子分类：
- B64C11/001： .{闭式螺旋桨}
- B64C11/002： .{制动螺旋桨,如用于测量发动机的功率输出}
- B64C11/003： .{可变直径的螺旋桨;相关的机械装置}
- B64C11/005： .{螺旋形螺旋桨}
- B64C11/006： .{桨轮}
- B64C11/007： .{推进盘,即具有专用于推进目的表面的推进盘}
- B64C11/008： .{以振动吸收或平衡装置为特点的(用于旋翼飞机B64C27/001)}
- B64C11/02： .桨毂结构
- B64C11/16： .桨叶
- B64C11/30： .桨叶变距机构
- B64C11/46： .多个螺旋桨的配置或其特有的结构特征{(B64C11/306优先)}
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | 비행체의 날개 전개 장치 및 이를 구비한 비행체 | KR1020180076367 | 2018-07-02 | KR101913688B1 | 2018-10-31 | 이승진; 안정우; 박진용; 조용주 |
| 본발명의실시예에따른비행체의날개전개장치는, 낙하산구조물이연결되는분리기구, 및상기분리기구가분리가능하게연결되고, 비행체의전방날개와후방날개각각에연결되며, 상기낙하산구조물의저항력에따라상기전방날개와상기후방날개를전개하는날개전개부를포함한다. | ||||||
| 82 | 프로펠러 풍동시험 장치 | KR20180064829 | 2018-06-05 | KR20180064366A | 2018-06-14 | 조태환; 김양원 |
| 본발명은추력센서에모터등의자중이미치는영향을미연에막을수 있는프로펠러풍동시험장치를제공하는것이그 기술적과제이다. 이를위해, 본발명의프로펠러풍동시험장치는, 고정받침부재를포함하는기둥부; 상기기둥부에고정되는추력센서부; 상기추력센서부의앞에구비되는구동모듈; 및상기구동모듈을상기고정받침부재에이동가능하게받치는이동받침부를포함한다. | ||||||
| 83 | 지면 이동 및 자력 상승 가능한 드론 | KR1020150177185 | 2015-12-11 | KR101807082B1 | 2017-12-08 | 곽승계 |
| 본발명은, 구름부재를구비하는메인프레임; 상기메인프레임에스윙가능하게설치되는서브프레임; 상기서브프레임에설치되는로터; 및상기로터의회전방향이달라지도록상기로터에공급되는전류의극성을변환하여, 상기구름부재가지면에의해구르게하거나, 상기구름부재가지면위로상승하게하는제어유닛을포함하는, 지면이동및 자력상승가능한드론을제공한다. | ||||||
| 84 | 지면 이동 및 자력 상승 가능한 드론 | KR1020150177185 | 2015-12-11 | KR1020170069679A | 2017-06-21 | 곽승계 |
| 본발명은, 구름부재를구비하는메인프레임; 상기메인프레임에스윙가능하게설치되는서브프레임; 상기서브프레임에설치되는로터; 및상기로터의회전방향이달라지도록상기로터에공급되는전류의극성을변환하여, 상기구름부재가지면에의해구르게하거나, 상기구름부재가지면위로상승하게하는제어유닛을포함하는, 지면이동및 자력상승가능한드론을제공한다. | ||||||
| 85 | 비행기 구조체 | KR1020150155253 | 2015-11-05 | KR101627680B1 | 2016-06-07 | 남양우 |
| 본발명비행기구조체는비행의안정성이향상되고복수의로터블레이드를구비하여서어느하나의블레이드가손상되더라도추락의위험성을줄일수 있도록한다. | ||||||
| 86 | 엘리본 제어 시스템 | KR1020127009072 | 2010-09-09 | KR1020120098607A | 2012-09-05 | 미랄레스,카로스토마스; 프럼브,닉; 타우,슈요; 올센,나탄 |
| 본 발명은, 동체 하우징 편향 액츄에이터 혼(621, 622)을 대향하는 탄성장착된 트레일링 에지를 가진 에어포일(141, 142, 1345, 1346)을 통해 키놀이, 옆놀이, 및/또는 빗놀이를 제어하도록 구성된 항공기 또는 무인 항공기(UAV)(100, 400, 1000, 1500)를 포함하는 시스템에 관한 것이다. 실시형태들은, 회전 가능하게 부착되며 이펙터 부재(1049, 1149, 1249, 1349)에 의해 작동될 수 있는 하나 이상의 방향타 요소(1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546)를 포함하고, 상기 이펙터 부재는 동체 하우징(1001) 내에 배치되며, 하나 이상의 방향타 요소들과 맞물리도록 일부 신장 가능하다.
|
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| 87 | Thrust measuring apparatus | KR20100139884 | 2010-12-31 | KR20120077798A | 2012-07-10 | KIM SUNG YUG; KIM DONG MIN |
| PURPOSE: A thrust measuring device is provided to minimize influence according to an installation posture of a thrust measuring device and to enhance the accuracy of a thrust measurement. CONSTITUTION: A thrust measuring device comprises a base body(10), a rotary shaft(20) for fixing a platform, a thrust generator platform(30), top and bottom balancing weights(51,52), right and left balancing weights(61,62), and a pressure sensor(40). The rotary shaft is fixed on the top of the base body. The thrust generator platform rotates by being integrated with the rotary shaft for fixing the platform. The top and bottom balancing weights are arranged top and bottom centroids of the thrust generator platform on a rotary center of the rotary shaft for fixing the platform. The right and left balancing weights are arranged right and left centroids of the thrust generator platform on the rotary center of the rotary shaft for fixing the platform. The pressure sensor detects pressure in which a right extension unit(34) of the thrust generator platform pushes when the thrust generator platform rotates. | ||||||
| 88 | 프로펠러 추력 측정기 | KR1020060070979 | 2006-07-27 | KR1020080010676A | 2008-01-31 | 장진한; 한종수; 김동현 |
| A measuring apparatus for propeller thrust is provided to improve accuracy of measurement by minimizing loss of power supplied from an engine or motor in the case of thrust measurement. A measuring apparatus for propeller thrust comprises a standing support, a driving unit(5), a mount(7), and a mounting pad(9) for installing a push-pull gauge(8). The standing support is formed with upper, lower and vertical frames and serves as a support pad. The driving unit is connected to guide bars(3) installed in both sides of the upper frame via a bearing(4). The mount is mounted with a propeller(6) in the driving unit. The mounting pad for measuring thrust of the propeller is selectively installed on the upper frame at the front and the back of the driving unit. | ||||||
| 89 | 엘리본 제어 시스템 | KR1020187030734 | 2010-09-09 | KR1020180120778A | 2018-11-06 | |
| 본발명은, 동체하우징편향액츄에이터혼을대향하는탄성장착된트레일링에지를가진에어포일을통해피치(pitch), 롤(roll), 및/또는요우(yaw)를제어하도록구성된항공기또는무인항공기(UAV)를포함하는시스템에관한것이다. 실시형태들은, 회전가능하게부착되며이펙터부재에의해작동될수 있는하나이상의방향타요소를포함하고, 상기이펙터부재는동체하우징내에배치되며, 하나이상의방향타요소들과맞물리도록일부신장가능하다. | ||||||
| 90 | 엘리본 제어 시스템 | KR1020127009072 | 2010-09-09 | KR101914305B1 | 2018-11-01 | 미랄레스,카로스토마스; 프럼브,닉; 타우,슈요; 올센,나탄 |
| 본발명은, 동체하우징편향액츄에이터혼(621, 622)을대향하는탄성장착된트레일링에지를가진에어포일(141, 142, 1345, 1346)을통해키놀이, 옆놀이, 및/또는빗놀이를제어하도록구성된항공기또는무인항공기(UAV)(100, 400, 1000, 1500)를포함하는시스템에관한것이다. 실시형태들은, 회전가능하게부착되며이펙터부재(1049, 1149, 1249, 1349)에의해작동될수 있는하나이상의방향타요소(1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546)를포함하고, 상기이펙터부재는동체하우징(1001) 내에배치되며, 하나이상의방향타요소들과맞물리도록일부신장가능하다. | ||||||
| 91 | 프로펠러 풍동시험 장치 | KR20160143615 | 2016-10-31 | KR20180047494A | 2018-05-10 | 조태환; 김양원 |
| 본발명은추력센서에모터등의자중이미치는영향을미연에막을수 있는프로펠러풍동시험장치를제공하는것이그 기술적과제이다. 이를위해, 본발명의프로펠러풍동시험장치는, 고정받침부재를포함하는기둥부; 상기기둥부에고정되는추력센서부; 상기추력센서부의앞에구비되는구동모듈; 및상기구동모듈을상기고정받침부재에이동가능하게받치는이동받침부를포함한다. | ||||||
| 92 | 비행체용 덕트 팬 | KR1020140182027 | 2014-12-17 | KR1020160073570A | 2016-06-27 | 정진덕 |
| 본발명은덕트팬을구비한비행체에관한것이다. 본발명의한 실시예에따른비행체용덕트팬은프로펠러, 상기프로펠러의하측에배치된스테이터(stator), 그리고상기프로펠러를둘러싸는덕트팬 하우징(ducted fan housing)을포함하며, 상기덕트팬 하우징은상기프로펠러의프로펠러면이선택적으로노출또는비노출되도록상기프로펠러의축 방향으로이동가능한다. 이를통하여, 본비행체용덕트팬은비행체의호버링상태에서는덕트팬 하우징이프로펠러의회전면아래로내려와측풍이불어도덕트팬에의한유동박리가발생하지않아프로펠러의효율이헬리콥터의로터와동일한수준으로유지할수 있다. 또한, 고속순항할때는덕트팬이기존장착상태로돌아와덕트팬의본래성능을발휘할수 있게된다. | ||||||
| 93 | 프로펠러부 전개식 무인 비행체 | KR1020150094614 | 2015-07-02 | KR101589263B1 | 2016-01-28 | 이선호 |
| 본발명은본체부와, 프로펠러가설치된복수의프로펠러부와, 상기프로펠러부가상기본체부상에겹쳐지게배치된상태를유지하도록상기프로펠러부를록킹시키는록킹유닛과, 상기본체부와각 프로펠러부를연결하며상기록킹유닛의록킹이해제됨에따라상기프로펠러부를상기본체부의주변위치로전개시키는전개부를포함하는프로펠러부전개식무인비행체를개시한다. | ||||||
| 94 | 무선 모형 헬리콥터 | KR1020060109402 | 2006-11-07 | KR100806921B1 | 2008-02-22 | 이금우; 서이환 |
| A radio control helicopter plate is provided to unify 90 and 120 degree-type swash plates that were used by being separately manufactured, and to promote flight stability by changing a position of a fuel tank. A radio control helicopter includes the swash plate comprising an upper plate, a spherical bearing, the lower plate(16), and a ball bearing. The lower plate has six link connection ends(21,22,23,24,25,26) integrally formed on the outer diameter surface at certain angles and having a shape that is vertically bent in an upper direction. | ||||||
| 95 | 스와시 플레이트 수평장치 및 이를 이용한 작동방법 | KR1020060056018 | 2006-06-21 | KR1020070121229A | 2007-12-27 | 정규영 |
| A swash plate leveling device and an operation method using the same are provided to set the horizontality of a swash plate without disassembling and assembling a model helicopter and to be used in common regardless of the size of the swash plate. In a swash plate leveling device(10) for setting horizontality of a swash plate installed in a model helicopter, the leveling device is provided with a staple-shaped section and installed at an edge portion of the swash plate. Both ends of the leveling device are symmetrically bent inward at the predetermined angle. An adjusting unit(11) having threads to fix the leveling device by applying force to the swash plate penetrates through the center of the leveling device. Plural level meters(14) are installed in one end of the leveling device to check that the swash plate is kept in a horizontal state, from the outside. | ||||||
| 96 | GIMBALED THRUSTER CONFIGURATION FOR USE WITH UNMANNED AERIAL VEHICLE | EP16867252.5 | 2016-11-18 | EP3380397A1 | 2018-10-03 | LUKACZYK, Trent; COLONNO, Michael |
| A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure. | ||||||
| 97 | ROTORCRAFT CONFIGURATION AND METHOD OF ROTORCRAFT DESIGN | EP15845805 | 2015-09-29 | EP3201081A4 | 2018-04-18 | MOFFITT BLAKE ALMY; WAKE BRIAN E; LORBER PETER F |
| A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof. | ||||||
| 98 | PROPELLER HEALTH MONITORING | EP16306182.3 | 2016-09-16 | EP3296195A1 | 2018-03-21 | EL HALOUI, Abdellah; PETELLAZ, Bruno |
A method for monitoring the health of propellers in an aircraft is provided. The method includes receiving pressure waves generated by at least one rotating propeller and analysing data corresponding to the received pressure waves to detect tonal noise which is within a selected frequency range. If tonal noise at harmonics of the propeller rotational frequency within the selected frequency range is detected within the selected frequency range, it is established that the health of at least one propeller may be impaired and an alert is created for inspection and maintenance to take place.
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| 99 | UAV whith deployable wings and method of flight control | EP10833732.0 | 2010-09-09 | EP2475575B1 | 2017-11-01 | MIRALLES, Carlos, Thomas; PLUMB, Nick; TAO, Tony Shuo; OLSEN, Nathan |
| A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100, 400, 1000, 1500) configured to control pitch, roll, and/or yaw via airfoils (141, 142, 1345, 1346) having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns (621, 622). Embodiments include one or more rudder elements (1045, 1046, 1145, 1146, 1245, 1345, 1346, 1445, 1446, 1545, 1546) which may be rotatably attached and actuated by an effector member (1049, 1149, 1249, 1349) disposed within the fuselage housing (1001) and extendible in part to engage the one or more rudder elements. | ||||||
| 100 | RESONANT BLADES USING AN APERTURE FOR CANCELLATION OF PROPELLER GENERATED NOISE | EP16709172.7 | 2016-02-10 | EP3227180A1 | 2017-10-11 | LINCH, Jonathon J. |
| An exemplary apparatus minimizes an aircraft propeller noise having an associated frequency and a corresponding wavelength. A resonant tone produced on the propeller blade elicits a sound with substantially the same frequency as the associated frequency of the offending source. The resonant tone is powered by an inflow of air in or across an aperture of a resonant structure during the rotation of the blade and the aperture has an opening from which the sound is emitted. The resonant structure is dimensioned to generate a sound with substantially the same frequency as the offending source. The aperture is located on the blade with the opening a distance from a target origin of the noise that is substantially one half of the wavelength of the noise so that the sound arrives at the target origin of the noise substantially 180 degrees out of phase with the noise. | ||||||
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