| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | 헬리콥터 앤티토크 테일 회전기 블레이드 | KR1020090044977 | 2009-05-22 | KR1020090122149A | 2009-11-26 | 브로클허스트알란; 스칸드로글리오알레산드로 |
| PURPOSE: A helicopter anti-torque tail rotor blade is provided to improve design of a free end of the blade and reduce acoustic emission of an anti-torque tail rotor. CONSTITUTION: A helicopter anti-torque tail rotor blade includes a leading edge(8), a trailing edge(9), and an end(14c). The trailing edge interacts with an air current of a rear part of the leading edge. The end is extended between a reference section(51) and a section(11) outside a radius direction for a rotation axis of the blade. Length of a cord at the end decreases as it goes from the reference section to the end. In the end, the leading edge and the trailing edge are combined. | ||||||
| 22 | 복합재료 날개 구조물의 피로수명 평가 방법 | KR1020140115174 | 2014-09-01 | KR1020160027529A | 2016-03-10 | 장준환; 이윤표 |
| 본발명에따른복합재료날개구조물의피로수명평가방법은블레이드시편에가해지는원심력과수직하중을측정하기위해로드셀을장착하는단계, 블레이드각 단면에부가되는플랩모멘트(moment of flap)와래그모멘트(moment of lag) 측정을위해풀 브릿지(Full-Bridge) 회로를장착하는단계, 하중을단계적으로높여가며블레이드구조물이파손될때까지복수회의사이클까지피로시험을수행한후 정적및 동적변형률을계산하는단계, 정적변형률과동적변형률을혼합하여등가변형률을계산하여복합재날개구조물에대한피로선도를얻는단계, 및피로하중스펙트럼을이용하여피로평가를수행하여복합재료날개복합재료날개구조물의피로수명을계산하는단계;을포함하여, 복합구조구성품의피로수명을정확히측정할수 있는효과가있다. | ||||||
| 23 | 로터 블레이드의 온도측정장치 | KR1020100033410 | 2010-04-12 | KR1020110114013A | 2011-10-19 | 김경삼 |
| 본 발명이 해결하려는 과제는 지상에서 로터 블레이드의 온도와 상기 온도에 도달하는 시간을 측정하기 위한 로터 블레이드의 온도측정장치를 제공하는 것이다. 본 발명 로터 블레이드의 온도측정장치는 로터 블레이드를 가열하기 위한 히터매트부와; 상기 히터매트부에 공급되는 전원을 제어하는 제어부와; 상기 히터매트부에 의해 가열된 로터 블레이드의 온도를 측정하는 센서부와; 상기 히터매트부에 전원이 공급된 시간을 측정하는 측정부로 구성되어 지상에서 로터 블레이드의 온도와 상기 온도에 도달하는 시간을 측정하기 위한 것을 특징으로 한다. 본 발명에 의하면, 지상에서 로터 블레이드의 온도와 상기 온도에 도달하는 시간을 측정할 수 있으므로 상당한 시간과 비용을 절약할 수 있으며, 측정된 결과를 이용하여 로터 블레이드에 공급되는 열을 제어하여 로터 블레이드를 효율적으로 제빙할 수 있다. 또한, 히터매트를 복수개로 구성할 수 있으므로 로터 블레이드의 영역별 온도와 상기 온도에 도달하는 시간을 측정 할 수 있다. | ||||||
| 24 | 갈라진 형태의 로터 블레이드를 구비하는 로터 장치 | KR1020027000193 | 2000-07-06 | KR100469515B1 | 2005-02-02 | 배너슈,루돌프 |
| 본 발명은 로터 축 주위를 회전하게끔 배열되는 적어도 하나의 로터 블레이드(4)가 구비되며 유체가 주요 흐름방향(H)을 따라 관통하게 되는 로터(1)에 대한 것이다. 상기 로터 블레이드(4)는 회전축(2)로부터 유체 안으로 적어도 부분적으로 연장된다. 로터 블레이드(4)가 회전축(2) 주위로 회전(D)하게 되면 상기 유체의 주요 흐름방향과는 반대방향으로 추진력이 발생하게 되거나, 유체의 흐름에 의해 회전축 주위로 토크(torque)가 발생된다. 본 발명의 목적은 이러한 유형의 로터장치에서 로터 블레이드의 끝에서 발생하게 되는 소용돌이를 감소시켜서 유체의 흐름에 따른 손실과 손실을 감소기키는데 있다. 상기 로터 블레이드(4)는 회전축으로부터 일정한 거리만큼 떨어진 지점에서 적어도 두 개의 부분 블레이드(5, 6)으로 갈라지고 이 갈라진 두 부분 블레이드는 고리를 형성한다. 하나의 부분 블레이드(5)는 로터 블레이드(4)와 인접하는 적어도 한 영역에서 로터 블레이드(4)에 대해 회전방향(D)으로 연장되며, 다른 하나의 부분 블레이드(6)는 로터 블레이드(4)와 인접하는 적어도 한 영역에서 로터 블레이드(4)에 대해 회전방향(D)과 반대방향으로 연장된다. 상기 두 개의 부분 블레이드(5, 6)는 그들의 끝에서 하나로 결합되어 유체가 관통하게되는 루프면(12)을 형성한다. | ||||||
| 25 | PROPELLER | EP13875362.9 | 2013-12-09 | EP2941539B1 | 2018-10-17 | SHARROW, Gregory Charles |
| A propeller having a central post to which one or more blades are connected. The blades are disposed and configured to pull air in from the propeller's sides toward the propeller's axis of rotation to create pressure in an area in the vicinity of the center of the propeller's rotating axis for generating thrust. | ||||||
| 26 | VARIABLE GEOMETRY LIFT FAN MECHANISM | EP13830270 | 2013-08-23 | EP2888165A4 | 2016-04-13 | LONG GEOFFREY A; LYASOFF RODIN |
| 27 | PROPELLER | EP13875362.9 | 2013-12-09 | EP2941539A2 | 2015-11-11 | SHARROW, Gregory Charles |
| A propeller having a central post to which one or more blades are connected. The blades are disposed and configured to pull air in from the propeller's sides toward the propeller's axis of rotation to create pressure in an area in the vicinity of the center of the propeller's rotating axis for generating thrust. | ||||||
| 28 | METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS | EP12822015 | 2012-08-03 | EP2740210A4 | 2015-03-18 | GILES ALAN M; MACHIN JAMES T; GERIGUIS JOHN A |
| Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface. | ||||||
| 29 | Rotor blade having passive bleed path | EP11165283.0 | 2011-05-09 | EP2390178A3 | 2014-12-17 | Denner, Brett W.; Domel, Neal D. |
A rotor blade (14) includes a bleed path (30) opening to a suction surface (28) eg. via inlet (32), extending through the blade (14), eg. via conduit (34), and exiting, eg. via outlet (36), to at least one of the suction surface (28) or a trailing surface (24). Working fluid flows through the bleed path (30) under centrifugal pumping forces when the blade rotates to passively bleed working fluid from the suction surface (28).
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| 30 | LOW LIGHT LEVEL ILLUMINATION FOR ROTATING OBJECTS | EP03765842 | 2003-07-22 | EP1540239A4 | 2010-12-15 | BUCKINGHAM THOMAS M; ELGER WALLACE M |
| 31 | Method and apparatus for modulating airfoil lift | EP03254503.0 | 2003-07-18 | EP1384896A3 | 2006-08-16 | Saddoughi, Seyed Gholmali; Leyva, Ivett Alejandra; Dean, Anthony John; Robic, Bernard Francois; Butler, Lawrence |
An apparatus (100) comprising: an airfoil (110) adapted for generating a lift force; and a first pulse detonation actuator (120) disposed inside the airfoil (110) and adapted for impulsively detonating a fuel/air mixture to produce a pressure rise and velocity increase of combustion products therein, the airfoil (110) having a plurality of lift control holes (130) adapted for communicating combustion product flows from the first pulse detonation actuator (120) to an airfoil surface (140) to modulate the lift force.
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| 32 | PROPROTOR BLADE WITH LEADING EDGE SLOT | EP03815629.5 | 2003-01-23 | EP1585665A1 | 2005-10-19 | ROBERTSON, Daniel, B.; SMITH, Dudley, E.; HOLLIMON, Charles, L.; NARRAMORE, Jimmy, C.; MULLINS, Robert, B. |
| A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so that a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades. | ||||||
| 33 | ROTOR MIT GESPALTENEM ROTORBLATT | EP00945889.4 | 2000-07-06 | EP1196696B1 | 2003-05-07 | Bannasch, Rudolf |
| The invention relates to a rotor (1) through which a fluid flows in a main direction of flow (H) and which is provided with at least one rotor blade (4), said rotor blade being arranged in such a way that it can rotate about a rotor axis. The rotor blade (4) extends away from the axis of rotation (2), into the fluid, at least in sections. The rotation (D) of the rotor blade (4) about the axis of rotation (2) in a predetermined direction of rotation produces a propulsive thrust in the opposite direction to the main direction of flow, or a torque is produced about the axis of rotation as a result of the flow. The aim of the invention is to reduce the trailed tip vortex at the end of the rotor blades of rotors of this type and therefore to reduce the fluidic losses and flow noise. To this end, the rotor blade (4) extends in at least two partial blades (5, 6) at a set distance from the axis of rotation and forms a loop. One partial blade (5) extends in the direction of rotation (D) in relation to the rotor blade, at least in one area close to the rotor blade. The other partial blade extends in the opposite direction to the direction of rotation (D) in relation to the rotor blade (4), at least in one area close to the rotor blade (4). The two partial blades (5, 6) are interconnected in one piece at their ends so that they encompass a loop surface (12) through which the fluid flows, said loop surface extending essentially crosswise to the main direction of flow. | ||||||
| 34 | ROTOR MIT GESPALTENEM ROTORBLATT | EP00945889.4 | 2000-07-06 | EP1196696A2 | 2002-04-17 | Bannasch, Rudolf |
| The invention relates to a rotor (1) through which a fluid flows in a main direction of flow (H) and which is provided with at least one rotor blade (4), said rotor blade being arranged in such a way that it can rotate about a rotor axis. The rotor blade (4) extends away from the axis of rotation (2), into the fluid, at least in sections. The rotation (D) of the rotor blade (4) about the axis of rotation (2) in a predetermined direction of rotation produces a propulsive thrust in the opposite direction to the main direction of flow, or a torque is produced about the axis of rotation as a result of the flow. The aim of the invention is to reduce the trailed tip vortex at the end of the rotor blades of rotors of this type and therefore to reduce the fluidic losses and flow noise. To this end, the rotor blade (4) extends in at least two partial blades (5, 6) at a set distance from the axis of rotation and forms a loop. One partial blade (5) extends in the direction of rotation (D) in relation to the rotor blade, at least in one area close to the rotor blade. The other partial blade extends in the opposite direction to the direction of rotation (D) in relation to the rotor blade (4), at least in one area close to the rotor blade (4). The two partial blades (5, 6) are interconnected in one piece at their ends so that they encompass a loop surface (12) through which the fluid flows, said loop surface extending essentially crosswise to the main direction of flow. | ||||||
| 35 | Air propeller | EP84890156 | 1984-08-16 | EP0138800A3 | 1988-01-13 | Asboth, Oscar |
| 36 | 무인 항공기용 프로펠러의 최적 설계 시스템과 방법 | KR1020160082228 | 2016-06-30 | KR101810780B1 | 2017-12-19 | 위성용; 강희정 |
| 일실시예에따른무인항공기용프로펠러의최적설계시스템은, 블레이드의형상을나타내는형상함수및 상기블레이드의형상을최적화하기위한목적함수가입력되는입력부; 상기형상함수에기초하여블레이드의형상이생성되는익형생성부; 상기블레이드의형상에대하여성능이해석되는성능해석부; 상기성능해석부에서해석된성능데이터에기초하여상기목적함수가연산되는연산부; 및상기블레이드의최적형상이결정되는최적형상결정부;를포함하고, 상기최적형상결정부에서블레이드의최적형상은상기연산부에서연산된목적함수의값이최소값인경우의블레이드형상으로결정될수 있다. | ||||||
| 37 | 항공기용 프로펠러 블레이드 | KR1020130158982 | 2013-12-19 | KR1020150071884A | 2015-06-29 | 안정희; 조규철; 최민수; 조재범; 정혜영 |
| 본발명은블레이드의구조를분리제작한후 결합함으로써각 구성간의결합력을더욱높이면서제작의용이성및 내구성을보다향상시키며, 저중량고강도를실현할수 있는항공기용프로펠러블레이드에관한것으로, 항공기를구동하는회전모터의구동샤프트에결합되어함께회전하는로터허브에방사상으로결합된항공기용프로펠러블레이드에있어서, 상기블레이드는, 분리된상판및 하판의결합으로하나의몸체를이루며, 에어포일형상으로된 블레이드몸체및 상기로터허브에결합되는블레이드헤드를포함하고, 상기블레이드의상판및 하판은, 각각서로마주보는면에내부로코어홈이함몰형성되고, 상기블레이드는, 상기코어홈의내부에결합되는내부코어를더 포함하고, 상기블레이드의상판, 하판및 내부코어각각은, 유리섬유또는탄소섬유로이루어진섬유재를수지로다층접착하여경화시킨섬유강화복합소재(FRP, Fiber Reinforced Plastics)에의해제작된것을특징으로한다. | ||||||
| 38 | 공기 부양정 | KR1020110132506 | 2011-12-12 | KR1020130065905A | 2013-06-20 | 이찬우 |
| PURPOSE: A hovercraft is provided to improve external soundproof properties and reduce external exposure by sealing a casing and minimizing noise generation due to a propeller. CONSTITUTION: A hovercraft(1) comprises a hull(2), an engine(3), a dynamics propeller(4), and a casing(50). The engine and dynamics propeller are equipped in the rear side of the hull. The dynamics propeller rotates through the power of the engine to move the hull. The casing is hermetically equipped in the outer circumference of the dynamics propeller. The casing comprises a plurality of air intake ports(52) in the front side, a plurality of lateral exhaust ports(56) in the rear side, and rear and lateral blades. The rear and lateral blades selectively open or close rear and lateral exhaust ports. | ||||||
| 39 | 한 개의 구동 원에 연결된 동심 이축의 반전 구동 시스템과 이를 포함하는 회전 장치에 관한 것이다. | KR1020100077521 | 2010-08-11 | KR1020120062034A | 2012-06-14 | 박태균 |
| PURPOSE: A reversal driving system and a rotation apparatus including the same are provided to fixes a main shaft and a driven shaft to one panel by rotating the main shaft and the driven shaft to a reverse direction. CONSTITUTION: A shaft(A) rotates in a forward direction. The shaft is a main gear. A gear(C) rotates in the forward direction. Gears(D, E, F) rotate in a reverse direction. A gear shaft of the gears is separately or simultaneously is fixed to a panel. The panel supports the gears. The gears are an intermediate gear. A ring having a bearing is inserted into the gear shaft of the gears. A gear(G) is a concave gear. The gear is a driven gear. | ||||||
| 40 | PROPELLER BLADE SHEATH | EP16305594.0 | 2016-05-23 | EP3248867A1 | 2017-11-29 | ANDRZEJEWSKI, Arnaud; PICARD, Pierre-Alex; PRUNET, Ludovic; VIGIER, Frédéric; MOLES, Patrick |
Disclosed herein is a propeller blade assembly (10) comprising an airfoil (22) having a base (24), a tip (26) and a leading edge (28) and a root (30) extending from the base (24) of the airfoil (22) for attaching the airfoil (22) to a hub. The assembly (10) further comprises an electrically conductive sheath (40) for electrically grounding the airfoil (22). The electrically conductive sheath (44) is attached to the leading edge (28) of the airfoil (22) and extends from the base (24) to the tip (26) of the airfoil (22). The assembly (10) further comprises an electrically conductive element (50) for electrically connecting the electrically conductive sheath (40) to the root (30) or hub. Also disclosed is an electrically conductive sheath (40) for grounding an airfoil (22) and a method for assembling a propeller blade assembly (10).
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