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1. 发明授权

US11958599B2 Supporting structure with passively adaptable profile 有权
公开(公告)号：US11958599B2
公开(公告)日：2024-04-16
申请号：US17427675
申请日：2020-02-03
申请人： Guilhem Colombiès
发明人： Guilhem Colombiès
IPC分类号： B64C3/44 , B64C3/18 , B64C3/30 , B64C3/52
CPC分类号： B64C3/44 , B64C3/182 , B64C3/30 , B64C3/52 , B64C2003/445
摘要： The invention relates to a supporting structure (46) which is positioned in a fluid flow (44) and characterised in that it is configured to be elastically deformed, on at least one portion of the supporting structure (46), between a first idle state in the absence of external stress and a second deformed state in the presence of external stresses caused by the fluid flow (44) due to a change in the orientation of the supporting structure (46) and/or the fluid flow (44). The invention also relates to an aircraft comprising at least one such supporting structure (46).

2. 发明授权

US11491763B2 Structure adapted to traverse a fluid environment and method of retrofitting structure adapted to traverse a fluid environment 有权
公开(公告)号：US11491763B2
公开(公告)日：2022-11-08
申请号：US16924957
申请日：2020-07-09
申请人： BIOMERENEWABLES INC.
发明人： Ryan Church
IPC分类号： F03D1/06 , B32B9/02 , C12N11/00 , F03D13/10 , B64C3/00 , F01D5/14 , F01D21/00 , C12N1/16 , C12N9/80 , B64C3/46 , B64C3/30 , B64D15/16 , F03D80/40 , B33Y70/00 , B33Y10/00 , C12P1/00
摘要： A structure adapted to traverse a fluid environment exerting an ambient fluid pressure is provided. The structure includes an elongate body extending from a root to a wingtip and encapsulating at least one interior volume containing an interior fluid exerting an interior fluid pressure that is different from the ambient fluid pressure. A method of retrofitting a structure adapted to traverse a fluid environment exerting an ambient fluid pressure, the structure comprising an elongate body extending from a root to a wingtip and having at least one interior volume is also provided. The method includes sealing the elongate body to encapsulate the at least one interior volume containing an interior fluid; associating at least one valve with the at least one interior volume; and modifying interior fluid content via the at least one valve to produce an interior fluid pressure that is different from the ambient fluid pressure.

3. 发明授权

US10106243B2 Deployable wing for an aircraft 有权
公开(公告)号：US10106243B2
公开(公告)日：2018-10-23
申请号：US15096998
申请日：2016-04-12
申请人： Thomas E. Keavney , John C. Rufino
发明人： Thomas E. Keavney , John C. Rufino
IPC分类号： B64C3/30 , B64C3/54
摘要： An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space includes an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space. A plurality of reels is secured to the aircraft. A plurality of suspension lines connects the wing to the reels. At least one reel is operable to unwind a corresponding suspension line to allow the wing to inflate to the deployed condition exclusively by ram air generated by movement of the aircraft. A method of use for a deployable wing is also provided.

4. 发明授权

US09988138B2 Inflatable airfoil system having reduced radar observability 有权
公开(公告)号：US09988138B2
公开(公告)日：2018-06-05
申请号：US14250385
申请日：2014-04-11
申请人： The Boeing Company
发明人： Kevin Reed Lutke , Aaron Jonathan Kutzmann
IPC分类号： B64C3/30 , B64C39/02
CPC分类号： B64C3/30 , B64C39/024 , B64C2201/021 , B64C2201/102 , B64C2201/105
摘要： A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

5. 发明申请

US20170291683A1 DEPLOYABLE WING FOR AN AIRCRAFT 审中-公开
公开(公告)号：US20170291683A1
公开(公告)日：2017-10-12
申请号：US15096998
申请日：2016-04-12
申请人： THOMAS E. KEAVNEY , JOHN C. RUFINO
发明人： THOMAS E. KEAVNEY , JOHN C. RUFINO
IPC分类号： B64C3/30 , B64C3/54
CPC分类号： B64C3/30 , B64C3/54 , B64C2003/543 , B64D17/80
摘要： An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space includes an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space. A plurality of reels is secured to the aircraft. A plurality of suspension lines connects the wing to the reels. At least one reel is operable to unwind a corresponding suspension line to allow the wing to inflate to the deployed condition exclusively by ram air generated by movement of the aircraft. A method of use for a deployable wing is also provided.

6. 发明申请

US20170106969A1 LEADING EDGE FOR AN AIRFOIL 审中-公开
公开(公告)号：US20170106969A1
公开(公告)日：2017-04-20
申请号：US15295099
申请日：2016-10-17
申请人： Airbus Operations S.L.
发明人： Fernando Pereira Mosqueira , Jesús Javier VÁZQUEZ CASTRO
IPC分类号： B64C3/30 , B64C3/26 , B64C3/28
CPC分类号： B64C3/30 , B64C3/26 , B64C3/28 , B64C2003/146 , Y02T50/12
摘要： A leading edge for an airfoil comprising a torsion box, the leading edge comprising a leading plate and a first inflatable element suitable for being filled with air. The leading plate comprises a convex side and a concave side. The first inflatable element is in contact with at least part of the concave side, thus reinforcing the leading plate. An airfoil comprising such a leading edge is also provided.

7. 发明申请

US20160068251A1 INFLATABLE AND RIGIDIZABLE SUPPORT ELEMENT 有权
标题翻译：可充气和可靠的支持元素
公开(公告)号：US20160068251A1
公开(公告)日：2016-03-10
申请号：US14942174
申请日：2015-11-16
申请人： TUFTS UNIVERSITY
发明人： Alfram V. Bright , Richard Wlezien
IPC分类号： B64C3/30 , F03D11/04 , E04H12/00 , D06M10/10 , D06M15/327 , H05G2/00 , B64C3/56 , D06M10/00
CPC分类号： B64C3/30 , B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/102 , B64C2201/127 , D06M10/001 , D06M10/10 , D06M15/327 , E04H12/00 , F03D13/20 , H05G2/00 , Y02E10/728
摘要： The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements which find use in rapidly deploying and supporting the wing of an aerial vehicle.
摘要翻译：本发明提供了新颖的可膨胀和可固化的支撑元件，及其制造和使用方法。特别地，本发明提供了充气和可固化的支撑元件，其可用于快速展开和支撑飞行器的机翼。

8. 发明授权

US09216813B2 Inflatable and rigidizable support element 有权
标题翻译：充气和可固化的支撑元件
公开(公告)号：US09216813B2
公开(公告)日：2015-12-22
申请号：US13516453
申请日：2010-12-17
申请人： Alfram V. Bright , Richard Wlezien
发明人： Alfram V. Bright , Richard Wlezien
IPC分类号： B64C3/30 , B64C3/56 , B64C39/02
CPC分类号： B64C3/30 , B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/102 , B64C2201/127 , D06M10/001 , D06M10/10 , D06M15/327 , E04H12/00 , F03D13/20 , H05G2/00 , Y02E10/728
摘要： The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements rapidly inflated and rigidized using an acrylic adhesive and UV light generated by combustion, which find use, for example, in rapidly deploying and supporting the wing of an aerial vehicle and wind turbine towers.
摘要翻译：本发明提供了新颖的可膨胀和可固化的支撑元件，及其制造和使用方法。特别地，本发明提供了使用丙烯酸粘合剂和由燃烧产生的UV光快速膨胀和刚性化的可膨胀和可固化的支撑元件，其可用于例如快速部署和支撑飞行器和风力涡轮机塔架的机翼。

9. 发明授权

US09162761B2 Partially-inflated rigid-structure glider 有权
标题翻译：部分充气刚性结构滑翔机
公开(公告)号：US09162761B2
公开(公告)日：2015-10-20
申请号：US13925797
申请日：2013-06-24
申请人： Christopher Paul Farbolin
发明人： Christopher Paul Farbolin
IPC分类号： B64C31/02 , B64C1/34 , B64C3/30 , B64C31/028
CPC分类号： B64C31/02 , B64C1/34 , B64C3/30 , B64C31/028 , B64D2211/00
摘要： A partially-inflated rigid-structure glider is a portable or collapsible gliding apparatus that a user can transport in a carrying case. The gliding apparatus includes a rigid yet collapsible frame, tension membranes over both on the wings and tail, and inflatable bladder, a pair of drogue brakes, and a left and right steering mechanism. The pair of drogue brakes is located on opposing sides of the gliding apparatus and create drag on its respective side in order to turn the gliding apparatus either left or right. The user can activate either drogue brake with the left and right steering mechanism, which are control lines attached to each drogue brake. The tension membranes are fitted over the frame so that the gliding apparatus has an airfoil shape in order to create lift with the wings and tail while the gliding apparatus is in flight.
摘要翻译：部分充气的刚性结构滑翔机是用户可以在手提箱中运输的便携式或可折叠的滑翔装置。滑翔装置包括刚性且可折叠的框架，在翼和尾部上方均设有张力膜，以及可膨胀的气囊，一对锥形制动器以及左右转向机构。一对锥形制动器位于滑翔装置的相对侧上并且在其相应侧上产生拖动以便使滑翔装置左或右转动。使用者可以用左右转向机构来启动两个制动器，左右转向机构是连接到每个棘轮式制动器的控制线。张紧膜安装在框架上，使得滑翔装置具有翼型形状，以便在滑翔装置处于飞行状态时产生具有翼和尾部的升力。

10. 发明申请

US20090224108A1 PNEUMATIC CONTROL SYSTEM FOR AERODYNAMIC SURFACES 有权
标题翻译：气动表面气动控制系统
公开(公告)号：US20090224108A1
公开(公告)日：2009-09-10
申请号：US12042443
申请日：2008-03-05
申请人： Kevin R. Lutke , Aaron J. Kutzmann
发明人： Kevin R. Lutke , Aaron J. Kutzmann
IPC分类号： B64C3/30 , B64C3/44
CPC分类号： B64C3/46
摘要： A flight control system for an airfoil comprises a control surface, a chamber connecting the control surface to the airfoil, and a pneumatic mechanism fluidly connected to the chamber. The chamber may be comprised of at least two cells that may be fluidly separated by a membrane. The pneumatic mechanism is configured to provide differential pressure to the cells in order to alternately increase volume/pressure of the cells to cause deflection of the control surface. The cells may have a stretchable outer surface to allow for changes in the length of the outer surface in response to inflation/deflation of the cells. The outer surface of the cells may be substantially continuous with outer mold lines of the airfoil and of the control surface.
摘要翻译：用于翼型的飞行控制系统包括控制表面，将控制表面连接到翼型件的腔室以及与腔室流体连接的气动机构。腔室可以由至少两个细胞构成，这些细胞可被膜流体地分离。气动机构构造成为细胞提供差压以便交替地增加细胞的体积/压力以引起控制表面的偏转。细胞可以具有可拉伸的外表面，以允许响应于细胞的充气/放气而改变外表面的长度。电池的外表面可以与翼型件和控制表面的外部模具线基本上连续。

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