| 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 | Direct the rapid air flow generation wind direction changing device to the side and the side wall of the aircraft, it was created in close contact with the fixed aircraft | JP2004227322 | 2004-07-07 | JP3677748B1 | 2005-08-03 | 快堂 池田 |
| 【要 約】
【課 題】 風量は自在に変更可能なリニアモーターの駆動原理を有するシュラウド付回転翼、その吹き出し方向を自在に変更可能にすることによって、風量と風向の両方を自在に変更できる装置の作成を行い、作成した風量と風向を自在に変更できる装置を航空機の機体に取り付け、装置の風量と風向をコントロールすることによって、大量輸送と自在な飛行と安全な運行を省エネルギーで実現する。 【解決手段】 本発明は、直径が１０ｍや２０ｍを超える大型や超大型の急速風量発生風向変更装置を、機体の側面もしくは側壁に、片方当たり少なくとも１基、両方の側面もしくは側壁の合計で２基以上を取り付け、風量と風向を自在にコントロールできる急速風量発生風向変更装置の仕組みによって、大量の貨客輸送、空中での自在な飛行及び操縦容易で安全な省エネルギーの航空機を実現する。 【選択図】 図１５ |
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| 62 | Promotion linearization mechanism | JP2003519721 | 2002-08-06 | JP2004537680A | 2004-12-16 | アッシュワース，エリック |
| 流体流動制御機構を流体流動の線形化のために提供する。 該機構は、複数のプロペラ素子をその上に回動可能に支持する円筒状の外側バッフルを有するフレームを含む。 各プロペラ素子は、プロペラ素子が回動する各掃拭域を定義し、該掃拭域は、隣接するプロペラ素子の掃拭域と重複する。 外側バッフルは、各プロペラ素子の集合的掃拭域の外周に外接する。 該プロペラ素子は同方向に回動して、隣接するプロペラ素子の屈曲流動の力が実質的に互いに相殺され、前記機構を通過する流体流動は線形化されるのである。 羽根の非掃拭域内に追加されるバッフルと充填材とを、機構の特定用途のために設けてもよい。 様々な適用においては、接線流動の屈曲力の統合によって、ベクトル流動の線形力が形成され、そして、プロペラ回動平面上の屈曲力ポテンシャルの統合によって、効率流動系が形成され、放出流動と導入流動とを遮断し、これにより、動的流動の直近の流体は、乱されていない静的状態に保たれる。 これによって、流体推進組み立てにあたって、領域の静止帯域の外部効用マントルに備えることが可能となるのである。
【選択図】図１ |
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| 63 | Rootaa | JP15646479 | 1979-12-04 | JPH0231201B2 | 1990-07-12 | ARUBERUTO KURINGU |
| 64 | 동력 패러글라이더 | KR1020180010268 | 2018-01-26 | KR101862286B1 | 2018-05-29 | 송진석 |
| 본발명은동력패러글라이더에관한것으로서, 탑승자를수용할수 있는본체; 상기본체의상측에배치되며, 상기본체에양력을제공하기위한캐노피; 상기본체와상기캐노피를서로연결하는산줄; 상기본체에결합되어있으며, 상기본체에추진력을제공하는추력발생유닛; 상기추력발생유닛에의하여발생하는토크에의하여상기본체가받게되는비틀림모멘트를상쇄하기위한평형유지장치;를포함하며, 상기본체는, 전후방향으로연장된막대형상의부재로서, 한쌍이마련되어좌우방향로서로이격된상태로탑승자의상측에배치되는상측부재를포함하며, 상기평형유지장치는, 일단부가상기한 쌍의상측부재에결합되어있으며, 타단부는상기산줄에결합되어있는것을특징으로한다. 본발명에따르면, 상기본체의방향쏠림현상을제거함으로써비행안정성이증가하는효과가있다. | ||||||
| 65 | 틸트프롭 항공기 | KR1020160159422 | 2016-11-28 | KR101849246B1 | 2018-04-16 | 이명규; 최성욱; 김덕관 |
| 본발명에따르면, 날개에연결된로터의틸트각을조절하여수직이착륙또는전진비행여부를결정하는틸트프롭항공기(tilt-prop aircraft)에있어서, 틸트프롭항공기는, 로터에포함되고회전하여양력및 추력을발생시키는블레이드; 및상기로터와상기날개를연결하고상기틸트프롭항공기의비행평면에대한상기로터의틸트각을조절하는틸트중심축;을포함하고, 상기로터의틸트각조절시, 상기틸트중심축과기계적으로연동된동력전달수단을통해상기블레이드의피치각이변화하는틸트프롭항공기가제공된다. | ||||||
| 66 | 수공양용 쿼드콥트 | KR1020150013989 | 2015-01-29 | KR1020160093242A | 2016-08-08 | 이원영 |
| 본발명은공중과수중에서사용할수 있는수공양용쿼드콥트에관한것이다. 보다상세하게는, 본체의전후좌우에각각설치되어본체에구비된전원부의전원으로작동되는구동모터의구동축에설치된다수개의프로펠러가구동모터의작동에의해고속으로상승회전운동하면서상승양력에의해공중비행이가능하고특히, 상승회전운동과반대되는하강회전운동을하면서하강양력을발생시킴과동시에본체하부케이스에구비된공기또는물를저장하는밸러스트탱크, 밸러스트탱크내부에설치된밸브와밸브를통해물을유입또는배출하여부력을조절하는펌프를포함하는부력조절장치를이용하여수중잠수기동이가능한수공양용쿼드콥트에관한것이다. 이를위해본 발명은사용자의조종기와무선통신을수행하는통신부, 통신부의제어명령을전송받아비행과잠수자세제어및 임무수행을위해장착된전자장비를제어하기위한제어부, 전기를요하는장치에전원을공급하며충전가능한전원부를포함하는상부케이스, 공기또는물를저장하는밸러스트탱크, 밸러스트탱크에장착되는하나이상의밸브및 밸브를통해물을유입또는배출하여부력을조절하는하나이상의펌프를포함하는하부케이스, 및상부케이스와하부케이스사이를분리하며방수기능을구비한방수패널을포함하는본체; 본체일측에부착되는온도센스및 방수기능을구비한카메라를포함하는탐지장치; 및본체에전후좌우에대칭적으로고정설치되어외측으로연장된지지프레임; 및지지프레임이관통되어본체에고정되고실린더형상으로수직관통되어공기또는물이통과할수 있는관통유로를구비한덕트, 및덕트의중앙부에위치한지지프레임의말단에설치되고전원부로부터전원을공급받아본체에추진력을제공하며방수기능을구비한구동모터, 및구동모터와구동축에의해연결되는프로펠러를포함하는복수의구동로터를포함하는수공양용쿼드콥트를제공한다. | ||||||
| 67 | 슈라우드형 추진 로터리 어셈블리용 공기역학적 외부 환상면 스포일러를 구비한 블레이드 로터리 어셈블리 | KR1020140048260 | 2014-04-22 | KR101619993B1 | 2016-05-11 | 크레이트마이어-스텍볼프강 |
| 본발명은추진로터어셈블리(B)에관한것이다.내부베슬배열체(5)는스테이터중공구조체(8)에고정되게확보되고적어도하나의확대된고정둘레하우징(20)을갖고, 공기역학적외부환상면스포일러(18)는상기고정둘레하우징(20)을보완하는외부외면(35)을갖는다. 상기공기역학적외부환상면스포일러(18)는피동로터시스템(7)의로터블레이드(10)의각 외부팁(23)에반경방향으로고정된다. 토러스형상의공기갭(G)이제공되어, 외부층류유동(56)이입구내부흐름(54)과동시에유입되며상기토러스형상의공기갭(G)을통해안내되고, 상기입구메인흐름과외부층류유동은단일의출구제어기류(C)에서함께합쳐지도록수렴된다.본발명은일반적으로, 예를들어회전익항공기와유사한항공기와같은운송수단(A)에적용된다. | ||||||
| 68 | 수상 이동장치용 중공관식 임펠러부재 | KR1020030033433 | 2003-05-26 | KR100484852B1 | 2005-04-22 | 황칠성 |
| 본 발명은 수상 이동장치의 엔진으로부터 전달받은 동력을 롤러치차를 통해 크라운스프라켓기어로 전달받아 일체인 중공관을 회전시켜주므로서 내부의 임펠러에 의해 고속으로 공기나 수량을 배출시 발생하는 에너지를 메인 추진력이나 보조추진력으로 이용하게 한 것으로; 선체나 비행체의 몸체에 탑재된 엔진의 동력에 의해 수면 위를 부양 상태로 거리를 이동하게 추진력을 발생하게 구비한 수상 이동장치에 있어서, 상기 선체나 비행체의 외부 후미 일측이나 좌,우 양측에 연결 배치되는 동력전달축을 통해 전달된 동력을 전달하게 롤러치차를 설치하며, 상기 롤러치차와 치합하는 크라운스프라켓 기어를 일정 길이의 중공관 외주면에 일체로 형성하고, 내주면에 회전시 공기나 수량을 고속으로 배출하게 임펠러를 형성한 중공관식 임펠러부와, 상기 중공관식 임펠러의 외주면에 롤러치차를 통해 전달된 동력에 의해 고속으로 정밀 회전하게 커버 조립하는 중공관식 임펠러 하우징으로 구성되어 이루어짐을 특징으로 하는 수상 이동장치용 중공관식 임펠러부재를 제공하는 뛰어난 효과가 있다. | ||||||
| 69 | 高性能螺旋桨 | CN00213631.7 | 2000-02-29 | CN2420228Y | 2001-02-21 | 韩玮; 李远灵; 孙连云; 辛崇华; 李向宇 |
| 一种高性能螺旋桨,有轮毂,桨叶,其特征是各桨叶叶端有弧形叶边或单边弧形叶边。在桨叶和轮毂之间,或桨叶之间有加强筋。本实用新型的螺旋桨具有小的诱导阻力损耗,能将离心力转换为有效推力,提高桨叶叶端附近的压力输出,增大桨叶的作用力,提高有效桨叶面积,螺旋桨的流体动力特性趋向展弦比为无穷大的桨叶特性,因此增加桨叶面积,降低排出流体速度和温度,以及应用其他节能原理,效果有较大幅度提高,相对目前技术,效率有大幅度的提高。 | ||||||
| 70 | AIRCRAFT | EP16166183.0 | 2016-04-20 | EP3093235B1 | 2018-11-21 | Moxon, Matthew |
| An aircraft (10) comprises trailing edge flaps (17), a wing mounted propulsor (26) positioned such that the flaps (17) are located in a slipstream of the first propulsor in use when deployed. The aircraft (10) further comprises a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor comprises a ducted fan (30) configurable between a first mode, in which the fan (30) provides net forward thrust to the aircraft (10), and a second mode in which the fan (30) provides net drag to the aircraft. (10). The fan (30) is positioned to ingest a boundary layer airflow in use when operating in the first mode. | ||||||
| 71 | ANTRIEBSVORRICHTUNG FÜR EIN FLUGZEUG SOWIE EIN FLUGZEUG MIT EINER SOLCHEN ANTRIEBSVORRICHTUNG | EP16751178.1 | 2016-07-18 | EP3325344A1 | 2018-05-30 | Schwöller, Johann |
| The invention relates to a drive device for an aircraft, comprising a shaft turbine coupled to an impeller by means of a shaft. The impeller comprises a suction side and a thrust side. The shaft turbine is arranged in the region of the suction side of the impeller. The drive device is additionally designed to be arranged on an aircraft fuselage and/or inside an aircraft fuselage and/or in a housing on a carrier surface. | ||||||
| 72 | A gas turbine engine | EP13171359.6 | 2013-06-11 | EP2685065A3 | 2018-03-07 | Stretton, Richard; Howarth, Nicholas |
A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (126) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (126) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).
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| 73 | EXTREMELY QUIET SHORT TAKE-OFF AND LANDING (STOL) AIRCRAFT | EP16781880.6 | 2016-04-08 | EP3283367A2 | 2018-02-21 | RAHRIG, Kyle; SOMMER, Geoffrey; WAINFAN, Barnaby, S. |
| An extremely quiet short take-off and landing (STOL) aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage in an orientation that is rotated relative to the typical orientation on a helicopter. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; channel shrouds surrounding at least one of the engine systems; and a ducted fan thruster positioned on the fuselage. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system, the engine system comprising two engine dual packs; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage. | ||||||
| 74 | ROTATIONAL DUCTED FAN (RDF) PROPULSION SYSTEM | EP15881340.2 | 2015-02-02 | EP3261928A1 | 2018-01-03 | Samuelson, Devin G. |
| In accordance with the present invention, an embodiment of a rotational ducted fan motor comprises a monolithic rotational ducted fan rotor, an electric propulsion system, a static aft-shroud comprising electrochemical-energy-storage, and an engagement system. The rotational ducted fan rotor is the portion of a ducted fan motor comprising a propeller, a duct, and a center hub, and having the effect of increasing the pressure difference from upstream to downstream of the propeller. The electric propulsion system comprises permanent magnets affixed to the rotational ducted fan rotor, repelling magnetic coils affixed to the static aft-shroud and electrical power provided by the electrochemical-energy-storage comprised within the aft-shroud. | ||||||
| 75 | REDUCED COMPLEXITY RING MOTOR DESIGN FOR PROPELLER DRIVEN VEHICLES | EP16192580.5 | 2016-10-06 | EP3162702A3 | 2017-07-12 | CHO, Jinsoo; SALAMON, Adam C.; ALLEN, Edward Henry |
A motor (200) includes a stator (210) and a rotor (250) coupled via the center hub (270) of the rotor. The stator includes a support ring, the support ring (220) comprising a plurality of windings (230) arranged circumferentially. The rotor is configured to operate as a rotating propeller and includes a center hub, a rotor support ring, and a plurality of blades (260). The rotor support ring comprises a plurality of magnetic poles arranged circumferentially. Each particular blade is individually coupled to the rotor support ring.
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| 76 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP14798021 | 2014-05-15 | EP2998221A4 | 2017-01-04 | TSUNEKAWA MASAYOSHI; TAMURA TETSUYA |
| A vertical take-off and landing aircraft includes a propulsion mechanism 2 that generates lift and thrust, a main frame 4 that supports seating 41 and a landing undercarriage 42, a sub-frame 5 which supports the propulsion mechanism 2 and is arranged so as to be swingable back and forth relative to the main frame 4, a motive power supply unit 3 supported by the main frame 4 and supplying motive power to the propulsion mechanism 2, a control stick 6 connected to the sub-frame 5, and a main wing 7 arranged on the propulsion mechanism 2, wherein the main wing 7 is formed to be retracted to a position not interfering with an air flow of the propulsion mechanism 2 in a normal time and to be movable to a position where lift is generated when thrust is lost. Gliding is made possible even if thrust is lost while increasing in size of a fuselage is avoided. | ||||||
| 77 | Convertible helicopter ring member | EP14183100.8 | 2014-09-01 | EP2957502B1 | 2016-11-09 | Hethcock, J. Donn; Dreier, Mark; Smith, Dudley E.; Robinson, Robert Lee |
| 78 | Autonomous propulsion apparatus and method | EP14192537.0 | 2014-11-10 | EP2871130B1 | 2016-07-20 | Newman, Daniel |
| 79 | OUTBOARD PROPULSION SYSTEM FOR VESSELS | EP14702953.2 | 2014-01-14 | EP2945857A1 | 2015-11-25 | PERLO, Pietro; GUERRIERI, Pietro |
| An outboard propulsion system for vessels includes a supporting structure (4) to be anchored to the transom wall (5) of the vessel and a plurality of propellers (3) carried by the supporting structure (4). Each propeller (3) is associated to an electric motor (6) with a toroid geometry, having an annular rotor (R) rotatable within an annular stator (S) and defining therewithin a central aperture (A), with the blades (3A) of the propeller (3) which are carried by the rotor (R) and extend to the central aperture (A). | ||||||
| 80 | UNDUCTED THRUST PRODUCING SYSTEM | EP13786120.9 | 2013-10-23 | EP2912270A1 | 2015-09-02 | BREEZE-STRINGFELLOW, Andrew; KHALID, Syed, Arif; SMITH, Leroy, Harrington, Jr. |
| An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream. | ||||||
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