专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明公开

EP2885206A1 IMPROVED WING CONFIGURATION 审中-公开
标题翻译：改进机翼构
公开(公告)号：EP2885206A1
公开(公告)日：2015-06-24
申请号：EP13829750.2
申请日：2013-08-16
申请人： Adelaide Research&Innovation Pty Ltd
发明人： KELSO, Richard
IPC分类号： B64C3/10 , B64C21/00 , F03D1/06 , F03D3/06 , B64C11/18 , B64C27/467 , F04D29/24 , F03B3/14
CPC分类号： B64C3/14 , B64C3/10 , B64C3/16 , B64C11/005 , B64C2003/142 , B64C2003/146 , B64C2003/148 , F01D5/141 , F01D5/146 , F03B3/14 , F03D1/0633 , F04D29/384 , F04D29/544 , F05B2210/16 , Y02E10/223 , Y02E10/721 , Y02T50/12 , Y02T50/673
摘要： This invention relates to a wing comprising a generally aerofoil (or airfoil) shaped body having a leading edge, a trailing edge, a span, and first and second major surfaces extending between the leading edge and the trailing edge, where at least one of said first or second major surfaces comprises cyclic spanwise variations at or near the leading edge thereof, but not the trailing edge thereof. In preference, the cyclic spanwise variations extend substantially chordwise from at or near the leading edge, progressively diminishing as they extend chordwise so as to disappear at or before reaching the trailing edge of the wing.

2. 发明授权

EP0167534B1 AN AIRFOIL HAVING IMPROVED LIFT CAPABILITY 失效
标题翻译：具有改进提升能力的航空器
公开(公告)号：EP0167534B1
公开(公告)日：1987-08-19
申请号：EP84901643.1
申请日：1984-01-16
申请人： THE BOEING COMPANY
发明人： HINKLEMAN, Michael, Jay
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/142 , Y02T50/12
摘要： An airfoil (10) having improved lift capability and having airfoil curves including a camber divided into three regions I, II and III. Region I has a starting point aft and adjacent a leading edge (12) and encompasses the airfoil stagnation point. Region I has a high curvature around the leading edge and decreases aft along the chord to a first local minimum value of less than 3 for K times C, where C is the length of the chord and K is the reciprocal of the local radius of curvature. The curvature region II starts at the after end of the region I within 10% of the chord length and the curvature in region II first increases from the first local minimum at the aft end of region I and then decreases to a second local minimum within 40% of the chord length.

3. 发明公开

EP3162701A1 AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF 审中-公开
标题翻译： LUFTFAHRZEUG UND VERFAHREN UND VORRICHTUNG ZU DESSEN STEUERUNG
公开(公告)号：EP3162701A1
公开(公告)日：2017-05-03
申请号：EP15275223
申请日：2015-10-30
申请人： BAE SYSTEMS PLC
IPC分类号： B64C3/46 , B64C3/44 , B64C3/48 , B64C29/02
CPC分类号： B64C3/48 , B64C3/44 , B64C3/46 , B64C29/02 , B64C2003/142 , B64C2201/088 , B64C2201/102 , Y02T50/12 , Y02T50/145
摘要： A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.
摘要翻译：一种用于飞行器（10）的机翼构件（14b），所述机翼构件包括限定其纵向轴线并具有上表面和下表面的核心部分（20），所述表面中的至少一个包括设备（22），所述设备（22）至少两个位置，其中在完全伸展的位置中，所述设备的至少部分从所述相应的表面向外延伸，以便增加所述翼部件的有效横截面积并限定相对于其的有效翼面。

4. 发明公开

EP2216243A2 Supersonic laminar flow aircraft wing airfoil 审中-公开
标题翻译： LaminarströmungsprofileinesÜberschallflugzeugflügels
公开(公告)号：EP2216243A2
公开(公告)日：2010-08-11
申请号：EP10152511.1
申请日：2010-02-03
申请人： Alenia Aeronautica S.p.A.
发明人： Di Muzio, Massimiliano , Gatti, Alfredo
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/142 , Y02T50/12
摘要： The lower curve of the airfoil has a forward portion with its concavity facing a forward-lower direction and converging in the leading edge. Such a forward portion locally generates forces having a forward direction component on the wing, i.e. in the direction of advancement of the aircraft, with a consequent reduction of the overall drag on the wing.
摘要翻译：翼面的下曲线具有前部，其凹部面向前下方向并且在前缘中会聚。这样的前部部分局部地产生在机翼上具有前向分量的力，即飞行器前进方向，从而导致机翼上的整体阻力减小。

5. 发明公开

EP1674389A1 Tragwerk, insbesondere Holmkasten, zur Bildung von aerodynamischen Wirkflächen von Luftfahrzeugen 有权
标题翻译： Tragwerk einer airodynamischenWirkflächeeines Flugzeugs
公开(公告)号：EP1674389A1
公开(公告)日：2006-06-28
申请号：EP05027965.2
申请日：2005-12-20
申请人： Airbus Deutschland GmbH (HRB 43527)
发明人： Law, Barnaby
IPC分类号： B64C3/42 , B64C3/44 , B64C3/52
CPC分类号： B64C3/18 , B64C3/42 , B64C3/44 , B64C3/52 , B64C2003/142 , Y02T50/12 , Y02T50/14
摘要： Die Erfindung betrifft ein Tragwerk, insbesondere einen Holmkasten 1,20,49, zur Bildung von aerodynamischen Wirkflächen von Luftfahrzeugen, insbesondere von Tragflächen, Höhenleitwerken oder Seitenleitwerken von Flugzeugen, mit einer Oberschale 2,21,50 und mit einer Unterschale 3,22,51.
Erfindungsgemäß ist im Bereich zwischen der Oberschale 2,21,50 und der Unterschale 3,22,51 mindestens ein Stellelement 11-14,33-48,53-64,67,68 zur Änderung der Oberflächengeometrie der aerodynamischen Wirkfläche und/oder der mechanischen Eigenschaften des Tragwerks angeordnet.
Mittels des erfindungsgemäßen Tragwerks und des hiermit gebildeten Holmkastens 1,20,49 können aerodynamische Wirkflächen, beispielsweise Tragflächen, Höhenleitwerke, Seitenleitwerke oder dergleichen für Luftfahrzeuge, insbesondere Flugzeuge, gebildet werden, die sich dynamisch an unterschiedliche Flugzustände anpassen lassen.
Hierdurch lassen sich unter anderem aerodynamische Verbesserungen durch eine mittels der Steuerelemente 11-14,33-48,53-64,67,68 dem jeweiligen Betriebszustand des Flugzeugs angepasste Oberflächengeometrie der aerodynamischen Wirkflächen und/oder Gewichtseinsparungen durch eine Minimierung von strukturmechanischen Belastungen des Tragwerks erzielen.
摘要翻译：该箱具有布置在上壳体（2）和下壳体（3）之间的定位单元（11-14）。使用控制和调节单元，定位单元根据负载条件改变空气动力学有效表面的表面几何形状和/或箱的机械特性。定位单元根据负载条件改变箱体的弯曲扭转耦合。

6. 发明公开

EP2925600A4 WING AND APPLICATION THEREOF 有权转让
标题翻译： WINGS及其用途
公开(公告)号：EP2925600A4
公开(公告)日：2016-07-27
申请号：EP13858980
申请日：2013-11-25
申请人： BRAY ROBERT REGINALD
发明人： BRAY ROBERT REGINALD
IPC分类号： B63H9/06 , B64C3/14
CPC分类号： B64C3/26 , B63H9/0607 , B64C2003/142 , Y02T50/12 , Y02T70/583
摘要： The present disclosure relates to a wing. More specifically, aspects of the invention relate to a variable shaped wing movable incrementally between a neutral configuration and a deformed configuration, wherein the wing takes a reflexed camber aerofoil section shape in the deformed configuration. The wing includes a first aerofoil segment and a second aerofoil segment having ends connected or fixed to one another at opposing neutral leading and trailing edges and spaced apart from one another along their lengths across a neutral mean camber line extending between the neutral leading and trailing edges to form a neutral aerofoil section of the wing. One or more actuators deform the wing between the neutral aerofoil section and a reflexed camber aerofoil section, with the first and second aerofoil segments being resilient to bias the wing towards an initial at rest aerofoil section.

7. 发明公开

EP2885206A4 IMPROVED WING CONFIGURATION 审中-公开
标题翻译：改进机翼构
公开(公告)号：EP2885206A4
公开(公告)日：2016-03-16
申请号：EP13829750
申请日：2013-08-16
申请人： ADELAIDE RES &INNOVATION PTY LTD
发明人： KELSO RICHARD
IPC分类号： F03D1/06 , B64C3/10 , B64C3/16 , B64C11/00 , B64C11/18 , B64C27/467 , F03B3/14 , F03D3/06 , F04D29/24
CPC分类号： B64C3/14 , B64C3/10 , B64C3/16 , B64C11/005 , B64C2003/142 , B64C2003/146 , B64C2003/148 , F01D5/141 , F01D5/146 , F03B3/14 , F03D1/0633 , F04D29/384 , F04D29/544 , F05B2210/16 , Y02E10/223 , Y02E10/721 , Y02T50/12 , Y02T50/673

8. 发明授权

EP1674389B1 Tragwerk einer aerodynamischen Wirkfläche eines Flugzeugs 有权
标题翻译：飞行器的结构在空气动力学作用表面
公开(公告)号：EP1674389B1
公开(公告)日：2007-09-12
申请号：EP05027965.2
申请日：2005-12-20
申请人： Airbus Deutschland GmbH (HRB 43527)
发明人： Law, Barnaby
IPC分类号： B64C3/42 , B64C3/44 , B64C3/52
CPC分类号： B64C3/18 , B64C3/42 , B64C3/44 , B64C3/52 , B64C2003/142 , Y02T50/12 , Y02T50/14

9. 发明公开

EP1043223A3 Enhanced aerodynamic profile 审中-公开
标题翻译：改进的空气动力学外形
公开(公告)号：EP1043223A3
公开(公告)日：2001-10-17
申请号：EP00500051.8
申请日：2000-03-30
申请人： Munoz Saiz, Manuel
发明人： Munoz Saiz, Manuel
IPC分类号： B64C3/14 , B64C9/24 , B64C1/00 , B64C30/00 , B64C3/50
CPC分类号： B64C9/24 , B64C3/14 , B64C3/50 , B64C30/00 , B64C2003/142 , B64C2003/144 , B64C2003/146
摘要： The enhanced aerodynamic profile of the invention consists of a profile consisting of three sections: a front or leading edge of two sides or plates forming an acute dihedral angle with the vertex facing forward, a central section formed by two parallel sides or plates, and a rear section or trailing edge formed by two sides or plates at an acute dihedral angle with the vertex facing rearward, where the unions on the lower or upper surfaces are suitably rounded, where the front section is a fin or cone turning on an axis which divides it into two unequal parts, the rear part being larger, said fin or cone has the lower surface of its rear section inclined, adapting with another which is inclined in the upper front part of the central section, said fin with positive leading angles is automatically oriented with the direction of the slipstream.

10. 发明公开

EP0772731A1 AIRFOIL SECTION 失效
标题翻译：翼型
公开(公告)号：EP0772731A1
公开(公告)日：1997-05-14
申请号：EP95937244.0
申请日：1995-11-15
申请人： Romanian Air Transport - Tarom -
发明人： TAPOSU, Iosif
IPC分类号： B64C3 , F03D1
CPC分类号： F03D1/0641 , B64C3/14 , B64C2003/142 , F05B2240/301 , Y02E10/721 , Y02T50/12
摘要： The invention refers to an airfoil section that can be used in the areospace and naval industries and also to construct propellers, fans, air-conditioning equipment, hydraulic turbines, missiles, and torpedoes. The principle requires to meet the Kutta-Jukovsky condition at both the leading and trailing edges, i.e. a zero jump of the pressure in these points. This condition is satisfied if the equalities g(0)=g'(0)=0, and g(1)=g'(1)=0 hold where g(x) is the one half thickness distribution along the chord, and g'(x) is the first order derivative of g, both being taken in the specified points. The above-mentioned conditions can be used either to modify the leading and trailing edges of a given classical profile, or to generate new airfoil sections by using a definite skeleton line and a definite thickness distribution. Using this airfoil section, new lifting surfaces with higher performances as to the present-day configurations can be constructed.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式