| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 221 | Marine Propulsion Multihull Ship | US15111896 | 2015-01-15 | US20160332700A1 | 2016-11-17 | Lionel Huetz; Gianluca Guelfi; Matthieu Kerhuel; Hubert Thomas |
| A ship having a length to width ratio smaller than two and including a superstructure and at least two hulls, the superstructure forming a wing able to generate an aerodynamic lift comprised between 20 and 90% of the weight of the ship at a cruising speed thereof, the wing including curved ends connected to each of the hulls and having a developed surface of an extrados of the wing substantially equal to the product of the length by the width of the ship, wherein a point for application of the aerodynamic lift generated by the superstructure is situated behind the center of gravity for application of the gravitational forces on the ship, and a point for application of the resultant of the hydrodynamic forces generated by the hulls is situated in front of the center of gravity. | ||||||
| 222 | LIFTING ENTRY/ATMOSPHERIC FLIGHT (LEAF) UNIFIED PLATFORM FOR ULTRA-LOW BALLISTIC COEFFICIENT ATMOSPHERIC ENTRY AND MANEUVERABLE ATMOSPHERIC FLIGHT AT SOLAR SYSTEM BODIES | US14297370 | 2014-06-05 | US20150210407A1 | 2015-07-30 | KRISTEN S. GRIFFIN; JON CARPENTER; GREGORY J. LEE; AMY LO; RONALD POLIDAN; DANIEL SOKOL; BARNABY WAINFAN; WARREN JAMES; DENNIS POULOS |
| An aerial vehicle including a collapsible and inflatable vehicle body capable of being filled with a lighter than air gas so as to make the vehicle semi-buoyant or 100% buoyant at a predetermined altitude in an atmosphere above a solar system body. The vehicle body has a shape suitable to provide aerodynamic lift. The vehicle may include a propulsion device coupled to and extending from the vehicle body, where the device provides power to aerodynamically lift the vehicle above the 100% buoyant altitude to a higher altitude where the vehicle can maintain that altitude through the aerodynamic lift and vehicle buoyancy. The vehicle is configured to be deployed/inflated from a collapsed and stowed configuration to a deployed/inflated configuration in an orbit above the atmosphere of the solar system body, and is configured to enter the atmosphere in the inflated configuration and descend without propulsion. | ||||||
| 223 | フライングディスク | JP2015122410 | 2015-06-02 | JP2016221202A | 2016-12-28 | 柴崎 威暢 |
| 【課題】飛行中に係る空力的不安定性を相対風の誘導により解消し、水平位に安定した長距離飛行を可能とするフライングディスクの形状を得る。 【解決手段】揚力の不足する後翼においては後翼下方に相対風を誘導し、回転で生じる片翼の揚力の不足においては回転に沿う流れで不足する片翼下方へ相対風を誘導し、前後左右の揚力差を同時解消する形状を得る。 【選択図】図2 |
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| 224 | Low aerodynamic noise type current collection equipment | US375830 | 1995-01-20 | US5566799A | 1996-10-22 | Hideto Hidaka; Kengo Iwamoyto; Yasuhiro Noguchi; Motohiro Miyamura; Seiichi Yazima; Inao Sakai |
| Low aerodynamic noise type current collection equipment is provided for reducing variations in aerodynamic force applied to a current collector during train operation. A central region (2a) of a current collector (1) having a collector head (2) with a top surface in which a contact strip (3) is embedded is rectangular in cross-section, and each side region is shaped convex in cross-section in the front and rear directions, with e.g. an elliptical shape. The rectangular shape has characteristics such that the magnitude of the aerodynamic lift force would be kept substantially constant even if the inclination angle against the aerial flow would be changed. Accordingly, the cross-sectional shape of the central region (2a) of the current collector (1), which is liable to receive the turbulent aerial flow from the support portion (4) in the current collector (1), makes it possible to suppress the variation in aerodynamic lift force generated in the current collector even if the angle of the aerial flow that would collide against the current collector (1) would be unstable. The cross-sectional shape of each side region (2b) being made convex in the front and rear directions reduces the aerodynamic noise. | ||||||
| 225 | FLYING VEHICLE WITH LIFT GENERATORS | PCT/BA1998/000001 | 1998-04-16 | WO99007601A1 | 1999-02-18 | |
| Aeromobil is a dynamic flying machine heavier than air which produces necessary aerodynamic force for lift, thrust and control moments in aerodynamic generators. Flying characteristics of Aeromobil are those which make it possible for it to lift and land vertically in its own characteristic way, to soar in big altitude range, to take any direction in space by its vertical axle while soaring, to get to translational motion in any direction from every soaring position, to get into soaring position from every direction of translational motion, to turn around all three space axles simultaneously while soaring (it can be turned around side axle x for 360 degree, around vertical axle z for 360 degrees), and the aircraft can be turned around vertical axle y for 360 degrees in order of horizontal progressive motion whether in motion ahead or back. All flying characteristics are controlled by hydraulic system over Distributor of group change of angle of attack, Distributor of control by direction, altitude and laterally, Distributor of thrust vector, and Distributor of brake vector. | ||||||
| 226 | Rear wheel steering angle control device | JP23817191 | 1991-09-18 | JPH0577754A | 1993-03-30 | SATO MANABU; NAKADA MORITSUNE |
| PURPOSE:To increase steering stability by changing control method into control of rear steering angle when a vehicle speed is over a specified limit to control the aerodynamic characteristics of the vehicle in a device in which a steering angle relative to a front wheel steering angle is controlled based on a specified control raw to control the plane movement of the vehicle. CONSTITUTION:A rear wheel steering angle control system including an actuator for rear wheel steering 9 and an aerodynamic characteristic control system including front and rear movable blades 40 and 50 are provided to control the plane movement of a vehicle, and they are controlled by a controller 17 based on outputs from various sensors. Namely, in rear wheel steering angle control, a rear wheel steering angle relative to a front wheel steering angle is controlled based on a specified control law by outputs from a steering angle sensor 18 and a vehicle speed sensor 19 to control the plane movement of the vehicle. If the speed is over a specified limit, the aerodynamic characteristics of the vehicle are controlled instead of control of the rear wheel steering angle. In this control law of aerodynamic characteristics, an aerodynamic device is controlled so that any lift due to aerodynamic force may not be applied to the front wheel part of the vehicle and a downward force may be applied to the rear wheel part of it. | ||||||
| 227 | High lift force-generating device, wing and slat | JP2010030075 | 2010-02-15 | JP2011162154A | 2011-08-25 | HAYASHI KENSUKE; ISHIHARA KENYA; YAHATA YUSAKU; HIRAI MAKOTO |
| PROBLEM TO BE SOLVED: To provide a high lift force-generating device and a wing, which can suppress generation of aerodynamic noise while suppressing increase in body weight. SOLUTION: A recess and projection part 20 is formed in a bottom plate 7 extending rearward in a lower surface of a slat 3, so that a position in which air flow flowing along the surface of the slat 3 is exfoliated from the bottom plate 7 to generate a vortex is made uneven in the air flow direction. Thereby, the vortex generated in a recess 20A and the vortex generated in a projection 20B are short in correlation with each other, and the vortices are hardly connected to each other, and becomes the independent vortexes, so that the generated vortex is weak in strength, which can reduce the pressure fluctuation on a body surface, and suppress generation of the aerodynamic sound. COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 228 | AIRBORNE PLATFORM | PCT/PT2012000007 | 2012-03-15 | WO2012125052A3 | 2012-12-27 | 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. | ||||||
| 229 | Dynamic lift adjustment structure of current collector | JP2012138787 | 2012-06-20 | JP2014003847A | 2014-01-09 | MITSUMOJI TAKESHI; SATO YUICHI; IKEDA MITSURU |
| PROBLEM TO BE SOLVED: To provide a dynamic lift adjustment structure of a current collector, which can easily adjust dynamic lift acting on the current collector by reducing aerodynamic force acting on the frame of the current collector with a simple structure.SOLUTION: A turbulent flow transition part 10 allows a laminar flow boundary layer formed on a frame surface 6e by a flow F on the frame surface 6e of a current collector 3 to make a transition to a turbulent flow boundary layer. When there is the turbulent flow transition part 10 on the frame surface 6e, the laminar flow boundary layer on the frame surface 6e makes a transition to the turbulent flow boundary layer, and the flow F is disturbed by the turbulent flow transition part 10, causing active momentum exchange. Thus, the flow F is hardly separated from the frame surface 6e, and the separation of the flow F from the frame surface 6e is retarded. As a result, a separation point of the flow F is moved backward to the downstream side so that Karman vortices generated behind a frame 6 are weakened, and aerodynamic force Lacting on the frame 6 is reduced. Thereby, dynamic lift Lacting on the current collector 3 is adjusted. | ||||||
| 230 | AIRBORNE PLATFORM | PCT/PT2012000007 | 2012-03-15 | WO2012125052A4 | 2013-02-21 | 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. | ||||||
| 231 | ФЮЗЕЛЯЖ И СПОСОБ УМЕНЬШЕНИЯ СОПРОТИВЛЕНИЯ | PCT/RU2011/000227 | 2011-04-06 | WO2011129721A1 | 2011-10-20 | КРЕЩИШИН, Геннадий Трофимович; КРЕЩИШИНА, Лариса Трофимовна |
Изобретение относится к авиационной технике и применимо для улучшения аеродинамического качества вертолётов, самолетов в том числе, крупных аэробусов классической схемы и амфибий, экранолётов и судов на воздушной подушке, возможно, путём проведения их модернизации. Технической задачей является уменьшения сопротивления по- лёту, возможно, в результате модернизации вертолёта, самолёта, экраволета, судна на воздушной подушке. Технический результат достигается уменьшением площади кон- такта внешней поверхности хвостовой части фюзеляжа со скороот- ным воздуштым потоком, для чего упомянутую площадь контакта уменьшают путём увеличения площади отверстий в хвостовой части фюзеляжа. Для увеличения подъемной силы без увеличения сопро- тивления давления у аэродинамического канала дно выполняют вы- пукым в верх, например, выгнутым в верх по форме выпуклой стороны аэродинамического профиля. Верхнее отверстие в обшивке фвэеяяжа для аэродинамического канала монет быть размещено в пространстве вдоль средней части киля и выполненным раеделённм вдоль килем, направо и налево, например, поводам, Аэродинами- ческий канал виполнен сквозным и может быть открытым. Отверс- тие, совмещённое о передней верхней кромкой аэродинамического канала, выполнено большей площади, чем заднее отверстие, чем его заднее отверстие, оовмещенное с концом фюзеляжа, возможно в виде и путём среза конца фюзеляжа. |
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| 232 | HIGH-LIFT DEVICE | EP16173405.8 | 2016-06-07 | EP3231702A1 | 2017-10-18 | Everaert, Bob Armand Henri; Verhuizen, Alexander Jean M.; Thys, Raf; De Baere, Tom Robert Adelin; Raets, Michaël |
A high-lift device (1) comprising an airfoil shaped body (2) having a leading edge and a trailing edge and extending in a spanwise direction configured mainly to generate aerodynamic force; a profile structure (9) arranged to be mounted inside of the airfoil shaped body and extending in spanwise direction of the airfoil shaped body that is configured to provide most of the mechanical strength and stiffness; wherein the airfoil shaped body (2) is provided with an opening (7) extending in spanwise direction at one side through which the profile structure (9) can be fastened and remains accessible inside of the airfoil shaped body.
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| 233 | AERONEF COMBINE MUNI D'UN DISPOSITIF ANTICOUPLE COMPLEMENTAIRE | EP16177015.1 | 2016-06-29 | EP3118112A1 | 2017-01-18 | TOULMAY, François |
La présente invention concerne un aéronef combiné (1) comportant un fuselage (2), un rotor principal (3), un dispositif anticouple principal (4) et deux ailes (11,11') positionnées de part et d'autre dudit fuselage (2). Chaque aile (11,11') comporte au moins un volet (12,12') mobile situé au niveau de son bord de fuite. Lesdits volets (12,12') peuvent être orientés de façon dissymétrique vis à vis d'un flux d'air généré en réaction à la portance dudit rotor principal (3) de part et d'autre dudit fuselage (2) afin de créer des efforts aérodynamiques longitudinaux de sens opposés de part et d'autre dudit fuselage (2) et, par suite, un couple complémentaire s'ajoutant au couple principal dudit dispositif anticouple principal (4).
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| 234 | Tragflügel für ein Luftfahrzeug mit einer vom Staudruck verstellbaren Klappe | EP02011007.8 | 2002-05-17 | EP1262404A1 | 2002-12-04 | Müller, Günther; Schneider, Horst, Dr. |
Es wird ein auftriebskrafterzeugendes Profil (1) für ein Luftfahrzeug mit verstellbaren Mitteln zur Profilanpassung (2) und einer eine Stellkraft auf diese ausübenden Stelleinrichtung (3, 4, 5, 6) beschrieben. Erfindungsgemäß ist die Stelleinrichtung (3, 4, 5, 6) vom Staudruck beaufschlagt und erzeugt die besagte Stellkraft abhängig von der Größe des Staudrucks. |
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| 235 | Wind turbine blade of variable geometry with passive control | EP13167746.0 | 2013-05-14 | EP2664791A2 | 2013-11-20 | Torres Martinez, Manuel |
The present invention relates to a wind turbine blade of variable geometry with passive control, incorporating lift-regulating means formed by elastic membranes (4, 4a), arranged on the surface of the extrados face of the aerodynamic profile, which membranes (4, 4a) have an inner chamber which is arranged connected to a pneumatic circuit (8) through which a reference negative pressure generated by means of vacuum pumps (9) is applied, such that said membranes (4, 4a) can be deformed as a function of the air striking the blade (1) of application in order to modify the aerodynamic characteristics thereof.
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| 236 | 自律的ピッチ・コントロール型風車ブレード形状 | JP2014109524 | 2014-05-12 | JP2015214962A | 2015-12-03 | 天野 完一; 那須野 友規子 |
| 【課題】風力発電装置において、風車コスト低減を実現する自律的ピッチ・コントロール型風車を提供する。 【解決手段】従来型に見られる可変ピッチ制御機構装置を排除するために、風車ブレード形状に、自然風速変動に呼応して、可変ピッチ機能を維持し、風車ブレードに自律的にピッチ角を調整することが可能な形状を付与する。新しい風車ブレード形状は、反りを持つ翼型の空力特性を利用して、風車ブレード翼の翼幅に沿って途中の反転位置で翼型を反転させることによって、自然風速変動に呼応して風車ブレード翼内で自律的に捩りモーメントの釣り合いを実現する。このとき、反転した翼型に発生する揚力は、反転しない翼型と同様に、風車ブレード翼のハブ周りの回転方向に揚力の成分を有している点を特徴とする。 【選択図】図1 |
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| 237 | WIND TURBINE BLADE WITH BASE PART HAVING INHERENT NON-IDEAL TWIST | PCT/EP2010/056793 | 2010-05-18 | WO2010145902A1 | 2010-12-23 | FUGLSANG, Peter; BOVE, Stefano; FUGLSANG, Lars |
A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft is described. The rotor comprises a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow, the profiled contour in the radial direction being divided into a root region with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and preferably a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, wherein the airfoil region comprises at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region, the first longitudinal segment comprising a first base part having a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The first base part has an inherent non-ideal twist, such as no twist, or a reduced twist compared to a target blade twist, so that an axial induction factor of the first base part without flow altering devices at a design point deviates from a target axial induction factor. The first longitudinal segment is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target axial induction factor at the design point. |
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| 238 | WIND TURBINE BLADE PROVIDED WITH FLOW ALTERING DEVICES | PCT/EP2010/056817 | 2010-05-18 | WO2010133594A1 | 2010-11-25 | FUGLSANG, Peter; BOVE, Stefano; FUGLSANG, Lars |
A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft is described. The rotor comprises a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow, the profiled contour in the radial direction being divided into a root region with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and preferably a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, wherein the airfoil region comprises at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region, the first longitudinal segment comprising a first base part having a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The first base part has an axial induction factor, which without flow altering device deviates at least 5% from a target axial induction factor at a design point. The first longitudinal segment is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target axial induction factor at the design point. |
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| 239 | WIND TURBINE BLADE | PCT/EP2010/056804 | 2010-05-18 | WO2010133585A1 | 2010-11-25 | FUGLSANG, Peter; BOVE, Stefano; FUGLSANG, Lars |
A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft is described. The rotor comprises a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow, the profiled contour in the radial direction being divided into a root region with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and preferably a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, wherein the airfoil region comprises at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region, the first longitudinal segment comprising a first base part having a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The first base part has an inner dimension that varies linearly in the radial direction of the blade in such a way that an induction factor of the first base part without flow altering devices at a rotor design point deviates from a target induction factor. The first longitudinal segment is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment to substantially meet the target induction factor at the design point. |
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| 240 | BI-DIRECTIONAL WING UNFOLDING MECHANISM | PCT/IB2017/054165 | 2017-07-11 | WO2018015838A1 | 2018-01-25 | BAVANARI, Venkata Lakshmi Chennakeseva Rao; SHAIK, Ismail; JAIN, Prakash Chand; PAMARTHI, Seeta Rama Anjaneyulu; ALI, Naveed; DAS, Ranajit; KAPADIA, Kaikobad Erachshaw |
The present disclosure relates to a bi-directional wing unfolding mechanism for unfolding and locking wings of air vehicle during deployment. The mechanism comprises one or more flexible member to enable lift and rotational movements of the wings of air vehicle about one or more axis. The mechanism also comprises one or more pairs of lock pins to lock undesired lift and rotational movement of the wings after the desired movements, thereby enabling minimum roll disturbance and near synchronous locking of all wings. Further, the mechanism also enables folding and unfolding of the wings having higher aspect ratio by folding and unfolding at mutually perpendicular axes. The mechanism also enables lower drag and results in high aerodynamic performance, low roll rate and better flight trajectory. |
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