| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 一种超高速飞行器的热防护与减阻系统 | CN201510079182.0 | 2015-02-13 | CN104608942B | 2017-05-17 | 张文武; 向树红; 郭春海; 童靖宇; 张天润; 杨旸; 宋涛 |
| 本发明提供了一种超高速飞行器的热防护与减阻方法和系统。该方法在超高速飞行器的腔体内部设置冷源，腔体壁面设置若干微孔，在驱动力作用下冷源呈高压气体状自微孔射出，在腔体外表面形成气膜。该气膜不仅能够对超高速飞行器进行热防护，而且能够有效减少飞行器与外界气体的粘阻，有助于减缓或消除热障现象，从而提高超高速飞行器的安全性，延长使用寿命，具有良好的应用前景。该系统采用冷源驱动装置，包括空气泵、冷源储存器与缓冲器；工作状态时，空气泵向冷源储存器提供压缩空气，在空气压力作用下冷源进入缓冲器并气化，气体在压力作用下自微孔喷出形成气膜。 | ||||||
| 2 | 在物体上产生势能的方法和装置 | CN02823844.3 | 2002-11-29 | CN1596208A | 2005-03-16 | 阿恩·克里斯蒂安森 |
| 本申请涉及一种用流体动力效果在一个物体上产生势能的方法和装置，由该方式获得的力对于船、潜艇、飞机和飞船的推进和操纵是有用的。被静止地浸入流体中的物体到处受到相等的压力，一个靠近物体一侧的流体流将减小局部压力并在物体上产生一个势能，当前这是通过在流体中移动物体来进行的，参考飞机机翼。可以通过在物体一侧上建立一个流体流或多个流体流来产生势能，被铰接到飞机的物体对于飞机的升起、推进和操纵是有用的，并可以使它们独立于用于升起和操纵的速度，对于潜水艇的情况是相同的。飞船和远洋船可以被如此设计，就是使它们的推进物体被结合到它们的形状中。从被放在每个物体的滞止线附近的管子中的喷嘴、孔或缝隙，流体流被产生，从而确定了其前缘。在一个船上使用该技术，该技术减弱了其船首波并消除了与螺旋桨推进相关联的动力学损失，增强了操纵力和操纵精确度。 | ||||||
| 3 | 薄片组件 | CN201480070864.9 | 2014-12-22 | CN105899429A | 2016-08-24 | C·瓦尔索普; N·A·米尔扎 |
| 本发明提供一种薄片组件(22)，其在使用中被安装于基座结构以形成流体流经表面的至少一部分。该薄片组件包括：壳体(42)，其具有至少一个增压室(45)，所述增压室(45)设置在壳体(42)内。壳体(42)的壁(44)设有多个流路(46)，该流路(46)从所述壁(44)的增压室一侧延伸到壁的外表面(48)。设置有流路封闭器(50)，其可操作以打开和关闭至少一些流路(46)。 | ||||||
| 4 | 一种超高速飞行器的热防护与减阻方法和系统 | CN201510079182.0 | 2015-02-13 | CN104608942A | 2015-05-13 | 张文武; 向树红; 郭春海; 童靖宇; 张天润; 杨旸; 宋涛 |
| 本发明提供了一种超高速飞行器的热防护与减阻方法和系统。该方法在超高速飞行器的腔体内部设置冷源，腔体壁面设置若干微孔，在驱动力作用下冷源呈高压气体状自微孔射出，在腔体外表面形成气膜。该气膜不仅能够对超高速飞行器进行热防护，而且能够有效减少飞行器与外界气体的粘阻，有助于减缓或消除热障现象，从而提高超高速飞行器的安全性，延长使用寿命，具有良好的应用前景。该系统采用冷源驱动装置，包括空气泵、冷源储存器与缓冲器；工作状态时，空气泵向冷源储存器提供压缩空气，在空气压力作用下冷源进入缓冲器并气化，气体在压力作用下自微孔喷出形成气膜。 | ||||||
| 5 | 在物体上产生势能的方法和系统 | CN02823844.3 | 2002-11-29 | CN1329244C | 2007-08-01 | 阿恩·克里斯蒂安森 |
| 本申请涉及一种用流体动力效果在一个物体上产生势能的方法和装置，由该方式获得的力对于船、潜艇、飞机和飞船的推进和操纵是有用的。被静止地浸入流体中的物体到处受到相等的压力，一个靠近物体一侧的流体流将减小局部压力并在物体上产生一个势能，当前这是通过在流体中移动物体来进行的，参考飞机机翼。可以通过在物体一侧上建立一个流体流或多个流体流来产生势能，被铰接到飞机的物体对于飞机的升起、推进和操纵是有用的，并可以使它们独立于用于升起和操纵的速度，对于潜水艇的情况是相同的。飞船和远洋船可以被如此设计，就是使它们的推进物体被结合到它们的形状中。从被放在每个物体的滞止线附近的管子中的喷嘴、孔或缝隙，流体流被产生，从而确定了其前缘。在一个船上使用该技术，该技术减弱了其船首波并消除了与螺旋桨推进相关联的动力学损失，增强了操纵力和操纵精确度。 | ||||||
| 6 | 超高速航空機の熱防護と抵抗軽減方法及びシステム | JP2017560861 | 2016-02-06 | JP2018505099A | 2018-02-22 | 張文武; 向▲樹▼紅; 郭春海; 童靖宇; 張天潤; ▲楊やん▼; 宋涛 |
| 【課題】超高速航空機の熱防護と抵抗軽減システム及び方法に関する。【解決手段】超高速航空機の機体の内部には冷却源(200)と、冷却源駆動装置(100)とが設けられ、機体壁面(310)には複数の微細孔(300)が設けられ、冷却源駆動装置(100)は空気ポンプ(110)と冷却源格納器(210)と緩衝器(150)とを含み、動作時において、空気ポンプ(110)が冷却源格納器(210)に圧縮空気を供給し、冷却源(200)が空気圧力により緩衝器(150)に入り気化され、高圧の気体が微細孔(300)から噴射されて機体外面にガス膜を形成する。当該ガス膜は超高速航空機に対して熱防護を行うことができるとともに、航空機と外気との粘性抵抗を効果的に低減させることができ、熱の壁といった現象の軽減又は解消に寄与することができ、超高速航空機の安全性を向上し、耐用年数を延長することができる。【選択図】図1 | ||||||
| 7 | Method and system for generating a potential on the object | JP2003547247 | 2002-11-29 | JP2005510667A | 2005-04-21 | クリスティアンセン，アーネ |
| This application concerns a method and system using a hydrodynamical effect for producing a potential over a body. The force obtained this way is useful for the propulsion and maneuvering of ships, submarines, aeroplanes, and airships. A body immersed in a fluid at rest is subject to equal pressures on all sides. A stream close to one side of the body will reduce the local pressure and produce a potential over the body. This is currently done by moving the body in the fluid, cf. aeroplane wings. The potential may be produced by setting up a stream or streams over one side of the body. Bodies attached to aeroplanes by hinges are useful for their lift, propulsion and maneuvering, and will make them independent of velocity for lift and maneuvering. The same will be the case for submarines. Airships and seagoing vessels may be designed so as to have their propulsive bodies integrated in their form. The streams are produced from nozzles, holes, or slits in tubes placed near the stagnation line of each body, thus defining its leading edge. Used on a ship, this technique lowers its bow wave and removes the dynamical losses connected with screw propulsion. The maneuvering force and precision are enhanced. | ||||||
| 8 | Tangential acoustic injection system for the boundary layer control | JP2000605480 | 2000-02-25 | JP2002539035A | 2002-11-19 | エル． ギスリン，ダニエル; シー． マコーミック，デュアン |
| The nozzle of an acoustic jet directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, an engine air inlet, a jet engine gas flow path or on the suction surface of an airfoil, the gas particles in the chamber of the tangential acoustic jet being replenished with approaching low momentum flux particles drawn from the gas flow in a direction normal to the surface, thereby to provide a net time-averaged flow of increased momentum flux particles to defer the onset of boundary layer separation and/or reduce the thickness of the boundary layer. The acoustic jet is driven by a gas pressure oscillation generator which may be a loudspeaker, a resonant solenoid piston, a cranked piston, or the like. | ||||||
| 9 | JPH02501213A - | JP50647188 | 1988-06-23 | JPH02501213A | 1990-04-26 | |
| A basic airfoil has its operating performance improved by incorporating one or more apertures in the airfoil adjacent its trailing edge. These apertures (24) extend from the upper surface (18) of the airfoil down through to the lower surface (20) of the airfoil. The entry port (25) and the exit port (26) of these apertures (24) has a greater circumference than that of the throat (27) circumference which is intermediate thereto. This structure forms a venturi having a vertical axis. Spaced below the throat (27) of the aperture (24) are a plurality of air nozzles (30) that communicate with an air plenum chamber (32) within the airfoil. A source of pressurized air (35) is connected to the plenum chamber (32). The venturi enhanced airfoil can be utilized both in a horizontal fixed airfoil or its structure can also be incorporated into the tail rudder (53) of an aircraft or helicopter. The venturi enhanced airfoil can be oriented in any position between the horizontal and vertical axes. | ||||||
| 10 | 물체 위에 퍼텐셜을 생성하는 방법 및 시스템 | KR1020047008355 | 2002-11-29 | KR1020040071155A | 2004-08-11 | 크리스티안센,아르네 |
| 본 출원은 물체 위에 퍼텐셜을 제조하기 위해 유체역학적 효과를 이용하는 방법 및 시스템에 관한 것이다. 이러한 방식으로 얻어진 힘은 선박, 잠수함, 비행기 및 비행선의 추진 및 조종에 사용된다. 유체 내에 침지된 물체는 모든 측면에서 동일한 압력을 받는다. 물체의 한 측면에 근접한 흐름은 국부 압력을 감소시키며 물체 위에 퍼텐셜을 생성한다. 이는 물체, 즉 비행기 날개를 유체 내에서 이동시킴으로써 수행된다. 그러한 퍼텐셜은 물체의 한 측면 위에 흐름 또는 흐름들을 설정함으로써 생성될 수 있다. 힌지에 의해 비행기에 부착되는 물체는 상승, 추진 및 조정에 유용하며 상승 및 조정을 위한 속도와 무관하게 한다. 잠수함의 경우도 이와 동일하다. 비행선 및 해양 선박은 형태가 일체화된 추진형 물체를 갖도록 설계된다. 흐름은 각 물체의 정체선 근처에 놓여 선단 엣지를 형성하는 튜브 내의 노즐, 구멍 또는 슬릿으로부터 생성된다. 선박에 사용될 때, 이러한 기술은 선수 파도를 낮추며 스크류 추진력과 관련된 동력학적 손실을 제거한다. 조종력과 정밀도가 개선된다. | ||||||
| 11 | Active flow control on a vertical stabilizer and rudder | EP11183674.8 | 2011-10-03 | EP2441669B1 | 2017-01-04 | Whalen, Edward A; Goldhammer, Mark I |
| 12 | ROTOR NOISE SUPPRESSION | EP13872275.6 | 2013-12-31 | EP2964890A2 | 2016-01-13 | KARAM, Michael Abraham |
| An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture. | ||||||
| 13 | SYNCHRONIZATION OF FLUIDIC ACTUATORS | EP12843978.3 | 2012-10-25 | EP2771239A1 | 2014-09-03 | SEIFERT, Avraham; DAYAN, Isaac; SHTENDEL, Tom |
| A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators. | ||||||
| 14 | METHOD AND APPARATUS FOR CONTROLLING FLOW ABOUT A TURRET | EP11727877.0 | 2011-06-13 | EP2595880A1 | 2013-05-29 | ULLMAN, Alan, Z. |
| Methods and apparatus are provided to control flow separation of an ambient flow along a surface and about a turret (12), such as by reducing flow separation aft of the turret. By reducing flow separation, the resulting turbulence may be similarly reduced such that the performance of a system, such as a laser system, housed by the turret may be improved. To reduce flow separation, a motive flow may be provided by ejector nozzles (32) that open through the surface and are positioned proximate to and aft of the turret relative to the ambient flow. The motive flow has a greater velocity than the ambient flow to thereby create a region aft of the turret of reduced pressure relative to an ambient pressure. Within this region of reduced pressure aft of the turret, a portion of the ambient flow mixes with the motive flow, thereby reducing or eliminating flow separation. | ||||||
| 15 | METHOD AND DEVICE FOR GENERATING MIXTURES OF FLUIDS IN A BOUNDARY LAYER | EP03782227.7 | 2003-11-25 | EP1565659B1 | 2007-11-14 | VIDA, Nikolaus; KIKNADEZ, Gennady Iraklievich; GACHECHILADZE, Ivan Alexandrovich |
| The invention proposes a method and a device to generate an area of a mixture of fluids by introducing media having at least a different physical or chemical property into a boundary layer of a surface using vortices. The method and the device can be applied to moving vehicles or walls of containers surrounding streaming fluids, the fluids being especially mixtures of gases, liquids or combinations of gases and liquids. | ||||||
| 16 | Combined acoustic and anti-ice engine inlet liner | EP98306935.2 | 1998-08-28 | EP0913326B1 | 2002-04-24 | Parente, Charles A. |
| 17 | SYNTHETIC JET ACTUATORS FOR COOLING HEATED BODIES AND ENVIRONMENTS | EP98957870 | 1998-11-12 | EP1040736A4 | 2001-03-07 | GLEZER ARI; ALLEN MARK G |
| Briefly described, the present invention is concerned with cooling heated bodies and/or heated fluid with synthetic jet actuators in either open or closed systems. A first preferred embodiment of a cooling system of the present invention comprises a synthetic jet actuator directed to impinge directly on a heat producing (or heated) body. The synthetic jet actuator generates a synthetic jet stream comprised of cool ambient fluid that impinges on the heated surface thereby cooling this surface. As an example, the heated surface/body could be a microchip array in a microcomputer. After coming into contact with the heated surface, the fluid moves along the surface and is finally rejected to the ambient where it mixes and cools down. The synthetic jet may be incorporated into a modular unit that may be clipped on to a circuit board or other heat producing element to provide added, 'ad hoc' cooling. In another configuration, a synthetic jet actuator may be positioned, relative to the heated surface, to create a synthetic jet stream to flow along the heated surface. In this embodiment, the flow would be approximately tangential to a surface of a heat producing body. This embodiment may further comprise a cyclical flow of the fluid jet, along the heated body and about a heat sink surface. | ||||||
| 18 | Improvements in jet-propelled aircraft | EP88830351.8 | 1988-08-30 | EP0356601A1 | 1990-03-07 | Capuani, Alfredo |
In a jet-propelled aircraft of the type in which the propulsion jets are directed onto a wing (4) so as to achieve an ejector effect, two vertical tail-fin (10) surfaces are provided and extend downwardly beneath the centre of gravity of the aircraft to return the aircraft to a correct attitude when it tends to assume a position in which its longitudinal axis is transversal to the direction of flight. |
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| 19 | Anordnung zur Beeinflussung der Strömung an aerodynamischen Profilen | EP81108456.5 | 1981-10-17 | EP0052242A1 | 1982-05-26 | Quast, Armin, Dipl.-Ing.; Horstmann, Karl-Heinz, Dipl.-Ing. |
Durch die vorliegende Anordnung ist es möglich, laminare Ablöseblasen zu verhindern oder diese in widerstandsvermindernder Weise zu reduzieren. Dies wird dadurch erreicht, daß bei Profilen für Reynolds-Zahlen < 5 x 10+6 eine Vielzahl von Ausblas- und/oder Ansaugeöffnungen 12 mit kleinem Querschnitt im Bereich der Ablösestelle 6,10 der laminaren Strömung angeordnet sind, deren Ausblase- bzw. Ansaugebeiwert Die Ausblasrichtung der Ausblasöffnungen 12 liegt im wesentlichen senkrecht zur Profiloberfläche. Die Ausblasöffnungen 12 weisen einen Durchmesser kleiner 1 mm, vorzugsweise zwischen 0,6 und 0,8 mm auf. Die Ausströmgeschwindigkeit liegt in der Größenordnung von 10 ms. Für die Zufuhr und Drucküberhöhung des auszublasenden Fluids ist zweckmäßig eine Staudruckanordnung 16,18 vorgesehen. Die Anordnung wird besonders zweckmäßig bei Flügelprofilen langsam fliegender Flugzeuge, vorzugsweise von Segelflugzeugen oder Leichtflugzeugen, verwendet. |
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| 20 | Thermal protection and drag reduction method and system for ultra high-speed aircraft | US15550777 | 2016-02-06 | US20180057191A1 | 2018-03-01 | Wenwu ZHANG; Shuhong XIANG; Chunhai GUO; Jingyu TONG; Tianrun ZHANG; Yang YANG; Tao SONG |
| Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged. | ||||||
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