| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | 무인 비행체 | KR1020140016927 | 2014-02-13 | KR1020150096039A | 2015-08-24 | 최해천; 김주하 |
| 본 발명은 무인 비행체에 관한 것으로, 더욱 상세하게는 공력 성능을 향상시킨 무인 비행체에 관한 것이다.
본 발명은 동체와 날개의 구조 개선을 통해 양항비를 개선함으로써, 공력 성능이 향상된 새로운 구조의 무인 비행체를 제공하는 것을 목적으로 한다. 본 발명은 무인 비행체의 동체의 양쪽 측부에서 좌우 방향으로 연장된 날개에 좌우 방향으로 연장되고 상호 전후 방향으로 이어진 언덕부와 골부를 포함하는 복수의 주름부를 마련함으로써, 무인 비행체의 양항비를 개선할 수 있고, 이를 통해 무인 비행체의 항속거리, 체공 시간, 활공비 등의 공력 성능을 향상시킬 수 있는 효과가 있다. |
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| 122 | 잠수비행자동차 | KR1020150013460 | 2015-01-28 | KR1020150089970A | 2015-08-05 | 박영찬 |
| 본발명은금속구체형태이고수중이나공중을자유자재로주행할수 있는잠수비행자동차에관한것이다. 이와같은잠수비행자동차는, 금속구체형상인차체(100)와; 상기차체(100)의내부에설치되어, 상기차체(100)의공중비행시전진비행을위한추력을발생시키는가스터빈엔진(101)과; 상기차체(100)의하단부에설치되어, 상기차체(100)의수중비행시수중추진체가되도록이온빔을이용하여플라즈마를고속으로분출시키는수소이온엔진(200)과; 상기차체(100)의상단부에설치되며, 액체질소에의해냉각되어상기차체(100)를공중부양및 회전시키는적어도한 쌍의마방진영구자석세트(300a,300b)와; 상기차체(100)의하부에설치되며, 이온해수를통과시켜후미로발사하여그 반작용으로발생되는자기력을이용하여추진력을발생시키는적어도한 쌍의전자석코일건(400a-400d)과; 상기차체(100)의밑면에고정되어착륙시사용되는전륜및 후륜전자석도로바퀴(500a,500b)와; 상기회초리처럼휘어지는속이비어있도록형성되며, 상하날개짓을통하여상기차체(100)의공중비행및 수평을유지하는한 쌍의깃대날개(600a,600b)와; 자기장과해수흐름을이용하여전력을생산하는자가발전장치(700,700a)와; 수중비행시에는방수기능을유지하며, 공중비행시에는운전석이상부로솟아올라와서셰일을구축하는운전및 제어장치(800)로구성된다. | ||||||
| 123 | 틸트-큐브 무인기 | KR1020140109454 | 2014-08-22 | KR1020160023285A | 2016-03-03 | 장성호 |
| 본발명은틸트-큐브무인기에관한것으로, 더욱상세하게는고정익무인기의날개상에육방으로추력을가할수 있는직육면체형상의추진부를형성함으로써, 좁은장소에서도수직으로이착륙이가능하며, 측풍에취약하지않을뿐만아니라, 고정익에의해신속하게이동할수 있는틸트-큐브무인기에관한것이다. | ||||||
| 124 | 배터리보온장치가 포함된 고고도 전기동력 무인기용 배터리팩 | KR1020140168002 | 2014-11-28 | KR101599035B1 | 2016-03-03 | 박부민; 이보화 |
| 본발명은고고도에서동작하는무인기에서사용되는리튬이온배터리팩의온도를제어하는배터리보온장치가포함된고고도전기동력무인기용배터리팩을개시(introduce)한다. 상기배터리보온장치가포함된고고도전기동력무인기용배터리팩은, 고고도에서동작하는무인기에전기동력을제공하는배터리보온장치가포함된것으로, 배터리셀, 배터리관리시스템및 배터리보온장치를포함한다. 상기배터리관리시스템은상기배터리셀의동작을제어한다. 상기배터리보온장치는상기배터리셀의온도를제어한다. 특히상기상기배터리보온장치는, 상기배터리팩의외부온도, 상기배터리셀의온도및 배터리관리시스템의온도중 적어도하나를측정하는적어도하나의온도센서, 상기배터리셀에열에너지를제공하는발열체및 상기온도센서의측정결과를이용하여상기발열체의온도를제어하는발열제어장치를포함한다. | ||||||
| 125 | 팽창형 동체와 조인드윙을 갖는 무인항공기 | KR1020140021311 | 2014-02-24 | KR1020150100026A | 2015-09-02 | 이희우 |
| 본 발명은 무인항공기에 관한 것으로 동체의 단순화와 초경량화를 도모하고 동체의 내충격성을 향상시켜 주며 비행효율과 단거리 이착륙성능 및 장기체공성능을 향상시켜주기 위해서 조인드윙과 연결되는 동체를 비활성기체로 충전되는 원통형 기낭을 포함하는 팽창형 동체로 형성하며, 상기 팽창형 동체의 노즈콘에는 추진기관을 구비하고, 상기 팽창형 동체의 후단부에는 방향타를 포함하는 수직날개를 구비하여서 된 것을 특징으로 한다.
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| 126 | 친환경 기능성 상도 도료 조성물 및 이의 제조 방법 | KR1020120002004 | 2012-01-06 | KR1020130081046A | 2013-07-16 | 우정훈; 유병일 |
| PURPOSE: An environment-friendly functional top-coat paint composition is provided to provide environment-friendly paint with low VOC content, which is capable of reducing the usage amount of solvents. CONSTITUTION: A top-coat paint composition contains 50-70 parts by weight of polyisocyanate curing agent, and 100 parts by weight of polyester main resin with 150-200 (mg KOH/g) of hydroxyl group and 1,000-2,000 (cps/25°C) of viscosity. The polyester main resin is obtained by mixing 35-42 parts by weight of neopentyl glycol, 15-30 parts by weight of adipic acid, and 20-25 parts by weight of isophtalic acid with nitrogen. | ||||||
| 127 | 하늘을 나는 자전거용 활공도약대 | KR1020100121759 | 2010-12-02 | KR1020100136954A | 2010-12-29 | 김재원 |
| PURPOSE: A leaping board for a flying bicycle is provided, which enables to take off a flying bicycle safely and secures user's safety. CONSTITUTION: A leaping board for a flying bicycle comprises: an iron tower main body(51) which has a trapezoidal shape and is installed to be erected; an electric elevator(52) which is installed in the inner center of the iron tower main body and is operated to move up and down; and a gliding guide rail(53) projected into a downward slope structure from the upper front of the iron tower main body. | ||||||
| 128 | 항공기 및 항공기 동체로 구조 크래들을 회수하는 방법 | KR1020090062907 | 2009-07-10 | KR1020100007782A | 2010-01-22 | 판코티,산티노; 발레리오,단테 |
| PURPOSE: An aircraft and a method of retrieving a rescue cradle into the aircraft fuselage are provided to keep aviation at fixed height without speed. CONSTITUTION: A fuselage(2) forms a path opening(12). A driving unit(3) transfers a rescue cradle(32). A first wall(16) moves between the close position for closing a first part(24) of the opening and a first opening position for allowing incoming and outgoing to the first part of the opening. An aircraft(1) comprises a member(39) connected to the first wall. The member comprises one or more flat surfaces(40). The member moves to the first location on the first wall. When the first wall is located at the first opening position, the flat surface forms the support surface for the cradle. The first wall is connected to the fuselage. | ||||||
| 129 | 플랫폼 부양용 상승력 제공장치 | KR1020030070876 | 2003-10-11 | KR1020050035046A | 2005-04-15 | 로빈슨,노만브이 |
| 본 발명은 반동 또는 충격력을 발생시킬 수 있고 회전하는 아마츄어의 마주보는 양단에(opposite ends) 위치하는 두개의 중량체 유니트를 포함하는 플랫폼을 부양하고 조종하는 상승력 제공장치에 관한 것이다. 회전하는 아마츄어에서 들어오는 질량체의 속도와 중량에 의해 증폭된 반동 또는 충격력에 의해 상승력이 제공된다. | ||||||
| 130 | AIRCRAFT HAVING SUPPORTING FUSELAGE | EP16761131.8 | 2016-03-09 | EP3279082A1 | 2018-02-07 | Bosio Blanco, Carlos Conrado; Blanco, Roberto Horacio; Klarenberg, Alejandro Jose |
The aircraft defines a lifting volume including at least part of the central body housing the transported payload. Said volume has a conventional aerodynamic profile along the longitudinal direction of the aircraft, with portions of wings projecting symmetrically and transversely at both sides thereof From the longitudinal axis said wings at each side shows corresponding first sections with negative dihedral and forward swept until reaching corresponding inflexion points from which two distal second sections or tracts projects with positive dihedral and back swept until reaching the wingtips of the projected wingspan. |
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| 131 | CARGO TRANSPORT SYSTEM AND METHOD BASED ON UNMANNED AERIAL VEHICLE | EP15768689 | 2015-03-05 | EP3125064A4 | 2017-03-01 | LI SHUFU |
| The present invention provides a cargo transport system and method based on an UAV. The cargo transport system includes an UAV (50) and a vehicle (10) that can send and receive the UAV, so that cargos can be transported between the vehicle (10) and another terminal (60) by the UAV (50); the UAV (50) is provided with a navigation system that guides the UAV (50) to fly between the vehicle (10) and the another terminal (60); the vehicle (10) includes: an UAV accommodating device (40) arranged at a top surface of the vehicle (10); an UAV sending controller (20) and an UAV receiving controller (30), which are arranged at the vehicle (10); and the UAV receiving controller (30) includes an identity verification unit (301) and a short distance guide unit (302). According to the cargo transport system based on an UAV of the present invention, the sending and receiving of the UAV (50) can be controlled by the vehicle (10), and the UAV (50) is accommodated in the UAV accommodating device (40). In addition, the vehicle (10) may also provide the identity verification information and the short distance guide information to the UAV (50) by the identity verification unit (301) and the short distance guide unit (302), so that the UAV (50) can determine a target vehicle and accurately land on the target vehicle. | ||||||
| 132 | PROCÉDÉ D'EXPLOITATION D'UN ENGIN, TEL QUE NOTAMMENT UN DRONE ET DISPOSITIF POUR SA MISE EN OEUVRE | EP16151645.5 | 2016-01-18 | EP3051375A1 | 2016-08-03 | LAURENT, Eric; LEGRAND, Thomas |
La présente invention concerne un procédé d'exploitation d'un engin (1), tel que notamment un drone (1), destiné à être envoyé en mission au sein d'un espace géographique à couvrir, ledit procédé comportant une étape de détermination de la trajectoire à parcourir par ledit engin (1) au cours de sa mission, et une étape de pilotage automatique dudit engin (1), dans lequel: Il est caractérisé en ce qu'on réalise l'étape de pilotage au moyen dudit module électronique qui définit l'ensemble des paramètres de ladite trajectoire à parcourir par ledit engin, après un échange de données, incluant la transmission des paramètres relatifs à l'espace géographique à couvrir, entre ledit appareil mobile (2) embarqué à bord dudit engin (1) et ledit module électronique (4) dudit engin (1) L'invention concerne également un dispositif pour la mise en oeuvre d'un tel procédé.
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| 133 | An aircraft | EP14192431.6 | 2014-11-10 | EP2878538B1 | 2016-05-18 | Moxon, Matthew |
| 134 | TRANSPORTATION SYSTEM INCLUDING A HOVERING VEHICLE | EP12714191.9 | 2012-04-05 | EP2697107B1 | 2015-09-30 | GOELET, John |
| A transportation system is disclosed. The transportation system has a vehicle that is self-powered and configured to generate an air cushion on a trackless lane having a substantially flat surface. The vehicle is configured to move over the substantially flat surface on the air cushion. The transportation system also has a guidance system configured to guide the vehicle between peripheries of the trackless lane. | ||||||
| 135 | An unmanned aircraft with failsafe system | EP13181174.7 | 2013-08-21 | EP2840022A1 | 2015-02-25 | De Smet, Bjorn; De Moor, Maarten; Cosyn, Peter |
An unmanned aircraft (101; 201) comprises: The controller (304) is then adapted to activate the reverse thrust system (301) in order to reverse thrust the unmanned aircraft (101; 201) in-flight upon notification from the detector (302) that the unmanned aircraft (101; 201) is in an uncontrolled situation.
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| 136 | AIRBORNE PLATFORM | EP12715455.7 | 2012-03-15 | EP2712346A2 | 2014-04-02 | COSTA DUARTE PARDAL, Tiago; MARQUES DOS SANTOS SILVA, Pedro Miguel |
| The invention pertains to aeronautical engineering and consists of an airborne platform that can be built to large sizes without requiring a rigid structure of comparable dimensions and which uses both buoyancy and the aerodynamic Magnus effect for lift. The aerodynamic lift is generated in lifting bodies (1), which also contain buoyant gas. The" lifting bodies (1) are stacked in a column, at the bottom of which there is a structural anchoring module (2) which also contains buoyant gas. ^The lifting bodies (1) and anchoring modules (2) are connected by slender structural elements which, when taken together as a whole form a non-rigid assembly. The platform may be tethered or configured as an aircraft, for which purpose other features may be added, such as a propulsion system (11), a crew gondola (6), cables to (7) and from (8) a swivel (12) and a payload (10) connected to said cables. | ||||||
| 137 | THE DEVICE TO GENERATE LIFT FORCE (OPTIONS) | EP11744111.3 | 2011-06-06 | EP2658776A2 | 2013-11-06 | Akhmejanov, Alibi |
| The options of the invention relate to the aviation and can be used in order to create lifting vehicle as well as load lifting devices. In order to achieve technical result - the decrease of energy losses on the while creating and change of vector of moving, aerodynamic, composite force, including as a component a lift force, - in the device to generate lift force containing a tubiform frame, superchargers, the wings having in section an aerofoil profile oriented by the leading edge to the direction of working medium exhaust out of the super-charger, adjusting units for a wing, guiding devices, each of those is installed in front of leading edge of each wing, the system to maintain the required working temperature of medium, unit to connect outdoor environment, as per the invention in the first option of the device a tubiform frame is of the form of a tore, in the second option - the form of closed volumetric loop, in the third option - a cylindrical form. Meanwhile each option of the device is equipped with relevant distinguishing units, providing the achieving of a technical result. | ||||||
| 138 | Self-righting frame and aeronautical vehicle | EP12165691.2 | 2012-04-26 | EP2517767A3 | 2013-03-27 | Dees, James; Yan, Gaofei |
An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.
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| 139 | WINGLESS HOVERING OF MICRO AIR VEHICLE | EP07813600.9 | 2007-07-31 | EP2046640A1 | 2009-04-15 | ROY, Subrata |
| Embodiments of the subject invention relate to a Wingless Hovering Micro Air Vehicle (WHOMAV) and its Power Source Unit (PSU). Embodiments can operate at reasonable power levels for hovering and withstanding expected wind gusts. Embodiments of the subject invention can have a diameter less than 15 cm. Embodiments can have one or more smooth (continuous curvature) surface and can be operated using electromagnetic and electrohydrodynamic principles. The wingless design of specific embodiments can allow operation with no rotating or moving components. Additional embodiments can allow active response to the surrounding flow conditions. The issue of low lift to drag ratio and degradation of airfoil efficiency due to the inability of laminar boundary layers attachment can also be significantly reduced, or eliminated. The electromagnetic force can be generated by applying a pulsed (alternating/rf) voltage between a set of grounded and powered electrodes separated by a polymer insulator, dielectric, or other material with insulating properties. | ||||||
| 140 | FLYING DISK SHAPED FLYING/SPACE VEHICLE WITH THE USE OF A NEW TECHNIC OF THRUST THROUGH THE ROLLING OF A WHEEL | EP01958261.8 | 2001-08-07 | EP1307655A1 | 2003-05-07 | Hatzistelios, Nikolaos C. |
| This invention called airwheel, concerns of a flying disk shaped flying/space vehicle with the use of a new technic of thrust through the rolling of a wheel. If we exercise a force from a fixed point on the edge of a turning wheel (fixed related to the main body of the vehicle) and the direction of the force is opposite to the direction of the linear speed of the edge, then we will simulate the friction force between the turning wheel of a car and the road which forces the rolling of the car wheel and not just the revolving of it. The airwheel uses to roll (fly) a wheel named in the invention rolling wheel (b) and it embraces the main body (a) of the airwheel as well as an other wheel (Angular Momentum Maintenance Wheel (c)) which turns the other way around to maintain the angular momentum. The airwheel uses nozzles (k) to manoeuvre. Airwheel ingests atmospheric air to fly and avoids/standsup against air pockets using gas saved in a cylindric tank in it which diverts gas under great pressure to the nozzles. For the interplanetary flight airwheel uses the magnetic fields of the magnetosphere, magnetotail and the magnetic fields of solar wind. It comprises T-shaped telescopic devices which on the upper side of the 'T' contain couples of superconductor bobbins. | ||||||
