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1. 发明授权

EP3150485B1 ACTIVE FLOW CONTROL ON A VERTICAL STABILIZER AND RUDDER 有权
公开(公告)号：EP3150485B1
公开(公告)日：2018-12-12
申请号：EP16199645.9
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.

2. 发明公开

EP3348471A1 LIFTING SURFACE 有权
公开(公告)号：EP3348471A1
公开(公告)日：2018-07-18
申请号：EP17382018.4
申请日：2017-01-17
申请人： Airbus Operations, S.L.
发明人： GARCÍA NIETO, Carlos , VÉLEZ DE MENDIZÁBAL ALONSO, Iker , CRESPO PEÑA, Soledad , GUINALDO FERNÁNDEZ, Enrique , VÁZQUEZ CASTRO, Jesús Javier , TORRES SALAS, Álvaro
IPC分类号： B64C23/06
CPC分类号： B64C21/08 , B64C21/10 , B64C23/06 , B64C2230/08 , B64C2230/26 , Y02T50/162
摘要： Lifting surface comprising:
• a movable discontinuity (1) located in the surface of the lifting surface, the movable discontinuity (1) being movable between:
o an active position in which the movable discontinuity (1) acts as vortex generator, and
o a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface,

• a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface comprising at least two openings (3) in its surface spanwise distant from each other in communication with the conduit (2),
the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.

3. 发明授权

EP2536627B1 AERODYNAMIC STRUCTURE HAVING A RIDGED SOLAR PANEL AND AN ASSOCIATED METHOD 有权
标题翻译：具有激光太阳能电池板的空气动力学结构及相关方法
公开(公告)号：EP2536627B1
公开(公告)日：2017-08-02
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：提供了空气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获的太阳能。飞行器可包括机身和由机身携带并限定其外表面的太阳能面板。太阳能面板可以包括沿纵向方向延伸的多个脊状结构。脊状结构可以布置成使得外表面上的大部分气流沿纵向方向流动。多个脊状结构可以包括多个纵向延伸的突出部，所述突出部通过相应的谷间隔开。

4. 发明授权

EP2625096B1 DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT 有权
标题翻译：用于增加飞行器的气动升降装置和方法
公开(公告)号：EP2625096B1
公开(公告)日：2017-07-19
申请号：EP11767986.0
申请日：2011-10-05
申请人： Airbus Operations GmbH
发明人： WEBER, Carsten , FISCHER, Markus , GROTE, Arne , RADESPIEL, Rolf , DREYER, Martin
IPC分类号： B64C5/12 , B64C9/34 , B64C23/06
CPC分类号： B64C23/06 , B64C5/12 , B64C9/34 , Y02T50/162 , Y02T50/44

5. 发明公开

EP3176082A1 A VORTEX GENERATOR ARRANGEMENT FOR AN AIRCRAFT 有权
标题翻译：航空器的涡旋发生器装置
公开(公告)号：EP3176082A1
公开(公告)日：2017-06-07
申请号：EP15197297.3
申请日：2015-12-01
申请人： Airbus Operations GmbH
发明人： Stefes, Bruno , Eilken, Wolfgang , Paul, Erich
IPC分类号： B64C23/06 , B64C13/16 , B64C9/02
CPC分类号： B64C23/06 , B64C3/00 , B64C5/02 , B64C9/00 , B64C9/02 , B64C9/14 , B64C13/16 , Y02T50/162 , Y02T50/32 , Y02T50/44
摘要： The present invention relates to a vortex generator arrangement for an aircraft (51), and to a flow control system and an aircraft comprising such vortex generator arrangement. The vortex generator arrangement comprises a surface portion (18, 19; 18, 51) facing a first region of space and adapted to constitute a flow surface, a vortex generating element (21) disposed in the first region of space, an element support structure (10) rigidly connected to the vortex generating element (21), a mounting structure (3, 4, 15) to which the element support structure (10) is mounted such that the element support structure (10) and the vortex generating element (21) together are rotatable with respect to the mounting structure (3, 4, 15) about a rotational axis (40) between a first rotational position and a second rotational position, a biasing means biasing the vortex generating element (21) towards the second rotational position, a retaining means adapted to retain the vortex generating element (21) in the first rotational position, and a release means adapted to release the vortex generating element (21) from the retaining means. The rotational axis (40) extends transversely with respect to the surface portion (18, 19; 18, 51). The vortex generating element (21) is disposed completely in the first region of space in each rotational position thereof about the rotational axis (40). The projection of the vortex generating element (21) onto a projection plane is smaller in the first rotational position than in the second rotational position, wherein the projection plane extends perpendicularly to a tangent plane of the surface portion (18, 19; 18, 51) at a reference point of the surface portion (18, 19; 18, 51) and to a predetermined direction parallel to the extension of the tangent plane.
摘要翻译：本发明涉及用于飞机（51）的涡流发生器装置，并且涉及包括这种涡流发生器装置的流量控制系统和飞行器。涡流发生器装置包括面向第一空间区域并适于构成流动表面的表面部分（18,19; 18,51），设置在第一空间区域中的涡流产生元件（21），元件支撑结构（10）刚性地连接到涡流产生元件（21）;安装结构（3,4,15），元件支撑结构（10）安装到所述安装结构（3,4），使得元件支撑结构（10）和涡流产生元件 21）一起相对于安装结构（3,4,15）围绕旋转轴线（40）在第一旋转位置和第二旋转位置之间旋转，偏置装置将涡流产生元件（21）朝向第二旋转位置旋转位置，适于将涡流产生元件（21）保持在第一旋转位置的保持装置以及适于将涡流产生元件（21）从保持装置释放的释放装置。旋转轴线（40）相对于表面部分（18,19; 18,51）横向延伸。涡流产生元件（21）在其每个旋转位置围绕旋转轴线（40）完全布置在第一空间区域中。涡流产生元件（21）在投影平面上的投影在第一旋转位置中比在第二旋转位置中小，其中投影平面垂直于表面部分（18,19; 18,51）的切面延伸）在所述表面部分（18,19; 18,51）的参考点并且平行于所述切平面的延伸的预定方向上。

6. 发明公开

EP3169968A1 OPTICAL WINDOW SYSTEM WITH AERO-OPTICAL CONDUCTIVE BLADES 有权
标题翻译：带有光导电刀片的光学窗系统
公开(公告)号：EP3169968A1
公开(公告)日：2017-05-24
申请号：EP15715905.4
申请日：2015-03-20
申请人： Raytheon Company
发明人： VASQUEZ, David A. , USHINSKY, Michael , ICHKHAN, Joseph J.
IPC分类号： F42B10/46 , B64C1/36 , B64C1/38 , F42B15/34 , B64C1/14
CPC分类号： B64C1/1484 , B32B37/30 , B64C1/1492 , B64C21/00 , B64C23/06 , B64C2230/10 , B64D47/08 , F42B10/46 , F42B15/34 , H05B3/84 , Y02T50/162 , Y02T50/166
摘要： A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.
摘要翻译：本文描述了一种改善在流体流动中操作的光学窗口的光学特性的方法，该光学窗口具有第一和第二光学透射材料板 - 每个光学透射材料具有彼此相邻，平行且至少部分地共同延伸的边缘。该方法包括在第一和第二透光材料板的两个相邻边缘之间插入导热片; 以及通过将导热叶片从光学窗玻璃的外表面突出到流体流中来提升光学窗口前方的逆流停滞区。

7. 发明公开

EP3053826A1 A VORTEX GENERATOR ARRANGEMENT 有权
标题翻译： WIRBELGENERATORANORDNUNG
公开(公告)号：EP3053826A1
公开(公告)日：2016-08-10
申请号：EP16154479.6
申请日：2016-02-05
申请人： Airbus Operations GmbH
发明人： Hegenbart, Matthias , Eilken, Wolfgang , Paul, Erich , Stefes, Bruno , Duken, Lena
IPC分类号： B64C9/02 , B64C13/16 , B64C23/06
CPC分类号： B64C23/06 , B64C9/02 , B64C13/16 , B64C21/10 , Y02T50/162 , Y02T50/44
摘要： The invention relates to a vortex generator arrangement for an aircraft, comprising a surface section (2), which is intended to have a flow flowing over it and in which an opening (3) is provided, a flap element (4) which is pivotable between a first position, in which it extends in the plane of the surface section (2), and a second position, in which it extends out of the plane of the surface section (2), a biasing arrangement (15) by means of which the flap element (4) is biased towards the second position, a first retaining device (13) for retaining the flap element (4) in the first position, a second retaining device (21) for retaining the flap element (4) in the second position against a torque acting on the flap element (4) towards the first position, and a release device (17) for releasing the flap element (4) from the first retaining device (13). The biasing arrangement (15), the first retaining device (13) and the second retaining device (21) are configured in such a manner that the second retaining device (21) automatically retains the flap element (4) in the second position after the flap element (4) has been pivoted by the biasing arrangement (15) from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device (21) automatically releases the flap element (4), and the flap element (4) pivots against the force of the biasing arrangement (15) into the first position and is automatically retained therein by the first retaining device (13).
摘要翻译：本发明涉及一种用于飞行器的涡流发生器装置，包括一个表面部分（2），该表面部分（2）旨在具有在其上流动的流动并且其中设有一个开口（3），一个可枢转的挡板元件在其在其表面部分（2）的平面中延伸的第一位置和第二位置之间，其延伸出表面部分（2）的平面之外的偏置装置（15），偏置装置其中所述翼片元件（4）被朝向所述第二位置偏置，用于将所述翼片元件（4）保持在所述第一位置的第一保持装置（13），用于将所述翼片元件（4）保持在所述第一保持装置所述第二位置抵抗朝向所述第一位置作用在所述翼片元件（4）上的扭矩，以及用于将所述翼片元件（4）从所述第一保持装置（13）释放的释放装置（17）。偏置装置（15），第一保持装置（13）和第二保持装置（21）被构造成使得第二保持装置（21）在襟翼元件（4）在第翼片元件（4）已经由偏置装置（15）从第一位置枢转到第二位置。一旦扭矩超过预定值，第二保持装置（21）就会自动释放襟翼元件（4），并且襟翼元件（4）克服偏压装置（15）的力转动到第一位置，并且是由第一保持装置（13）自动保持在其中。

8. 发明公开

EP3042073A1 VORTEX GENERATOR FOR A WIND TURBINE 有权转让
标题翻译： VORTEXGENERATORFÜREINE WINDTURBINE
公开(公告)号：EP3042073A1
公开(公告)日：2016-07-13
申请号：EP14792895.6
申请日：2014-09-01
申请人： Corten Holding BV
发明人： CORTEN, Gustave Paul
IPC分类号： F03D1/06
CPC分类号： F03D1/0675 , B64C23/06 , B64C2230/26 , F03D1/0633 , F03D1/0641 , F03D3/062 , F05B2240/122 , F05B2240/30 , Y02E10/721 , Y02T50/162 , Y02T50/166
摘要： A blade for a wind turbine having an airfoil with a thickness of at least 20% and in particular at least 25% including a vortex generator pair between chord wise position 20% c and 70% c, the vortex generator pair including 2 not directly connected fins and a base which interconnects the fins and where the fins are placed under opposite angles of attack. The fins are cambered by at least 1% in particular by at least 2% and more particularly by a least 3% of the fin chord. According to an embodiment the base of the vortex generator pair is W-shaped, the fins of a pair are designed to generate contra rotating vortices and the distance between the suction sides of the fins is approximately 150% of that between the pressure sides and the trailing part of the fins is rounded so that non-concentrated vortices are generated.
摘要翻译：一种用于风力涡轮机的叶片，其具有至少20％，特别是至少25％的厚度的翼型，包括在纬向位置20％c和70％c之间的涡流发生器对，所述涡流发生器对包括2未直接连接翅片和基座，其互连翅片，翅片在相反的角度下放置。翼片的弧度至少为1％，特别是至少为2％，特别是翅片弦的至少3％。根据一个实施例，涡流发生器对的基部是W形的，一对的翅片被设计成产生反旋转涡流，并且翅片的吸力侧之间的距离大约是压力侧和压力侧之间的距离的150％翅片的尾部是圆形的，从而产生非浓缩涡流。

9. 发明授权

EP2139763B2 DEPLOYABLE FLAP EDGE FENCE AND METHOD OF OPERATION 有权
标题翻译：折叠缘围栏一个在后面头盖和工作程序
公开(公告)号：EP2139763B2
公开(公告)日：2015-12-09
申请号：EP08745052.4
申请日：2008-04-03
申请人： The Boeing Company
发明人： LARSSEN, Jon V. , CALKINS, Frederick T.
IPC分类号： B64C9/18 , B64C9/24 , B64C23/06 , B64C7/00
CPC分类号： B64C9/18 , B64C7/00 , B64C9/24 , B64C23/06 , Y02T50/162 , Y02T50/32

10. 发明授权

EP2511175B1 Systems and methods for attenuation of noise and wakes produced by aircraft 有权
标题翻译：装置和方法用于飞机和椎骨的降噪
公开(公告)号：EP2511175B1
公开(公告)日：2014-10-22
申请号：EP12160691.7
申请日：2012-03-22
申请人： The Boeing Company
发明人： Shmilovich, Arvin , Khodadoust, Abdollah
IPC分类号： B64C23/06
CPC分类号： B64C21/04 , B64C9/38 , B64C21/08 , B64C23/06 , B64C2230/04 , B64C2230/06 , Y02T50/162

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