| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | 버티컬 이착륙, 버티컬 및 호리즌탈 비행 및 비행중 에너지 생성이 가능한 비행체 | KR1020180134426 | 2018-11-05 | KR1020180123457A | 2018-11-16 | |
| 본기술의일 실시예에의한버티컬이착륙, 버티컬및 호리즌탈비행및 비행중에너지생성이가능한비행체는제1 방향으로배치되는동체; 제2 방향으로상호대향하도록동체에배치되는 2개의메인윙들 - 제2 방향은제1 방향에수직임; 메인윙들각각에연결되며, 메인윙들을상호독립적으로틸팅하도록제어하는메인윙 틸팅제어부들; 메인윙들각각에구비되는메인추력체들; 제2 방향및 제3 방향으로동체의후단에배치되는테일윙들 - 제3 방향은제1 및 2 방향에수직임; 제3 방향으로배치된테일윙에배치되는방향타; 방향타의틸팅을제어하는방향타틸팅제어부; 동체의후단에배치되는테일추력체; 테일추력체의틸팅을제어하는테일틸팅제어부; 메인및 테일추력체들에게전력을공급하는전원부; 및비행체의자세의보정을위해메인추력체들및 테일추력체의출력및 메인윙들및 테일추력체의틸팅을제어하는자세제어부를포함할수 있다. | ||||||
| 62 | 비행체 | KR1020160171919 | 2016-12-15 | KR1020180069594A | 2018-06-25 | |
| 일실시예에따른비행체는, 동체; 상기동체의양 측으로부터스팬방향으로연장하는주날개; 상기주날개의내부에회전가능하게장착된회전익; 및상기주날개에개폐가능하게설치되고외부에대하여상기회전익을개방또는폐쇄시키는개폐부를포함할수 있다. | ||||||
| 63 | 드론 | KR1020160044900 | 2016-04-12 | KR1020170116814A | 2017-10-20 | 이승재 |
| 본발명은조종사없이무선전파의유도에의해서비행및 조종이가능한비행체인드론에관한것으로서, 좀더 상세하게는, 종래드론본체의최외곽에구비되어드론추진체로사용되는다수의고속회전블레이드를생략하는대신압축공기를고속으로분사시켜추진력을발생시키는무블레이드형추진체를가지는드론에관한것으로, 본발명에따른드론(1)은, 외부로부터공기를흡입하여소정압력값으로압축시킨후 배출시키는압축공기생성부(10, 20); 중앙에상기압축공기생성부(10, 20)가구비되고, 외측면에는소정간격을두고다수의압축공기배출홀(32)이형성되며, 내부에는상기다수의압축공기배출홀(32)과각각연통되어상기압축공기생성부(10, 20)로부터발생되는압축공기를안내배출시키는다수의분기배출로(31)가형성되는몸체부(30); 및상측에서하측으로갈수록중공반경이점차확장되는내부중공의원통형태로형성되어외측이상기몸체부(30)에결합되고, 외측단에는상기압축공기배출홀(32)과연통되게입구홀(41)이구비되어상기압축공기배출홀(32)로부터배출된압축공기가상기입구홀(41)을통해유입되며, 상측내주면에는압축공기가하측으로분사되는분사노즐부(43)가내주면을따라형성되고, 내부에는상기입구홀(41)을통해유입된압축공기를상기분사노즐부(43)로안내배출시키는분사배출로(42)가구비되는추진체(40);를포함하여구성되는것을특징으로한다. | ||||||
| 64 | 로터가 숨겨진 하이브리드 수직이착륙 무인항공기 | KR1020160097161 | 2016-07-29 | KR101772223B1 | 2017-08-28 | 민경무; 니케시브하타라이; 치아풍이 |
| 본발명은로터가숨겨진하이브리드수직이착륙무인항공기에관한것으로보다상세하게는항공기의수평비행시에는항공기의내부에숨겨지고, 수직비행시에노출되어작동하는로터가숨겨진하이브리드수직이착륙무인항공기에관한것이다. 본발명에따른로터가숨겨진하이브리드수직이착륙무인항공기는, 항공기의동체역할을하는몸체; 상기몸체의양측에마련되고, 상기몸체로부터수직방향으로회전가능하도록형성되는날개; 상기날개의양단부에마련되는윙렛; 상기날개의내부에마련되고, 상측방향으로추진력을발생하는전방로터; 상기몸체의후방에마련되어, 전방및 상방으로추진력을발생하는후방로터; 및상기몸체의내부에마련되고, 상기날개및 후방로터를회전시키는구동부;를포함하고, 상기구동부에의하여상기날개가수직방향으로회전하면상기날개의내부에위치되는상기전방로터가외부로노출되는것을특징으로한다. 본발명의일실시예에따르면수직비행시에날개를수직방향으로회전시켜전방로터가노출되도록하고, 수평비행시에전방로터가숨겨지게함으로써, 수평비행시에전방로터에의하여항력이발생되는것을방지할수 있는로터가숨겨진하이브리드수직이착륙무인항공기가제공된다. 또한, 날개의양단부에수직안정판(Vertical Stabilizer) 역할과윙팁에서의유도항력을줄이는역할을동시에하는윙렛을설치함으로써, 항공기의후방에별도의수직안정판을설치하지않아도되는로터가숨겨진하이브리드수직이착륙무인항공기가제공된다. 또한, 수직이착륙시에윙렛을회전시켜착륙장치역할을할 수있는로터가숨겨진하이브리드수직이착륙무인항공기가제공된다. | ||||||
| 65 | 수직 이착륙 비행체 | KR1020160029586 | 2016-03-11 | KR101749863B1 | 2017-06-22 | 정진덕 |
| 일실시예에따른수직방향으로이착륙되는비행체는몸체, 상기몸체에배치되어서동력을공급하는동력공급부, 상기몸체에배치되어서비행모드를제어하는제어부, 상기몸체에배치되고, 상기동력공급부로부터동력을전달받아회전하는수직추력부, 및상기동력공급부로부터동력을전달받아회전하고, 상기몸체의일 측에서배치되는가변추력부를포함할수 있다. 또한, 상기제어부는상기수직추력부와상기가변추력부를제어하며상기수직추력부는상기제어부에의해상기몸체에대하여평행하게배치되고, 상기가변추력부는상기제어부에의해상기몸체에대하여평행및 수직방향으로전환될수 있다. | ||||||
| 66 | 무인 비행체를 이용한 산지 생태 축산의 방목형 목장 운용 및 관리 시스템 | KR20150006816 | 2015-01-14 | KR101536095B1 | 2015-07-13 | JUNG NYUM; KIM KI IL; KIM MIN SEOK |
| 본발명은무인비행체를이용한산지생태축산의방목형목장운용및 관리방법과시스템에관한것이다. 본발명의무인비행체를이용한방목형산지생태축산초지관리시스템은, 초지를촬영하여초지의성장상태에따라구별이가능한목장관측데이터를형성하는촬영부(140)와, 항로를운항하면서위치정보를검출하는비행정보부(120)가구비되어초지상공의지정된항로를무인으로자동비행하여초지를촬영하고, 촬영된목장관측데이터와위치데이터를전송하는무인비행체(100)와; 상기무인비행체(100)와통신접속하여무인비행체(100)의제어신호와, 목장관측데이터와위치데이터를통신하는중계기(200)와; 상기중계기(200)와접속하여상기무인비행체(100)가촬영한목장관측데이터및 위치데이터를제공받고관리하며, 비행항로와정보의수집을제어하는관제국(300)과; 상기관제국(300)과접속하여목장관측데이터와위치데이터가저장되는데이터서버(400)와; 상기데이터서버(400)에저장된목장관측데이터와위치데이터를이용하여위치별초지의성장상태를산출하는분석장치(500);를포함하여구성된다. 본발명에의해, 드론과같은무인비행체를이용하여초지를영상촬영하여초지의성장상태를관리자에게보내방목가축의사육시가축의이동방향설정을용이하게하여최종적으로가축사육의생산성을높일수 있고, 단순히초지의성장상태에관한데이터를제공하는데 그치지않고가축의분포, 이동상태와비교하여가축의이동경로를관리자에게제공할수 있도록하여자동화된초지관리가이루어질수 있으며, 더불어가축의총 개체수및 적외선카메라를이용한가축의체온변화가파악되도록함으로써가축이탈, 가축의이상징후등을파악하여제공함으로써가축의관리까지용이하게이루어질수 있게된다. | ||||||
| 67 | 엔진 배기가스를 이용한 엔진 냉각장치 | KR1020060110448 | 2006-11-09 | KR1020080042267A | 2008-05-15 | 박선태; 김승주; 김중욱 |
| An engine cooling system using engine exhaust gas is provided to maintain a temperature of an engine at a predetermined level by rapidly sucking and exhausting air in case of vertical takeoff and landing of UAV(Unmanned Aerial Vehicle) or an R/C(Remote Control) model aerial vehicle. An engine cooling system using engine exhaust gas includes a front air inlet(10), an air passage(20), an air outlet(30), an engine(40), and an exhaust pipe(50). The front air inlet is installed at one side of an aerial vehicle body. One end of the air passage is connected to the front air inlet and has a predetermined rear length along the aerial vehicle body. The air outlet is connected to the other end of the air passage and passes through an outer wall of a rear side of the aerial vehicle body. The engine is installed in the air passage. The exhaust pipe is installed at the engine and has a predetermined rear length along the air passage. The engine cooling system is mounted at a UAV(Unmanned Aerial Vehicle) or an R/C(Remote Control) model aerial vehicle. | ||||||
| 68 | 테일붐-안정화 수직 이착륙 비행체 | KR1020067009973 | 2004-10-19 | KR1020060101497A | 2006-09-25 | 발드윈,더글라스,쥐. |
| A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed. | ||||||
| 69 | AN UNMANNED AERIAL VEHICLE | EP13900333.9 | 2013-12-24 | EP3087003B1 | 2018-11-28 | CHAN, Keen Ian |
| An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure. | ||||||
| 70 | AIRCRAFT WITH WING-BORNE FLIGHT MODE AND HOVER FLIGHT MODE | EP15747241.6 | 2015-07-21 | EP3172130B1 | 2018-10-03 | HULSMAN, Sander; DE GROOT, Jurjen; MILIS, Maarten; DOKTER, Dirk Lucas Eduard; BOUMAN, Joost Leon; KNOOPS, Ruud |
| An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,12) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof. | ||||||
| 71 | AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF | EP16788767.8 | 2016-10-28 | EP3368413A1 | 2018-09-05 | WRIGHT, Julian, David; COLOSIMO, Nicholas, Giacomo, Robert; WARSOP, Clyde |
| An air vehicle (10) comprising a main body (12)and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12), at least a first propulsion device (16) associated with a first of said wing members (14a) and a second propulsion device (16) associated with a second of said wing members (14b), each said propulsion device (16) being arranged and configured to generate linear thrust relative to said main body (12), in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode (Figure 2) and a rotary wing mode (Figure 3), wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body (12) is the same as the direction of thrust generated by the second propulsion device (16), and in said second mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body is opposite to that generated by the second propulsion device (16). | ||||||
| 72 | VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) | EP16766198.2 | 2016-09-02 | EP3347269A1 | 2018-07-18 | STARACE, Ralph C.; AUGUST, Robert A.; FRONIUS, Douglas L.; CREASMAN, Francois |
| One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body encapsulating an engine and the flight control system. The VTOL UAV further includes a rotor disk coupled to the engine and configured to provide vertical thrust and cyclic pitch control in the hover mode and to provide horizontal thrust for flight during the level-flight mode. | ||||||
| 73 | HIGH SPEED MULTI-ROTOR VERTICAL TAKEOFF AND LANDING AIRCRAFT | EP15862818 | 2015-10-28 | EP3224140A4 | 2018-07-04 | CLARIDGE JERRY DANIEL; MANNING CHARLES FISCHER |
| This disclosure is generally directed to a High Speed vertical takeoff and landing (VTOL) aircraft that includes fixed wing flight capabilities. The High Speed VTOL aircraft may include at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a main wing, and at least two thrust producing rotors located equidistant from a longitudinal axis of the aircraft on a vertical wing. The rotors may be driven by electric motors. However, other power sources may be used such as combustion or hybrid engines. By adjusting the speed and/or the pitch of the rotors, the aircraft can transition from a vertical flight configuration to a horizontal flight configuration and back. | ||||||
| 74 | AIRCRAFT | EP15851788 | 2015-10-20 | EP3209559A4 | 2018-06-13 | HOHENTHAL MARKUS |
| An electrically powered vertical takeoff and vertical landing (VTOL) aircraft, which comprises at least two main propellers, wherein the main propellers are adapted to generate at least 70% of the aircraft propulsion. The aircraft also comprises at least one adjustment propeller, which has its propeller slipstream adapted to produce a torque relative to a first axis or the first and second axes with respect to a fuselage of the aircraft for turning the aircraft relative to said first axis or said first and second axes. In addition, not less than 35%, but not more than 85%, of the aircraft's mass is adapted to lie, during takeoff and/or landing, on a rear side of a propeller line of said main propellers with respect to a nose of the aircraft. | ||||||
| 75 | AIRCRAFT HAVING DUAL ROTOR-TO-WING CONVERSION CAPABILITIES | EP17163294.6 | 2017-03-28 | EP3290337A1 | 2018-03-07 | GRONINGA, Kirk Landon; ROBERTSON, Daniel Bryan; STAMPS, Frank Bradley |
A tail sitter aircraft (10) includes a fuselage (12) having a forward portion (14) and an aft portion (16). The forward portion (14) of the fuselage (12) includes first and second rotor stations (18, 20). A first rotor assembly (22) is positioned proximate the first rotor station (18). A second rotor assembly (24) is positioned proximate the second rotor station (20). A tailboom assembly (26) extends from the aft portion (16) of the fuselage (12) and includes a plurality of landing members (28). A pusher propeller (38) extends from the tailboom assembly (26). In a vertical takeoff and landing mode, the first and second rotor assemblies (22, 24) rotate about the fuselage (12) to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller (38) provides forward thrust and the first and second rotor assemblies (22, 24) are non-rotatable about the fuselage (12) forming a dual wing configuration to provide lift.
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| 76 | AIRCRAFT WITH SELECTIVELY ATTACHABLE PASSENGER POD ASSEMBLY | EP16185727.1 | 2016-08-25 | EP3263445A1 | 2018-01-03 | McCULLOUGH, John Richard; OLDROYD, Paul K. |
In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.
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| 77 | VERTICAL TAKE OFF AND LANDING CLOSED WING AIRCRAFT | EP17170907.4 | 2017-05-12 | EP3243747A1 | 2017-11-15 | FENNY, Carlos Alexander; OLSON, Rohn Lee; ZAHASKY, Andrew James |
VERTICAL TAKE OFF AND LANDING CLOSED WING AIRCRAFT An aircraft (100) capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing (102) that provides lift whenever the aircraft (100) is in forward flight, a fuselage (104) at least partially disposed within a perimeter of the closed wing (102), and one or more spokes (106) coupling the closed wing (102) to the fuselage (104). The fuselage (104) can have a rear module substantially disposed within a perimeter of the distributed airframe (1002, Figure 11), and a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors (132) are disposed within or attached to the closed wing (102), fuselage (104) or spokes (106). Three or more propellers (120) are proximate to a leading edge of the closed wing (102) or the one or more spokes (106), distributed along the closed wing (102) or the one or more spokes (106), and operably connected to the one or more engines or motors (132). The propellers (120) provide lift whenever the aircraft (100) is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft (100) is in forward flight.
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| 78 | HIGH-AUTHORITY YAW CONTROL FOR A TANDEM VEHICLE WITH RIGID ROTORS | EP15858679.2 | 2015-11-10 | EP3218261A1 | 2017-09-20 | HEIN, Benjamin Reed |
| A method for executing yaw control of an aircraft including two rotors is provided. The method includes inducing helicopter yaw by creating a differential torque between the two rotors, wherein the creating of the differential torque comprises inducing a differential collective pitch to generate a differential thrust, and maintaining helicopter roll equilibrium during the inducing of the helicopter yaw by inducing a differential cyclic pitch to generate a differential lift offset. | ||||||
| 79 | AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF | EP15275223 | 2015-10-30 | EP3162701A1 | 2017-05-03 | |
| A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof. | ||||||
| 80 | ROTARY WING VEHICLE | EP13828332 | 2013-05-21 | EP2852529A4 | 2016-07-06 | ARLTON PAUL E; ARLTON DAVID J |
| A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight. | ||||||
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