| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | WIND TURBINE BLADE WITH LIFT-REGULATING MEANS IN FORM OF SLOTS OR HOLES | PCT/DK2008/000004 | 2008-01-04 | WO2008080407A1 | 2008-07-10 | BOVE, Stefano; GRABAU, Peter |
The blade (10) comprises adjustable lift-regulating means extending in the longitudinal direction of the blade (10), and activating means by means of which the lift-regulating means can be adjusted and thus alter the aerodynamic properties of the blade (10). The lift-regulating means are adapted and arranged so that by activation of the activating means, the lift can be reduced in a zone extending in the longitudinal direction of the blade (10) from a first position in proximity to the blade tip (14) to a second position between the first position and the root area (16) and this second position being variable in the longitudinal direction of the blade. The lift-regulating means are formed of at least one slot (12, 13, 15) or a number of holes (42, 43, 45, 52, 53, 55) arranged in at least one longitudinally extending zone, thereby allowing an interior cavity (22, 23, 25) of the blade (10) to communicate with the exterior. The lift-regulating means are adjustable by means of one or more activating means to regulate the amount of air emitted from the interior cavity (22, 23, 25) to the exterior to alter the aerodynamic properties of the blade (10). |
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| 182 | Wind-turbine blade, wind power generator equipped with the same, and design method for the same | JP2010238038 | 2010-10-22 | JP2012092657A | 2012-05-17 | FUKAMI KOJI |
| PROBLEM TO BE SOLVED: To provide a wind-turbine blade which achieves desired aerodynamic characteristics under condition that the upper-limit value of the chord length on the blade-root side is restricted.SOLUTION: The wind-turbine blade includes a blade body 3 in which the chord length is increased from the blade tip 1b side to the blade root 1a side. The blade body 3 has: a blade tip region 1c provided on the tip side of the blade body and in which the chord length is gradually increased toward the blade root 1a side while having a substantially constant first design lift coefficient; a maximum chord length position 1d located at a position that becomes the maximum chord length on the blade root 1a side and having a second design lift coefficient larger than the first design lift coefficient; and a transition region 1e located between the blade tip region 1c and the maximum chord length position 1d. The design lift coefficient of the transition region 1e is gradually increased from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip 1b side toward the blade root 1a side. | ||||||
| 183 | FUSELAGE AND METHOD FOR REDUCING DRAG | PCT/EA2012000008 | 2012-09-11 | WO2013037379A9 | 2013-05-16 | KRESHCHISHIN GENNADY TROFIMOVICH; KRESHCHISHINA LARISA TROFIMOVNA |
| The invention relates to aviation technology and can be used for improving the lift-drag ratio of helicopters and aeroplanes, including classically configured large airliners, and amphibious craft, aerodynamic ground-effect craft and hovercraft, possibly by modernization thereof. The technical problem addressed is that of reducing flight drag, possibly as a result of modernizing the helicopter, aeroplane, aerodynamic ground-effect craft or hovercraft. The technical result is achieved by reducing the contact area of the external surface of the tail part of the fuselage with a rapid air flow, for which the above-mentioned contact area is reduced by increasing the area of an opening in the tail part of the fuselage. In order to increase the lifting force without increasing the pressure resistance in an aerodynamic duct, the base is upwardly convex, for example is curved upwards following the shape of a convex side of an aerodynamic profile. The upper opening in the fuselage skin for the aerodynamic duct can be arranged in a space along the middle part of the rudder fin and is divided, for example in half, to the right and left along the rudder fin. The aerodynamic duct is continuous and can be open. An opening which is aligned with the leading upper edge of the aerodynamic duct has a larger area than a rear opening therein, which is aligned with the end of the fuselage, possibly in the form of and by means of a cut section in the end of the fuselage. | ||||||
| 184 | WIND TURBINE, WIND POWER GENERATION DEVICE PROVIDED THEREWITH, AND WIND TURBINE DESIGN METHOD | EP11834441 | 2011-10-20 | EP2631474A4 | 2015-05-06 | FUKAMI KOJI |
| Provided is a wind turbine blade that delivers the desired aerodynamic characteristics under conditions where the upper limit of the chord length near the blade root is limited. The wind turbine blade includes a blade body (3) whose chord length increases from a blade tip (1b) toward a blade root (1a). The blade body (3) includes a blade tip region (1c) located near the blade tip and whose chord length increases gradually toward the blade root (1a), the blade tip region (1c) having a substantially constant first design lift coefficient, a maximum-chord-length position (1d) located near the blade root (1a) and having a maximum chord length, the maximum-chord-length position (1d) having a second design lift coefficient higher than the first design lift coefficient, and a transition region (1e) located between the blade tip region (1c) and the maximum-chord-length position (1d). The transition region (1e) has a design lift coefficient increasing gradually from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip (1b) toward the blade root (1a). | ||||||
| 185 | Dispositif de simulation des efforts aérodynamiques appliqués sur deux gouvernes orientables d'un engin tel qu'un missile | EP97402291.5 | 1997-10-01 | EP0838673A1 | 1998-04-29 | Petit, Patrick; Mahoux, Alain |
Afin de simuler en laboratoire les efforts aérodynamiques dus à la portance et au braquage des deux gouvernes (12) orientables d'un engin (10), il est proposé un dispositif de simulation. Ce dispositif comprend notamment deux pièces d'ancrage (16), prévues pour être fixées sur les gouvernes (12), un système (26) de mise en tension, appliquant sur les gouvernes un effort de traction réglable simulant la portance, et deux systèmes (28) d'application de couples résistants, appliquant indépendamment sur chacune des gouvernes un couple résistant proportionnel à son braquage. |
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| 186 | TRANSFORMADOR DE ENERGÍA DE UN FLUIDO | PCT/MX2014/000132 | 2014-08-19 | WO2015026221A1 | 2015-02-26 | DE PAU MONTERO, Luis Arturo |
Convertidor de Energía de un Fluido, mismo que puede estar en reposo o en movimiento, comprende un eje con cuerpos aerodinámicos dispuestos de forma que al moverse la fuerza de sustentación que producen actúa a manera de torque aplicado al mismo eje. Dicho eje al girar transfiere su movimiento a los cuerpos aerodinámicos de forma que produzcan sustentación y torque y así se repite el ciclo. Por ejemplo el perfil Eppler 479 produce hasta 100 veces más Sustentación que Resistencia al avance al moverse. Este invento permite que la fuerza de sustentación de 100 se use para vencer 1 unidad de fuerza de resistencia del cuerpo y las restantes 99 unidades para mantener el movimiento y vencer las resistencias mecánicas (30% +-) y el remanente de fuerza para producir Electricidad o trabajo. |
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| 187 | METHOD AND APPARATUS OF FORMING THE TRIDIMENSIONAL VORTEX, AND THE TRIDIMENSIONAL VORTEX AIRCRAFT | PCT/CN2004/000451 | 2004-05-08 | WO2005108798A1 | 2005-11-17 | |
| The invention series belong to the field of aviation and electromagnetics. The invention is related to the creation and application of a novel vortex, which can be applied to the take-off and landing aircraft using the aerodynamic force as the lift within the atmosphere. Said vortex is formed by the fluid (air or plasma) passing through the specific adjusting passage with the assistance of a helical circular vortex accumulator. The air runs along the helix passage and accumulates at the ends to form an annulus vortex, which has the rotated vector on the horizontal plane and the vertical plane. The accumulator produces a novel vortex with high self-stability by forming a substantially circular (or conic) surface as the lift surface, or produces an annulus plasma flow as the Tokamak Device. It provides the main lift for the aircraft. It is a new type of aerodynamic force, and it makes all kinds of aircraft be helicopter. | ||||||
| 188 | AERODYNAMIC LIFT ENHANCING SYSTEM FOR A FLYING AUTOMOTIVE VEHICLE | US14744858 | 2015-06-19 | US20160368339A1 | 2016-12-22 | Taewoo Nam |
| An aerodynamic lift enhancing system for increasing aerodynamic lift generated by a body of an automotive flying vehicle is disclosed. The automotive flying vehicle includes a vehicle body enclosing a passenger compartment and having an upper surface at least partially defined by a hood, a roof extending over the passenger compartment, and a front windshield disposed between the hood and roof. The front windshield includes a leading edge positioned proximate a trailing edge of the hood and a trailing edge positioned adjacent the roof. The automotive flying vehicle includes wings extending laterally outward from the vehicle body. The aerodynamic lift enhancing system includes an air discharge nozzle located upstream from the leading edge of the front windshield, the air discharge nozzle operable to discharge a stream of air over the upper surface of the vehicle. | ||||||
| 189 | 二次元翼揚力タービンシステム | PCT/JP2001/006159 | 2001-07-17 | WO2003008801A1 | 2003-01-30 | 大田耕祐 |
| A two−dimensional blade lift turbine system utilizing a lift capable of generating an aerodynamic lift by using blades and converting a generated lift into a rotating force to rotate a generator for power generation, comprising a two−dimensional blade lift turbine having a plurality of two−dimensional blades annularly disposed therein, each formed by vertically placing a fixed blade of the size equal to that of an air plane wing and fixing the upper and lower sides of the blade to the ceiling and floor of an wind tunnel so as to utilize the ability of the air plane wing to produce a high lift, and an annular wind tunnel formed by annularly disposing a number of circulating Gettingen type wind tunnels combined with each other so as to simultaneously produce high lifts in order to produce a large amount of electric power, whereby a clean power can be generated anywhere, any time, and any amount without fuel, can be generated and directly supplied at the end consumer sites, and also can be supplied stably at a very low rate. | ||||||
| 190 | WIND TURBINE BLADE, WIND POWER GENERATION SYSTEM INCLUDING THE SAME, AND METHOD FOR DESIGNING WIND TURBINE BLADE | EP11834441.5 | 2011-10-20 | EP2631474B1 | 2016-12-21 | FUKAMI, Koji |
| Provided is a wind turbine blade that delivers the desired aerodynamic characteristics under conditions where the upper limit of the chord length near the blade root is limited. The wind turbine blade includes a blade body (3) whose chord length increases from a blade tip (1b) toward a blade root (1a). The blade body (3) includes a blade tip region (1c) located near the blade tip and whose chord length increases gradually toward the blade root (1a), the blade tip region (1c) having a substantially constant first design lift coefficient, a maximum-chord-length position (1d) located near the blade root (1a) and having a maximum chord length, the maximum-chord-length position (1d) having a second design lift coefficient higher than the first design lift coefficient, and a transition region (1e) located between the blade tip region (1c) and the maximum-chord-length position (1d). The transition region (1e) has a design lift coefficient increasing gradually from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip (1b) toward the blade root (1a). | ||||||
| 191 | FUSELAGE AND METHOD FOR REDUCING DRAG | EP12831379.8 | 2012-09-11 | EP2757039B1 | 2017-06-28 | Kreshchishin, Gennady Trofimovich; Kreshchishina, Larisa Trofimovna |
| 192 | FLYING APPARATUS | PCT/EP2015/073656 | 2015-10-13 | WO2016059040A1 | 2016-04-21 | LUCHSINGER, Rolf; GOHL, Flavio |
A flying apparatus is provided that comprises a airfoil (1) with a streamlined profile for generating an aerodynamic lift force vector (L) acting on the flying apparatus when being exposed to an apparent air flow. The flying apparatus also comprises at least three drive units (4, 42; 5, 51; 6, 61) being adapted to generate a resulting thrust force vector acting on the flying apparatus, the thrust force vector being alignable essentially in parallel with the aerodynamic lift force vector (L). For controlling the aerodynamic pitch of the flying apparatus, the flying apparatus comprises at least one control surface (31, 11). Furthermore, the flying apparatus has an aerodynamic neutral point (NP) that lies, along the longitudinal centre axis (10) and in the direction from the leading edge (17) to the trailing edge (18) of the airfoil (1), behind the centre of gravity (CG) of the flying apparatus. |
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| 193 | A CONSTANT CROSS - SECTION PROFILE FLYING PLATFORM WITH INCREASED LIFT FORCE | PCT/PL2013/000057 | 2013-04-23 | WO2013162389A1 | 2013-10-31 | DOBROCIŃSKI, Tadeusz |
The construction of a flying platform in the shape of a square, diamond or another geometry figure with a hole in it is described. It has a unique constant cross-section profile providing aerodynamic lift. This structural solution offers the possibility of flight in any of four directions: each corner could be the front corner of the flying platform. The aerodynamic lift is generated by air turbulences formed on the leading edges and resulting from the air flow disturbances. The design combines two features: the wing/fuselage profile and the shapes of square or diamond, distinguished by excellent flight. It has improved longitudinal and transverse flight stability. |
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| 194 | Method for easily evaluating drag of model receiving aerodynamic lift in magnetic suspension and balance system | JP2007092049 | 2007-03-30 | JP2008249527A | 2008-10-16 | SAWADA HIDEO |
| PROBLEM TO BE SOLVED: To provide a technique capable of rationally evaluating aerodynamic forces by substantially improving the efficiency of wind tunnel test and simultaneously eliminating such waste that both a model suspension device and a mechanical balance device, which should not have been required for a wind tunnel provided with a magnetic suspension and balance system, should be separately provided. SOLUTION: In a method for easily evaluating drag of a model receiving aerodynamic lift in a magnetic suspension and balance system, a known external force in a horizontal direction is provided for the model in a state on which lift is not acting to determine the relation of a drag coil current balancing the horizontal external force. A rate of change (B) of the drag coil current to changes in the horizontal external force is quantitatively evaluated on the basis of the relation. The relation between the drag coil current (I drag) and attitude angles (θ) when the attitude angle of the model is changed without providing any external force except gravity is determined. Drag (D) when lift (L) is acting is evaluated on the basis of gravity (mg) acting on the model on the basis of a proposed equation. COPYRIGHT: (C)2009,JPO&INPIT | ||||||
| 195 | SISTEMA Y PROCEDIMIENTO SUSTENTADOR, PROPULSOR Y ESTABILIZADOR PARA AERONAVES DE DESPEGUE Y ATERRIZAJE VERTICAL | PCT/ES2011/000147 | 2011-04-12 | WO2012035178A1 | 2012-03-22 | MUÑOZ SAIZ, Manuel |
Sistema y procedimiento sustentador, propulsor y estabilizador para aeronaves de despegue y aterrizaje vertical que consiste en aplicar simultáneamente y combinados como sustentadores durante el tramo inicial del ascenso y al final del descenso: a) unos fanes o turbinas eléctricas, EDF y b) al menos un rotor de palas externas y/o de alas giratorias, y/o c) el flujo de los motores dirigido hacia abajo y/o d) chorros de aire a presión inyectado sobre bordes de ataque de las aletas de control, y/o e) chorros de agua, y/o í) complementados con la sustentación aerodinámica producida durante el avance frontal de la aeronave, la estabilización se consigue con la rigidez giroscópica de los rotores y dos o más fanes sustentadores, aletas oscilantes y/o chorros de aire estabilizadores situados en dos o mas puntos periféricos en un plano normal al eje vertical de la aeronave. |
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| 196 | Aero-carrier | JP5565898 | 1998-01-30 | JPH11217099A | 1999-08-10 | SHIMONO HEIHACHI |
| PROBLEM TO BE SOLVED: To enable the rapid rotational motion in the advancing direction, in the right-to-left direction and in the horizontal plane even in a stopped condition in the air by generating the aerodynamic force of a propulsion blade by the rapid air flow generated by a multiple-blade fan of an air frame. SOLUTION: A propulsion blade affects no force to an air frame if the parallel and angle of attack is at the zero position to an air frame. Thus, the air frame is in a stopped condition in the air if the output of a drive engine 5 is regulated so that the lift generated by multiple-blade fans 4a, 4b is balanced with the total weight of the air frame and the drag generated by the air frame due to the air flow. The air frame is designed so that the center of gravity of the whole air frame is below the center of the aerodynamic force generated by the propulsion blade. If the air frame is inclined by the aerodynamic force, the resisting rotational moment is exerted, and thus, the air frame is constantly stable. When the angle of attack is changed forward, the generated aerodynamic force is directed forward of Y-axis to form the force to advance the air frame. If the angle of attack is changed to the opposite direction, the generated aerodynamic force is naturally directed backward. COPYRIGHT: (C)1999,JPO | ||||||
| 197 | 以高速在洶濤水中或水面上操動之進步型海上交通工具 | TW081110256 | 1992-12-18 | TW256811B | 1995-09-11 | 彼得R.派恩 |
| 一種水翼船，具有至少一船身，至少一從前述船身伸入水中而與船身相連之支臂，至少有一裝於每一支臂之翼，以及最好至少每一支臂有一減震支柱以樞軸將前述船身接至該支臂，以使前述減震支柱及該翼與靠近之波動水速相配合而移動，以便使前述水翼船能保持近乎不變的升力。此涉及之原理亦適用於水翼陸效型 (以下簡稱WIG型) 飛機，此種飛機係設計來靠近水面飛行，以利用靠近水面之良好空氣動力效果。 | ||||||
| 198 | 弱地效飛行器 | TW082101049 | 1993-02-15 | TW239108B | 1995-01-21 | 李群 |
| 一種弱地效飛行器，利用設置於飛行器機翼翼面的壓力傳感器（或壓差傳感器）感受機翼表面因地面效應而產生的空氣動力靜壓變化，傳感器輸出的電信號幅度與地效飛行高度成比例關係，經過處理放大，去控制飛行器的升力控制系統，調整飛行器的飛行高度，由於壓力傳感器可以檢測到相對微弱的靜壓變化，其輸出電信號又很容易做相關處理並放大很高的倍數，因而可以實現利用微弱的地表效應去控制地效飛行高度，即可以大大提高地效飛行高度。 | ||||||
| 199 | HIGH SPEED TRIANGULAR SHAPED HYDROPLANING MONOHULL CRAFT WITH AIRCRAFT-LIKE CONTROL SURFACES HAVING SURFACE ADHESION HULL CHARACTERISTICS | PCT/MY2015/050063 | 2015-06-25 | WO2016013923A1 | 2016-01-28 | TAN, Yu Lee |
The invention is an air propelled boat that has a triangular shaped hydroplaning monohull which has surface adhesion characteristics by means of a concave bottom hull. The invention also has aircraft-like control surfaces (5,6) for safety and control at high speeds. The invention is the only monohull marine craft which produces aerodynamic lift without wings and has air based propulsion (4), air based control surfaces and a unique concave planing hull. |
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| 200 | LAUNCHABLE DOLL | PCT/GB2006002712 | 2006-07-20 | WO2007010264A2 | 2007-01-25 | NORMAN CASEY WILLIAM; GAMLIN DAVID; THATCHER TONY |
| A launchable doll has wings (1) which impart aerodynamic lift to the doll when it is rotated, said wings being fixed to the doll at a waist level thereof. The wings (1) may be pivotable with respect to the body of the doll so that when not rotating the wings fall to a substantially vertical position and provide a skirt for the doll. A launcher (5) for the doll comprises a base (6), a tube (4) for containing legs of the doll and a mechanism for rotating the tube and the doll with respect to the base (6). | ||||||
