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. 发明申请

US20180155007A1 FLAP AND AIRCRAFT 审中-公开
公开(公告)号：US20180155007A1
公开(公告)日：2018-06-07
申请号：US15577712
申请日：2016-04-14
申请人： MITSUBISHI AIRCRAFT CORPORATION , Japan Aerospace Exploration Agency
发明人： Kensuke Hayashi , Mitsuhiro Murayama , Kazuomi Yamamoto
IPC分类号： B64C9/20 , B64C23/06
CPC分类号： B64C9/20 , B64C3/50 , B64C9/16 , B64C23/06 , B64C23/065 , B64C2230/14 , Y02T50/164 , Y02T50/44
摘要： A flap of an aircraft includes a flap body that is provided deployably with respect to a main wing, an inclined portion that protrudes from an upper surface of a tip part on at least an outboard side in a span direction of the flap body and is inclined with respect to an aircraft axis direction, and a protruding portion that smoothly protrudes from a lower surface of the tip part on at least the outboard side. A rear end of the inclined portion is located closer to a side end edge of the tip part in the span direction of the flap body than a virtual line that passes through a front end of the inclined portion and is parallel to the aircraft axis direction.

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

US09676471B2 Compliant structure design for varying surface contours 有权
公开(公告)号：US09676471B2
公开(公告)日：2017-06-13
申请号：US14469385
申请日：2014-08-26
申请人： FLEXSYS, INC.
发明人： Joel A. Hetrick , Sridhar Kota , Gregory F. Ervin
IPC分类号： B64C3/52 , B64C3/48 , B64C27/72 , B64C3/50 , B64C27/473 , B64C9/16 , B64C9/22
CPC分类号： B64C3/52 , B64C3/48 , B64C3/50 , B64C9/16 , B64C9/22 , B64C27/473 , B64C27/72 , Y02T50/34 , Y10T74/18056 , Y10T74/18288
摘要： An edge morphing arrangement for an airfoil having upper and lower control surfaces is provided with an elongated edge portion that overlies the edge of the airfoil, the edge portion having a surface element having first and second edges that communicate with, and form extensions of, respective ones of the upper and lower control surfaces of the elongated airfoil. The surface elements are formed of deformable compliant material that extends cross-sectionally from the first surface element edge to an apex of the edge portion, and to the second surface element edge. There is additionally provided a driving link having first and second driving link ends, the first driving link end being coupled to the interior of one of the first and second rib portions. The second end is arranged to receive a morphing force, and the rib element is deformed in response to the morphing force.

4. 发明申请

US20170015407A1 LEADING EDGE FLAP 审中-公开
标题翻译：领先翼片
公开(公告)号：US20170015407A1
公开(公告)日：2017-01-19
申请号：US15212456
申请日：2016-07-18
申请人： Theodore M. Garver
发明人： Theodore M. Garver
IPC分类号： B64C23/08 , F03D1/06 , F03D7/02 , B64C3/50
CPC分类号： B64C23/08 , B64C3/50 , B64C23/02 , F03D1/0675 , F03D7/0232 , F05B2240/31 , Y02E10/721 , Y02T50/14
摘要： A fluid interface device, such as an airfoil assembly, can include a device structure and at least one movable band oriented such that the band moves in a direction of fluid flow. The at least one movable band can be supported on the device structure such that an outer surface of the movable band is exposed along the device structure and is capable of movement relative thereto such that a relative velocity can be maintained between the outer surface and the device structure. The fluid interface device can also include an edge extension disposed along the leading edge of the device structure. An airplane, a wind turbine and a method are also included.
摘要翻译：诸如翼型组件的流体界面装置可以包括装置结构和至少一个可移动的带定向成使得带沿流体流动的方向移动。所述至少一个可移动带可以被支撑在所述装置结构上，使得所述可移动带的外表面沿着所述装置结构暴露并且能够相对于其移动，使得可以在所述外表面和所述装置之间保持相对速度结构体。流体界面装置还可以包括沿着装置结构的前缘设置的边缘延伸部。还包括飞机，风力发电机和方法。

5. 发明授权

US09463869B2 Slidable divergent trailing edge device 有权
标题翻译：可拖动的发散后缘装置
公开(公告)号：US09463869B2
公开(公告)日：2016-10-11
申请号：US14298105
申请日：2014-06-06
申请人： The Boeing Company
发明人： Flint M. Jamison , Stephen R. Amorosi , Michael K. Klein
IPC分类号： B64C3/50 , B64C13/24 , B64C3/38 , B64C3/28 , B64C3/14
CPC分类号： B64C13/24 , B64C3/28 , B64C3/38 , B64C3/50 , B64C9/02 , B64C9/16 , B64C2003/147 , Y02T50/12 , Y02T50/14 , Y02T50/32 , Y02T50/44
摘要： A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.
摘要翻译：机翼包括后缘，以及沿收起位置和完全展开位置之间的后缘的后表面可滑动的发散后缘装置。后缘装置在收起时完全位于后缘内，并且当展开时它增加了机翼的牵引力。

6. 发明授权

US09242718B2 Seal assembly 有权
标题翻译：密封组件
公开(公告)号：US09242718B2
公开(公告)日：2016-01-26
申请号：US13883181
申请日：2011-11-07
申请人： James Wilson , Alan Quayle , Paul Hadley
发明人： James Wilson , Alan Quayle , Paul Hadley
IPC分类号： B64C3/50 , B64C7/00 , B64C9/02 , B64C9/22 , B29C70/26
CPC分类号： B64C7/00 , B29C70/26 , B64C3/50 , B64C9/02 , B64C9/22 , Y02T50/43
摘要： A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.
摘要翻译：一种用于封闭结构的空气动力学表面中的孔的密封组件，所述密封组件包括：用于附接到所述结构的轨道; 以及可伸缩密封件，其包括柔性基板和连接到所述基板的多个杆，其中，所述杆中的至少一个安装成用于沿着所述轨道运动，并且所述密封件可以在延伸位置和缩回位置之间移动，沿着轨道的至少一个杆，伴随着密封基底的折叠/展开，并且其中密封件被偏压到其延伸位置。

7. 发明授权

US09227722B2 Flap support 有权
标题翻译：襟翼支撑
公开(公告)号：US09227722B2
公开(公告)日：2016-01-05
申请号：US13633976
申请日：2012-10-03
申请人： AIRBUS OPERATIONS LIMITED
发明人： Mochamad-Agoes Soenarjo
IPC分类号： B64C3/50 , B64C9/16
CPC分类号： B64C9/18 , B64C3/50 , B64C9/02 , B64C9/16 , Y02T50/32 , Y02T50/44
摘要： A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.
摘要翻译：一种用于具有后缘翼片的飞机机翼的翼片支撑结构，所述翼片支撑结构包括：翼片支撑梁，包括气动整流罩; 以及包括通用支撑结构的驱动单元，所述通用支撑结构可旋转地接收连接到用于移动所述后缘挡板的驱动臂的驱动轴，其中所述通用支撑结构还形成所述翼片支撑梁的一部分并且支撑所述空气动力学整流罩。

8. 发明申请

US20150353188A1 SLIDABLE DIVERGENT TRAILING EDGE DEVICE 有权
标题翻译：可滑动的多边形边缘装置
公开(公告)号：US20150353188A1
公开(公告)日：2015-12-10
申请号：US14298105
申请日：2014-06-06
申请人： THE BOEING COMPANY
发明人： Flint M. Jamison , Stephen R. Amorosi , Michael K. Klein
IPC分类号： B64C13/24 , B64C3/50 , B64C3/28
CPC分类号： B64C13/24 , B64C3/28 , B64C3/38 , B64C3/50 , B64C9/02 , B64C9/16 , B64C2003/147 , Y02T50/12 , Y02T50/14 , Y02T50/32 , Y02T50/44
摘要： A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.
摘要翻译：机翼包括后缘，以及沿收起位置和完全展开位置之间的后缘的后表面可滑动的发散后缘装置。后缘装置在收起时完全位于后缘内，并且当展开时它增加了机翼的牵引力。

9. 发明授权

US09180962B2 Leading edge variable camber system and method 有权
标题翻译：前缘可变外倾系统及方法
公开(公告)号：US09180962B2
公开(公告)日：2015-11-10
申请号：US14034987
申请日：2013-09-24
申请人： The Boeing Company
发明人： Matthew A. Moser , Mark J. Gardner , Michael R. Finn , Mark S. Good , Adam P. Malachowski , Monica E. Thommen , Stephen R. Amorosi , Dan Onu
IPC分类号： B64C3/50 , B64C9/24 , B64C13/50 , B64C13/00 , B64C13/16
CPC分类号： B64C3/50 , B64C9/06 , B64C9/12 , B64C9/24 , B64C13/00 , B64C13/16 , B64C13/26 , B64C13/503 , Y02T50/32 , Y02T50/44
摘要： A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.
摘要翻译：用于改变飞机机翼的机翼弯曲的系统可以包括联接到机翼的前缘装置。前缘装置可以被构造成相对于前缘装置的缩回位置沿向上的方向和向下的方向被致动。

10. 发明申请

US20140166818A1 SLAT, WING OF AIRCRAFT, FLIGHT CONTROL SURFACE OF AIRCRAFT, AND AIRCRAFT 有权
标题翻译：飞机飞行员，飞机飞行控制面和飞机
公开(公告)号：US20140166818A1
公开(公告)日：2014-06-19
申请号：US14126291
申请日：2012-08-21
申请人： Hideaki Tanaka
发明人： Hideaki Tanaka
IPC分类号： B64C3/50
CPC分类号： B64C3/18 , B64C3/185 , B64C3/187 , B64C3/50 , B64C9/22 , Y02T50/44
摘要： A flight control surface such as a slat capable of keeping and achieving a minimum basic functions even when it is damaged by collisions of birds or the like, and a wing using the same are provided. Both ends of one wire cable 15 or more are fixed to paired ribs 10A and 10B provided in a short direction of the slat. This wire cable 15 is placed so as to pass through a through-hole 13 formed in each of the ribs 10 positioned between the paired ribs 10A and 10B. Even if birds or the like collide with slat 3 at the time of a flight of the aircraft to damage and deform not only a skin 4 of the slat 3 but also any rib 10, the wire cable 15 between the paired ribs 10A and 10B prevents the slat 3 from being broken into pieces.
摘要翻译：提供了能够保持并实现最小基本功能的飞行控制表面，即使是由于鸟类等的碰撞而损坏的飞行控制表面，以及使用其的机翼。一根线缆15以上的两端固定在沿着板条的短方向设置的成对的肋10A，10B。这种线缆15被放置成穿过形成在位于成对肋10A和10B之间的每个肋10中的通孔13。即使在飞行器飞行时鸟类等与板条3碰撞，不但损坏并且不仅使板条3的皮肤4变形，而且使肋条10变形，则成对的肋10A和10B之间的线缆15防止板条3被破碎成碎片。

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