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11. 发明授权

EP2774843B1 System and method for reducing rotor blade noise 有权
标题翻译：系统和方法，用于减小转子叶片的噪音
公开(公告)号：EP2774843B1
公开(公告)日：2016-04-06
申请号：EP13165379.2
申请日：2013-04-25
申请人： Bell Helicopter Textron Inc.
发明人： Sutton, Drew
IPC分类号： B64C23/06 , B64C27/467 , F01D5/14
CPC分类号： F01D7/00 , B64C23/06 , B64C27/467 , B64C27/615 , B64C27/72 , B64C2027/7261 , B64C2230/14 , B64C2230/26 , B64C2230/28 , F01D5/145 , Y02T50/162 , Y02T50/166 , Y02T50/34 , Y02T50/66

12. 发明公开

EP2402251A3 A jet engine installation 无效转让
标题翻译：动力装置的安装
公开(公告)号：EP2402251A3
公开(公告)日：2015-08-05
申请号：EP11171651.0
申请日：2011-06-28
申请人： Rolls-Royce plc
发明人： Morvant, Romuald , Britchford, Kevin Mark
IPC分类号： B64D29/02 , B64C23/06
CPC分类号： B64D29/02 , B64C23/06 , Y02T50/162
摘要： Noise generated by a gas turbine engine 6 supported by a pylon 8 on a wing 2 of an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine 6. The shear layer is influenced by means of one or more winglets 18, 20, 22 which interact with the free-stream flowfield to deflect the shear layer 14 downwardly, to avoid interaction with a flap 4 on the wing 2, or to reduce the strength of the shear layer 14.

13. 发明授权

EP2167380B1 ENGINE NACELLE OF AN AIRCRAFT COMPRISING A VORTEX GENERATOR ARRANGEMENT 有权
标题翻译：发动机GONDOLA与涡流发生器排列的飞机
公开(公告)号：EP2167380B1
公开(公告)日：2015-03-25
申请号：EP08759254.9
申请日：2008-06-16
申请人： Airbus Operations GmbH
发明人： SCHWETZLER, Detlev
IPC分类号： B64C7/02 , B64C23/06 , B64D29/02
CPC分类号： B64C7/02 , B64C23/06 , B64D29/02 , Y02T50/162

14. 发明授权

EP2316729B1 An element for generating a fluid dynamic force 有权
标题翻译：元件用于产生流体动力
公开(公告)号：EP2316729B1
公开(公告)日：2015-03-11
申请号：EP10182928.1
申请日：2006-07-13
申请人： JARILO LIMITED
发明人： Prince, Simon , Khodagolian, Vahik
IPC分类号： B64C23/06
CPC分类号： B64C23/06 , B64C2230/06 , B64C2230/18 , B64C2230/20 , F03D1/0641 , F05D2240/30 , Y02E10/721 , Y02T50/162 , Y02T50/166

15. 发明公开

EP2801521A1 Vortex generator using shape memory alloys 有权
标题翻译： Wirbelgenerator unter Verwendung von Formspeicherlegierungen
公开(公告)号：EP2801521A1
公开(公告)日：2014-11-12
申请号：EP14167782.3
申请日：2014-05-09
申请人： The Boeing Company
发明人： Shivashankara, Belur N. , Mabe, James H. , Clingman, Dan J.
IPC分类号： B64C23/06
CPC分类号： F03G7/065 , B64C9/32 , B64C23/06 , Y02T50/162 , Y10T29/49002
摘要： In one embodiment, the disclosed vortex generator may include a flap (12); a bearing (16) configured to be mounted on a surface (20); an axle (14) retained in the bearing, the flap attached to the axle such that the flap rotates relative to the bearing about the axle; and an actuator (32) made of a shape memory alloy attached to the flap and to a support, the actuator shaped to receive the axle therethrough, such that a change in temperature of the actuator causes the actuator to rotate the flap relative to the bearing.
摘要翻译：在一个实施例中，所公开的涡流发生器可以包括挡板（12）; 构造成安装在表面（20）上的轴承（16）; 保持在所述轴承中的轴（14），所述翼片附接到所述轴，使得所述翼片相对于所述轴承绕所述轴线旋转; 以及致动器（32），其由形状记忆合金制成，附接到所述翼片和支撑件，所述致动器成形为接收所述轴穿过其中，使得所述致动器的温度变化使致动器相对于所述轴承旋转所述翼片。

16. 发明公开

EP2051906A4 AERODYNAMIC DEVICE FOR IMPROVEMENT OF SUSTENTATION COEFFICIENT 有权转让
标题翻译： AERODYNAMISCHE VORRICHTUNG ZUR VERBESSERUNG DES AUFTRIEBSKOEFFIZIENTEN
公开(公告)号：EP2051906A4
公开(公告)日：2013-06-05
申请号：EP07784931
申请日：2007-08-08
申请人： EMBRAER AERONAUTICA SA
发明人： DO AREAL SOUTO FERRARI MARCELLO
IPC分类号： B64C23/06 , B64C3/58 , B64C7/02 , B64C9/24
CPC分类号： B64C3/58 , B64C7/02 , B64C9/24 , B64C23/06 , Y02T50/162 , Y02T50/32
摘要： Aircraft wings are provided with aerodynamic devices that improve the wing's low airspeed aerodynamics. In preferred embodiments, the aircraft wings include a slat operatively positioned at the wing's leading edge for movement between a retracted position for relatively high airspeed aircraft operations, and a deployed position for relatively low airspeed aircraft operations. An aerodynamic device is positionally fixed to the wing laterally adjacent the leading edge slat, the device having a forward end extending forwardly of the wing leading edge. The device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, but provides substantially no aerodynamic improvement when the slat is in the retracted position thereof during high airspeed aircraft operations.
摘要翻译：机翼设有空气动力学装置，可改善机翼低空速空气动力学。在优选实施例中，飞行器机翼包括可操作地定位在翼的前缘上用于在用于相对高空速飞行器操作的缩回位置之间运动的板条和用于相对低空速飞行器操作的展开位置。空气动力学装置在横向邻近前缘板条定位固定在机翼上，该装置具有向前延伸到机翼前缘的前端。该装置可响应于板条运动到其展开位置而可操作，以便在低空速飞行器操作下改善机翼的空气动力学，但是当高空速飞行器中的板条处于其缩回位置时基本上不提供空气动力学改进操作。

17. 发明公开

EP2536627A2 AERODYNAMIC STRUCTURE HAVING A RIDGED SOLAR PANEL AND AN ASSOCIATED METHOD 有权
标题翻译： AERODYNAMISCHE STRUKTUR MIT EINEM GERIPPTEN SONNENKOLLEKTOR UNDZUGEHÖRIGESVERFAHREN
公开(公告)号：EP2536627A2
公开(公告)日：2012-12-26
申请号：EP11751968.6
申请日：2011-01-19
申请人： The Boeing Company
发明人： DONG, Jian
IPC分类号： B64C23/06 , B64D41/00 , H01L31/0236
CPC分类号： B64C23/06 , B64D41/00 , B64D2211/00 , H01L31/0236 , H02S10/40 , Y02E10/50 , Y02T50/162 , Y02T50/53 , Y02T50/55
摘要： Air vehicles and associated aerodynamic structures are provided which include ridged solar panels to both reduce the drag and increase the solar energy harvested by the solar panel. The air vehicle may include an airframe and a solar panel carried by the airframe and defining an exterior surface thereof. The solar panel may include a plurality of ridged structures extending in a lengthwise direction. The ridged structures may be arranged such that a majority of the airflow over the exterior surface flows in the lengthwise direction. The plurality of ridged structures may include a plurality of lengthwise extending projections spaced about by respective valleys.
摘要翻译：提供了空中车辆和相关的空气动力学结构，其包括脊状太阳能电池板以减少阻力并增加由太阳能电池板收集的太阳能。空中交通工具可以包括机身和由机身承载并限定其外表面的太阳能电池板。太阳能电池板可以包括沿长度方向延伸的多个脊状结构。脊状结构可以被布置成使得外表面上的大部分气流在长度方向上流动。多个脊状结构可以包括多个纵向延伸的突起，其围绕相应的谷分隔开。

18. 发明公开

EP2441669A2 Active flow control on a vertical stabilizer and rudder 有权
标题翻译：活动Strömungsssteuerung在尾翼与方向舵
公开(公告)号：EP2441669A2
公开(公告)日：2012-04-18
申请号：EP11183674.8
申请日：2011-10-03
申请人： The Boeing Company
发明人： Whalen, Edward A , Goldhammer, Mark I
IPC分类号： B64C5/06 , B64C21/00 , B64C23/00 , B64C23/06
CPC分类号： B64C5/06 , B64C21/00 , B64C23/005 , B64C23/06 , B64C2230/04 , B64C2230/16 , Y02T50/162 , Y02T50/166 , Y10T137/0318
摘要： Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft.

19. 发明公开

EP2316729A2 An element for generating a fluid dynamic force 有权
标题翻译：用于产生流体动力的元素
公开(公告)号：EP2316729A2
公开(公告)日：2011-05-04
申请号：EP10182928.1
申请日：2006-07-13
申请人： City University
发明人： Prince, Simon , Khodagolian, Vahik
IPC分类号： B64C23/06
CPC分类号： B64C23/06 , B64C2230/06 , B64C2230/18 , B64C2230/20 , F03D1/0641 , F05D2240/30 , Y02E10/721 , Y02T50/162 , Y02T50/166
摘要： This invention relates to an element (11) for generating a fluid dynamic force, the element (11) comprising first (13) and second (15) surfaces extending in opposite directions from a leading edge (17) of the element (11) and meeting at a trailing edge (18) thereof to define a three dimensional body that is shaped to generate a fluid dynamic force when immersed at an angle of attack α to a fluid flow over the element (11) in a flow direction U, the first surface (13) comprising an array of fluid inlets (19) and the second surface (15) comprising a corresponding array of fluid outlets (21), each said inlet (19) being fluidly coupled to a said outlet (21) by means of a fluid duct (23) at least part of which is pitched at an angle θ to a tangent plane (Y—Y) to said second surface (15) in the vicinity of said outlet (21) and skewed at an angle ϕ to said fluid flow direction U, the arrangement being such that the element (11) is operable in use to generate a relatively high fluid pressure region downstream of said leading edge (17) proximate said first surface (13) and a relatively low fluid pressure region downstream of said leading edge (17) proximate said second surface (15), and fluid from said relatively high fluid pressure region is enabled to flow into said fluid inlets (19) through said fluid ducts (23) and out of said fluid outlets (21) into said relatively low pressure region to generate fluid vortices which reenergise said low pressure region and delay boundary layer separation from said second surface (15).
摘要翻译：本发明涉及用于产生流体动力的元件（11），元件（11）包括从元件（11）的前缘（17）沿相反方向延伸的第一表面（13）和第二表面（15），以及在其后缘（18）处相遇以限定三维主体，所述三维主体被成形为当以在流动方向U上的元件（11）上的流体流以迎角α浸入时产生流体动力，第一包括流体入口（19）阵列的第一表面（13）和包括流体出口（21）的相应阵列的第二表面（15），每个所述入口（19）通过流体连接到所述出口流体通道（23），其至少一部分相对于在所述出口（21）附近的所述第二表面（15）的切平面（Y-Y）以角度θ倾斜并且以与所述出口流体流动方向U，该布置使得元件（11）在使用中可操作以产生相对较高的流体压力在所述前缘（17）的靠近所述第一表面（13）的下游和在所述前缘（17）的靠近所述第二表面（15）的下游的相对较低的流体压力区域，并且来自所述较高流体压力区域的流体是能够通过所述流体通道（23）流入所述流体入口（19）并流出所述流体出口（21）进入所述较低压力区域，从而产生流体涡流，所述流体涡流重新激励所述低压区域并延迟边界层与所述第二表面（15）。

20. 发明授权

EP1937553B1 DISPOSITIF DE CONTROLE D'UN SILLAGE TOURBILLONNAIRE ENGENDRE PAR UN ELEMENT OBLONG SUR L'EXTRADOS D'UNE SURFACE PORTANTE D'UN AERONEF 有权
标题翻译：设备用于控制细长元件飞机的机翼，这样生产的，以纺
公开(公告)号：EP1937553B1
公开(公告)日：2010-05-05
申请号：EP06808118.1
申请日：2006-09-13
申请人： AIRBUS OPERATIONS (SAS)
发明人： ATINAULT, Olivier
IPC分类号： B64C23/06 , B64C7/02
CPC分类号： B64C7/02 , B64C23/06 , Y02T50/162

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