 allow the moving body 10 itself to have a lift force, it is likely to be thrown by various accidents or a big fire during the flight, ) Allows the aircraft to glide in a form similar to falling fallen leaves, allowing soft landing.

또한, 상기 날개(20,22,24) 중 전방날개(20)는 상기 트러스(16,18)와 피버트로 연결시켜서 가동형카나드(귀날개)로 활용할 수도 있는 것이어서 단거리 이착륙성능을 더욱 향상시켜주게 된다. The front wings 20 of the vanes 20, 22 and 24 may be connected to the trusses 16 and 18 by a fulcrum to be used as a movable canard (ear wing) do.

10 ------- 동체
12,14 ------- 조인드윙
16,18 ------- 트러스
20 ------- 전방날개
22 ------- 하부날개
24 ------- 상부날개
26 ------- 수직날개
27,28 ------- 주랜딩기어
30 ------- 보조랜딩기어
34,36 ------- 추진기관
42 ------- 태양전지판10 ------- Fuselage
12,14 ------- Join Ding
16,18 ------- truss
20 ------- Front wing
22 ------- Lower wing
24 ------- Top wing
26 ------- Vertical wing
27,28 ------- Main landing gear
30 ------- Auxiliary landing gear
34,36 ------- Propulsion machinery
42 ------- Solar panel

Claims (4)

동체(10)와 연결되는 한 쌍의 조인드윙(12,14)을 가진 조인드윙형 무인항공기에 있어서, 상기 동체(10)가 한 쌍의 트러스(16,18)와, 상기 트러스(16,18)의 전방 쪽 상부를 연결해주는 전방날개(20)와, 상기 트러스(16,18)의 중반부 쪽 하부를 연결해주는 하부날개(22)와, 상기 트러스(16,18)의 후방 쪽 상부를 연결해주는 상부날개(24)로 이루어져 있으며, 상기 트러스(16,18)의 후방 단부에는 방향타를 포함하는 수직날개(26)를 구비하여서 된 것을 특징으로 하는 조인드윙형 무인항공기.A joining wing type UAV having a pair of joining dies (12, 14) connected to a body (10), characterized in that the body (10) comprises a pair of trusses (16, 18) A lower blade 22 connecting the lower half of the trusses 16 and 18 and a lower blade 22 connecting the upper side of the trusses 16 and 18, And a vertical wing (26) including a rudder on the rear end of the truss (16, 18). 제 1항에 있어서, 상기 트러스(16,18)의 전방수직부재(38,40)에 추진기관 (34,36)이 구비되어 있는 것을 특징으로 하는 조인드윙형 무인항공기.The joining drone of claim 1, wherein the forward vertical members (38, 40) of the truss (16, 18) are provided with propelling organs (34, 36). 제 1항에 있어서, 상기 조인드윙(12,14)과 상기 전방날개(20), 하부날개 (22), 상부날개(24)에 태양전지판(42)이 구비되어 있는 것을 특징으로 하는 조인드윙형 무인항공기.The joining dowel according to claim 1, wherein the joining dowel (12, 14) and the solar panel (42) are provided on the front wing (20), the lower wing (22) Unmanned aircraft. 제 1항에 있어서, 상기 전방날개(20)가 가동형 카나드로되어 있는 것을 특징으로 하는 조인드윙형 무인항공기.The joining-wing type unmanned aerial vehicle according to claim 1, wherein the front wing (20) is a movable canard.
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101646736B1 (en) 2016-01-25 2016-08-08 주식회사 케바드론 Joined wing type unmanned aircraft
CN106379525A (en) * 2016-12-01 2017-02-08 北京猎鹰无人机科技有限公司 Wing connected unmanned plane
CN109987217A (en) * 2019-04-29 2019-07-09 北京驰宇空天技术发展有限公司 Folding wings unmanned plane and its launching technique

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US7100867B2 (en) 2004-02-09 2006-09-05 Houck Ii Ronald G Lifting foil
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings

Patent Citations (4)

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Publication number Priority date Publication date Assignee Title
US4856736A (en) 1987-06-26 1989-08-15 Skywardens Limited Aircraft with paired aerofoils
US20060016931A1 (en) 2004-01-28 2006-01-26 Malvestuto Frank S High-lift, low-drag dual fuselage aircraft
US7100867B2 (en) 2004-02-09 2006-09-05 Houck Ii Ronald G Lifting foil
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101646736B1 (en) 2016-01-25 2016-08-08 주식회사 케바드론 Joined wing type unmanned aircraft
CN106379525A (en) * 2016-12-01 2017-02-08 北京猎鹰无人机科技有限公司 Wing connected unmanned plane
CN109987217A (en) * 2019-04-29 2019-07-09 北京驰宇空天技术发展有限公司 Folding wings unmanned plane and its launching technique

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