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1. 发明授权

US10618626B2 Wing for an aircraft having a simplified movable aerodynamic surface and a flexible sealing 有权
公开(公告)号：US10618626B2
公开(公告)日：2020-04-14
申请号：US15718974
申请日：2017-09-28
申请人： Airbus Operations GmbH
发明人： Bernhard Schlipf , Dort Daandels
IPC分类号： B64C9/02 , B64C9/14
CPC分类号： B64C9/02 , B64C9/14 , B64C2009/143
摘要： A wing for an aircraft includes a wing structure attachable to a body of an aircraft, at least one high lift body movably supported at the wing structure, a drive unit coupled with the wing structure and the high lift body and adapted to move the high lift body relative to the wing structure in a chordwise direction between a retracted position and an extended position, and a sealing device coupled with the high lift body and the wing structure. The high lift body comprises at least one outer edge facing to the wing structure, which at least one outer edge creates a gap to the wing structure at least in an extended position. The sealing device includes a flexible sealing body, which seals the intermediate space between the high lift body and the wing structure in extended positions of the high lift body.

2. 发明授权

US09714079B2 High-lift device of air vehicle 有权
公开(公告)号：US09714079B2
公开(公告)日：2017-07-25
申请号：US14389257
申请日：2013-03-29
申请人： THE SOCIETY OF JAPANESE AEROSPACE COMPANIES , KAWASAKI JUKOGYO KABUSHIKI KAISHA
发明人： Kazuhide Isotani , Kenji Hayama
IPC分类号： B64C3/58 , B64C3/50 , B64C9/18 , B64C9/02 , B64C21/08 , B64C9/14
CPC分类号： B64C21/08 , B64C3/50 , B64C9/02 , B64C9/18 , B64C2009/143 , B64C2230/14 , Y02T50/166
摘要： A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.

3. 发明授权

US09656739B2 High lift system for an aircraft and method for influencing the high lift characteristics of an aircraft 有权
公开(公告)号：US09656739B2
公开(公告)日：2017-05-23
申请号：US14063536
申请日：2013-10-25
申请人： Airbus Operations GmbH
发明人： Xavier Hue , Bernhard Schlipf
IPC分类号： B64C9/22 , B64C9/02 , B64C9/14
CPC分类号： B64C9/22 , B64C9/02 , B64C2009/143
摘要： A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.

4. 发明授权

US09079652B2 Droop panel linkage 有权
标题翻译： Droop面板连接
公开(公告)号：US09079652B2
公开(公告)日：2015-07-14
申请号：US13699025
申请日：2010-05-21
申请人： Haikou Yue
发明人： Haikou Yue
IPC分类号： B64C3/38 , B64C9/04 , B64C9/16 , B64C9/32 , B64C9/14
CPC分类号： B64C9/04 , B64C9/16 , B64C9/32 , B64C2009/143 , Y02T50/44
摘要： A droop panel linkage for aircraft includes a lever arm, a main lever, a main tube and at least one drive strut. The lever arm is pivotally attached at a first end to a flap and is pivotally connected at a second end to a first end of the main lever. A second end of the main lever is provided with a first engagement element for engaging with a second engagement element incorporated into or associated with the main tube. The main tube is pivotally connected to a proximal end of the drive strut. A distal end of the drive strut is pivotally attached to the droop panel.
摘要翻译：用于飞行器的下垂面板连杆包括杠杆臂，主杆，主管和至少一个驱动支柱。杠杆臂在第一端处枢转地附接到翼片，并且在第二端枢转地连接到主杆的第一端。主杆的第二端设置有用于与并入或与主管相关联的第二接合元件接合的第一接合元件。主管枢转地连接到驱动支柱的近端。驱动支柱的远端枢转地附接到下垂面板。

5. 发明授权

US09010692B2 High-lift device, wing, and noise reduction structure for high-lift device 有权
标题翻译：用于高升力装置的高升力装置，机翼和降噪结构
公开(公告)号：US09010692B2
公开(公告)日：2015-04-21
申请号：US13557400
申请日：2012-07-25
申请人： Makoto Hirai , Ichiro Maeda
发明人： Makoto Hirai , Ichiro Maeda
IPC分类号： B64C9/24
CPC分类号： B64C9/24 , B64C2009/143
摘要： A high-lift device suppresses the occurrence of aerodynamic noise while minimizing an increase in airframe weight. The device includes a slat main body disposed to be able to extend from and retract into a main wing, and a concave part formed on the slat main body at a location facing the main wing and able to accommodate at least a part of a leading edge of the main wing. The device also includes an airflow control part disposed at an area in the concave part facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body is retracted into the main wing, and that suppresses turbulence colliding against the area in the concave part facing the upper surface of the main wing when the slat main body is extended from the main wing.
摘要翻译：高升力装置抑制气动噪声的发生，同时使机身重量增加最小化。该装置包括：能够从主翼延伸并缩回到主翼中的板条主体;以及在面向主翼的位置上形成在板条主体上的凹部，能够容纳至少一部分前缘的主翼。该装置还包括一个气流控制部分，该气流控制部分设置在面对主翼的上表面的凹入部分的区域中，当该翼翼主体缩回到主翼中时，该气流控制部分被容纳在主翼和凹部之间，并且当板条主体从主翼部延伸时，抑制湍流与面向主翼的上表面的凹部中的区域碰撞。

6. 发明授权

US08763958B2 Multi-element airfoil system 有权
标题翻译：多元件翼型系统
公开(公告)号：US08763958B2
公开(公告)日：2014-07-01
申请号：US13449807
申请日：2012-04-18
申请人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
发明人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
IPC分类号： B64C3/50
CPC分类号： B64C7/00 , B64C9/02 , B64C9/18 , B64C9/24 , B64C2009/143 , Y02T50/32
摘要： A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.
摘要翻译：多元件翼型系统包括具有前缘区域的翼型元件和连接到翼型元件的皮肤元件。板条部署系统联接到板条和皮肤元件，并且能够展开和缩回板条和皮肤元件。当板条展开时，皮肤元件基本上填充形成在板条和翼型件之间的横向间隙。该系统还包括一个脱离装置和一个传感器，用于基于翼型元件的临界碰撞角度从该间隙移除皮肤元件。该系统可以替代地包括后缘翼片，其中皮肤元件基本上填充翼片和翼型元件的后缘区域之间的横向间隙。在每种情况下，皮肤元件填充翼型元件和展开的挡板或板条之间的间隙，以减少机身噪音。

7. 发明授权

US08511611B2 Slot seal 有权
标题翻译：槽口密封
公开(公告)号：US08511611B2
公开(公告)日：2013-08-20
申请号：US12783642
申请日：2010-05-20
申请人： Paul Blades
发明人： Paul Blades
IPC分类号： B64C1/38
CPC分类号： B64C9/02 , B64C7/00 , B64C9/16 , B64C25/16 , B64C2009/143 , Y02T50/32
摘要： A panel assembly for an aircraft comprises a panel rotatably connected to a support structure and moveable between a first position and a second position. The panel has an aerodynamic surface with a slot at one edge thereof which receives a portion of the support structure when the panel is in the first position. The assembly further comprises a resilient seal member which occupies the slot when the panel is in the second position. The panel may be an aircraft flight control surface, or an aircraft landing gear bay door.
摘要翻译：用于飞机的面板组件包括可旋转地连接到支撑结构并可在第一位置和第二位置之间移动的面板。该面板具有空气动力学表面，在其一个边缘处具有槽，当面板处于第一位置时，该空气动力学表面接收支撑结构的一部分。组件还包括弹性密封构件，当面板处于第二位置时占据槽的弹性密封构件。面板可以是飞机飞行控制面，也可以是飞机起落架舱门。

8. 发明申请

US20130075536A1 High Lift System For An Aircraft 审中-公开
标题翻译：一个飞机的高升力系统
公开(公告)号：US20130075536A1
公开(公告)日：2013-03-28
申请号：US13650749
申请日：2012-10-12
申请人： AIRBUS OPERATIONS GMBH
发明人： Karsten Schröder
IPC分类号： B64C9/24 , B64C9/34
CPC分类号： B64C9/24 , B64C9/34 , B64C2009/143 , Y02T50/32
摘要： A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.
摘要翻译：一种用于飞行器的高升降系统包括至少一个提升挡板，其设置在机翼上，在提升挡板的延伸位置处形成翼的前缘和提升挡板的后缘之间的间隙，并且至少一个翼片调节用于在提升翼片相对于翼片缩回和至少一个延伸位置之间移动的机构。机翼包括具有引导凹陷边缘的凹陷，用于将提升翼片收纳在缩回位置，并且布置在机翼的这样的区域中，使提升翼片的相应形成的后缘区域包括曲率，由此，机翼的前缘和提升翼的后缘是收敛的。收敛和改进的间隙增加了高升程系统的效率，而没有任何有效或可移动的装置。

9. 发明申请

US20120261517A1 Multi-Element Airfoil System 有权
标题翻译：多元素翼型系统
公开(公告)号：US20120261517A1
公开(公告)日：2012-10-18
申请号：US13449807
申请日：2012-04-18
申请人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
发明人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
IPC分类号： B64C3/50 , B64C13/16
CPC分类号： B64C7/00 , B64C9/02 , B64C9/18 , B64C9/24 , B64C2009/143 , Y02T50/32
摘要： A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.
摘要翻译：多元件翼型系统包括具有前缘区域的翼型元件和连接到翼型元件的皮肤元件。板条部署系统联接到板条和皮肤元件，并且能够展开和缩回板条和皮肤元件。当板条展开时，皮肤元件基本上填充形成在板条和翼型件之间的横向间隙。该系统还包括一个脱离装置和一个传感器，用于基于翼型元件的临界碰撞角度从该间隙移除皮肤元件。该系统可以替代地包括后缘翼片，其中皮肤元件基本上填充翼片和翼型元件的后缘区域之间的横向间隙。在每种情况下，皮肤元件填充翼型元件和展开的挡板或板条之间的间隙，以减少机身噪音。

10. 发明授权

US08191835B2 Wing of an aircraft 有权
标题翻译：机翼
公开(公告)号：US08191835B2
公开(公告)日：2012-06-05
申请号：US12448142
申请日：2007-12-11
申请人： Boris Grohmann , Johann Reichenberger , Thomas Lorkowski
发明人： Boris Grohmann , Johann Reichenberger , Thomas Lorkowski
IPC分类号： B64C3/50
CPC分类号： B64C9/02 , B64C7/00 , B64C2009/143
摘要： A wing of an aircraft has a mainplane, which has an upper face, a lower face and an aerodynamically shaped area. The wing has an additional airfoil which is articulated on the mainplane and can be extended from a retracted state with a slot area being opened between the mainplane and the additional airfoil. The wing also has a variable-position slot-varying apparatus which is arranged on the lower face, forms a part of the aerodynamic profile of the additional airfoil or mainplane when the additional airfoil is extended, and at least partially covers the slot area between the mainplane and the additional airfoil on the lower face when the additional airfoil is in the retracted state. The slot-varying apparatus can be varied between a curved configuration, in which it forms a part of an aerodynamic profile, and an extended configuration, in which it at least partially covers the slot area.
摘要翻译：飞机机翼有一个主面板，上面，下面和空气动力学形状的区域。机翼具有附加的翼型件，其在主平面上铰接，并且可以从缩回状态延伸，其中槽面区域在主平面和附加翼型之间打开。机翼还具有可变位置槽变装置，其布置在下表面上，当附加翼型件延伸时，形成附加翼型件或主平面的空气动力学轮廓的一部分，并且至少部分地覆盖主翼面和另外的翼面在下表面上，当附加翼型处于缩回状态时。槽改变装置可以在其形成空气动力学轮廓的一部分的弯曲构型和延伸构型之间变化，其中它至少部分地覆盖槽区域。

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