| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | STRUCTURE FOR AIRCRAFT, METHOD OF MANUFACTURING STRUCTURE FOR AIRCRAFT AND METHOD OF MAKING DESIGN INFORMATION OF STRUCTURE FOR AIRCRAFT | US15048671 | 2016-02-19 | US20160244182A1 | 2016-08-25 | Ai KAWASHIMA; Kousaburou AKIBA; Yasueki KOMABA; Yoshiaki HIROMATSU; Takayuki NISHI; Hiroyasu FUJITA |
| According to one implementation, a structure for an aircraft includes a first structural member, a second structural member coupled to the first structural member, a fastener and a conductive object. The fastener couples the first structural member to the second structural member. The fastener is inserted into an insertion hole formed in a portion where the first structural member is overlapped with the second structural member. The fastener is in electrically non-contact with the first and second structural members in the insertion hole. The conductive object is embedded inside at least either one of the first and second structural members. The conductive object prevents a spark between the fastener and each of the first and second structural members by forming a current pathway that leads current, flowing inside the at least either one of the first and second structural members, to the other structural member. | ||||||
| 162 | Electrical raft with map | US13716516 | 2012-12-17 | US09426844B2 | 2016-08-23 | Paul Broughton; Richard Peace; Gary Alan Skinner; Robin Charles Kennea; Michael Christopher Willmot; Philip Summerfield |
| An electrical raft 200 is provided that has electrical conductors 252 embedded in a rigid material 220. The electrical raft 200 may have other embedded components, such as embedded fluid pipes 210. The electrical raft 200 is provided with a raft map 400 that indicates the location and/or path of components embedded in the electrical raft 200. The raft map 400 can be used to identify the positions of the embedded components, and may also be provided with active elements, such as LEDs, which may be used to indicate an operating state of the systems/components embedded in the electrical raft 200. The raft map 400 may be useful in assembly, repair and fault diagnosis, for example. | ||||||
| 163 | Device for preventing the passage of gases and/or fluids from a wingbox into a fuselage of an aircraft | US13264802 | 2010-04-15 | US09415879B2 | 2016-08-16 | Christos Bogiatzis |
| A device is disclosed for preventing gases and/or fluids emanating from a wing box of an aircraft from passing to an aircraft fuselage cell situated underneath it. The device comprises at least one sheet-like material positioned below or above the wing box. The sheet-like material is preferably made of a woven fabric comprising aramid fibers or the like, which fabric in order to ensure the required seal vis-à-vis liquid and/or gaseous substances, in particular vis-à-vis fuels, has been impregnated or soaked with an epichlorohydrin elastomer compound or with some other elastomer, for example a rubber compound or the like. | ||||||
| 164 | DOOR FOR CLOSING OPENING IN STRUCTURE AND AIRCRAFT | US14977121 | 2015-12-21 | US20160176496A1 | 2016-06-23 | Zengli Han; Haifeng Chen; Ming Luo; Angel Postigo-Rodriguez; Daniel De-La-Sen-Perez; Laure Partouche |
| The present invention relates to a door for closing an opening in a structure, including: a body arranged to be capable of abutting against a first side of the opening; at least one clamping member configured to be capable of abutting against an opposite second side of the opening; and a fastener arranged to fasten or release the clamping member relative to the body. The clamping member is moveable relative to the body between a first position where the clamping member abuts against the second side of the opening so as to clamp the structure between the body and the clamping member and a second position where the clamping member allows the door to be opened. The present invention further relates to an aircraft including the above door. | ||||||
| 165 | METHODS, SYSTEMS, AND DEVICES FOR RADIO-FREQUENCY ASSISTED REMOVAL OF SEALANT | US15012572 | 2016-02-01 | US20160151944A1 | 2016-06-02 | Darrin M. Hansen; Carissa Ann Pajel |
| Cured flexible sealant may be removed from a substrate if the cured flexible sealant includes within its volume a susceptor such as metal susceptor particles. Removal proceeds by exposing the sealant with the susceptor to radio-frequency radiation sufficient to cause dielectric heating in the susceptor. The consequent heating in the cured sealant reduces the bond strength of the cured sealant. The reduced bond-strength sealant may be removed by physical methods, such as scraping etc., much more easily than the original (unexposed) cured sealant. Also disclosed are sealant compositions with susceptor, susceptor tools to introduce susceptor into cured sealant, and handheld radio-frequency heaters to apply radio-frequency radiation to cured sealant. | ||||||
| 166 | AIRCRAFT WITH A WING TIP COMPRISING A FUEL POD | US14933321 | 2015-11-05 | US20160130012A1 | 2016-05-12 | Roger LAGUIA-BARNOLA; Matthew Noel ORCHARD; Norman WOOD |
| An aircraft comprising a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations. | ||||||
| 167 | Methods, systems, and devices for radio-frequency assisted removal of sealant | US14282743 | 2014-05-20 | US09283598B2 | 2016-03-15 | Darrin M. Hansen; Carissa Ann Pajel |
| Cured sealant may be removed from a substrate if the cured sealant includes a susceptor within its volume. Removal proceeds by exposing the sealant with the susceptor to radio-frequency radiation sufficient to cause dielectric heating in the susceptor and the consequent heating in the cured sealant reduces the bond strength of the cured sealant. The reduced bond-strength sealant may be removed by physical methods, such as scraping etc., much more easily than the original (unexposed) cured sealant. Also disclosed are sealant compositions with susceptor, susceptor tools to introduce susceptor into cured sealant, and handheld radio-frequency heaters to apply radio-frequency radiation to cured sealant. | ||||||
| 168 | FUEL TANK, MAIN WINGS, AIRCRAFT FUSELAGE, AIRCRAFT, AND MOVING BODY | US14780156 | 2014-01-28 | US20160052638A1 | 2016-02-25 | Nobuyuki KAMIHARA; Kazuaki KISHIMOTO; Toshio ABE; Yuichiro KAMINO |
| A fuel tank including a structural member that uses carbon-fiber-reinforced plastic including a reinforcing material containing carbon fiber and a matrix containing a plastic, the structural member being formed by laminating a conductive sheet between prepregs of the carbon-fiber-reinforced plastic, and being formed with a fastening hole in which a bolt is fastened, and a cut surface of the structural member formed by cutting the structural member being exposed within an internal area in which fuel is stored. | ||||||
| 169 | Electrical structure having a grounding plane | US13716300 | 2012-12-17 | US09204497B2 | 2015-12-01 | Michael Christopher Willmot; John Philip Richardson; Jason Watkiss; Paul Broughton; Richard Peace; Gary Alan Skinner; Robin Charles Kennea |
| An electrical assembly including electrical raft having electrical conductors embedded in a rigid material is provided. The electrical assembly has an electrically conductive screen layer. The electrically conductive screen layer provides electromagnetic protection to the electrical conductors. The electrically conductive screen layer is electrically connected to a mounting fixture, which in turn may be electrically connected to an apparatus on which the electrical assembly may be mounted. The electrical raft is used to transport electrical signals (which may be, for example power and/or control signals), for example around a gas turbine engine. | ||||||
| 170 | VENT STRINGER FITTING | US14249735 | 2014-04-10 | US20150336656A1 | 2015-11-26 | Corey A. Rolfes |
| A fitting for a vent stringer of a type having an open end and an outer edge defining the open end. The fitting may include a fitting body receivable along the open end of the vent stringer, the fitting body having a groove that generally corresponds with the outer edge of the vent stringer, the groove of the fitting body shaped to receive the outer edge of the vent stringer to create a tongue and groove joint with the outer edge; and a connection between the fitting and the stringer to prevent slidable movement of the fitting relative to the stringer. | ||||||
| 171 | Fluid Dynamic Vent Dam | US14634818 | 2015-02-28 | US20150239570A1 | 2015-08-27 | Kenneth L. Brook; Bonnie A. Keefe |
| The disclosure provides in one embodiment for a vent dam for use in a vent stringer in a fuel vent system. The vent dam is configured to mount to and within the vent stringer The vent dam has a contoured guiding surface for guiding fuel flow into and out of an interior of the vent stringer, wherein the vent dam, the vent stringer, and a tube attached to the vent stringer are in fluid communication with one or more fuel tanks. The vent dam further has one or more side flanges extending from the contoured guiding surface for providing attachment of the vent dam to one or more interior portions of the vent stringer, wherein the contoured guiding surface and the one or more side flanges are formed as one piece. | ||||||
| 172 | Continuously Curved Spar and Method of Manufacturing | US13855705 | 2013-04-02 | US20150203187A1 | 2015-07-23 | Michael Patterson Johnson; James F. Ackermann; Christopher C. Eastland; Dyrk L. Daniels; Steven J. Burpo |
| There is provided in an embodiment an airfoil. The airfoil has one or more fuel containment regions disposed in the airfoil and one or more continuously curved spars extending from a root end of the airfoil toward a tip end of the airfoil. At least one continuously curved spar has a unitary configuration, has one or more continuous curves along the continuously curved spar, and either has a portion forming a structural wall of at least one of the one or more fuel containment regions, or, is internal to the one or more fuel containment regions. | ||||||
| 173 | Composite material structure and aircraft wing provided therewith | US13881521 | 2012-01-26 | US09027881B2 | 2015-05-12 | Yuya Tanaka; Hideyuki Suzuki; Yutaka Kanayama; Kazuki Sato; Masatake Hatano; Satoru Saito; Akihisa Watanabe; Ryo Abe |
| Provided is a composite material structure enabled to be reduced in weight. The composite material structure includes a front section (3a) extending in one direction and formed as a composite material made of fiber reinforced plastics, a rear section (3c) separated from the front section (3a) by a predetermined space, extending in the one direction, and formed as a composite material made of fiber reinforced plastics, and access panels (5) provided between the front section (3a) and the rear section (3c) and having a dimension in the one direction shorter than the front section (3a) and the rear section (3c). The access panels (5) are fixed to the front section (3a) and the rear section (3c) in an orthogonal direction substantially orthogonal to the one direction and set to be displaceable in the one direction and are removable. | ||||||
| 174 | Aircraft fuel tank vent | US13216289 | 2011-08-24 | US08936218B2 | 2015-01-20 | Joseph K-W Lam; Franklin Tichborne; Simon Masters; David Parmenter |
| An aircraft having a dihedral wing configuration with a wing fuel tank and a vent system for ventilating the fuel tank, the vent system including a combined vent-surge tank disposed inboard of at least part of the wing fuel tank, a vent fluidically connecting the vent-surge tank to ambient, and a vent line fluidically connecting the upper part of the fuel tank to the combined vent-surge tank, wherein the vent line has its lowest point at the combined vent-surge tank. | ||||||
| 175 | COMPOSITE STRUCTURE, AIRCRAFT WING AND AIRCRAFT FUSELAGE INCLUDING COMPOSITE STRUCTURE, AND METHOD OF MANUFACTURING COMPOSITE STRUCTURE | US14373513 | 2013-02-14 | US20140377500A1 | 2014-12-25 | Masahiro Kashiwagi; Yoshinori Nonaka; Toshio Abe |
| A composite structure (3) formed of a composite member which extends in one direction, includes holes (5), and is made of fiber reinforced plastics. A tensile load and/or a compressive load are applied to the composite structure (3) in the one direction. Tensile stiffness and/or compression stiffness of peripheral areas (3a) of the holes (5) is lower than tensile stiffness and/or compression stiffness of the other area (3b), which surrounds the peripheral areas (3a), in the one direction, and the width of the peripheral area (3a) in a direction orthogonal to the one direction is set to 1.1 times or less of the diameter of the hole (5) in the direction orthogonal to the one direction. | ||||||
| 176 | VENT MEMBER, WING PANEL, AND MAIN WING FOR AIRCRAFT | US14353951 | 2012-11-27 | US20140299713A1 | 2014-10-09 | Ushio Komoda; Hideto Motohashi |
| An opening portion of a vent member is prevented from being blocked, and thus ventilation is reliably performed. A plurality of opening portions (40A, 40B) are formed in a single vent stringer (20), and thus even in a case where one of the opening portions (40A, 40B) is blocked, ventilation is secured by the other opening portion. At this time, since the opening portions (40A, 40B) are formed in surfaces different from each other in the vent stringer (20), a possibility that both the opening portions (40A, 40B) may be simultaneously blocked is less. | ||||||
| 177 | Closing member for opening | US13577733 | 2011-02-09 | US08840068B2 | 2014-09-23 | Hideto Motohashi |
| An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. In a door body 30, an outer surface 31a of a plate part 31 is formed by a composite material layer 60, and a side of an inner surface 31b and a flange part 32 are formed by a metallic material layer 61. The door body 30, a clamp ring 40, and an opening 12 of a wing panel 11 are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12. | ||||||
| 178 | Aircraft fuel tank | US13131063 | 2009-06-24 | US08678320B2 | 2014-03-25 | Hiroaki Yamaguchi; Yuichiro Kamino; Tooru Hashigami; Kazuyuki Oguri |
| An aircraft fuel tank that is capable of suppressing the occurrence of sparks on a pipe caused by a lightning current through the pipe during a lightning strike, and also suppressing static electricity charging of a pipe caused by flow electrification generated by the fuel. An aircraft fuel tank (1) in which a storage section is formed using a conductive upper skin (5), a conductive lower skin (7) and conductive spars (9), the tank comprising: pipes inside the tank, such as a refuel pipe (17), an engine feed pipe (19) and an inert gas pipe (21), which are disposed inside the storage section and are earthed (27) at a plurality of locations, and pipe outer surface layers (31) having semiconductor properties that are formed in an integrated manner on the outer surfaces of the pipes inside the tank such as the replenishing pipe (17), the supply pipe (19) and the gas pipe (21). | ||||||
| 179 | Wing structure | US13263215 | 2010-03-31 | US08616499B2 | 2013-12-31 | Michael Tucker; Timothy Sanderson |
| A wing structure is provided, wherein the wing structure comprises; an upper covering, a lower covering, and a spar, the spar comprising; a spar web, an upper spar cap attached to the upper covering, and a lower spar cap attached to the lower covering, the wing structure also comprising a face spaced apart from the spar web extending between the upper and lower spar caps. The wing structure is arranged to contain fuel in a fuel containment area between the upper and lower coverings on one side of the spar web. The upper and lower spar caps extend from the spar web only on the other side of the spar web to the fuel containment area. | ||||||
| 180 | STRINGER, AIRCRAFT WING PANEL ASSEMBLY, AND METHOD OF FORMING THEREOF | US13982091 | 2012-01-26 | US20130316147A1 | 2013-11-28 | Paul Douglas; David Patrick Stephane Petitt |
| Embodiments of the invention relate to a stringer (108) adapted to transport fluid in an aircraft wing (100). For example, the stringer may be adapted to provide venting to one or more fuel tanks (111) in the aircraft wing, or may be adapted to provide fuel to the one or more fuel tanks. To perform this function, the stringer comprises a duct member (120) providing a duct and a structural member (121) providing an attachment surface for attachment of the stringer to a wing panel (112). Typically, the stringer is formed from a composite material such as carbon fibre reinforced plastic. A method of manufacturing the stringer is also disclosed. | ||||||
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