| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Fluid dynamic vent dam | US12652020 | 2010-01-04 | US09010689B1 | 2015-04-21 | Kenneth L. Brook; Bonnie 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 comprises a contoured guiding surface for guiding fluid flow in a vent stringer. The vent dam further comprises one or more side flanges extending from the contoured guiding surface for providing attachment of the vent dam within the vent stringer. | ||||||
| 102 | AIRCRAFT FUEL TANK INERTING SYSTEM | US14398484 | 2013-04-29 | US20150096984A1 | 2015-04-09 | Dominic Ashton; John Wood; John Foster |
| An aircraft fuel tank system includes at least one fuel tank having a plurality of interconnected bays and a vent arranged so as to allow an inward venting of atmospheric air. The system is arranged so as to direct the inwardly vented air along a vent duct. The vent duct is arranged so as to convey the inwardly vented air to substantially each one of the interconnected bays. | ||||||
| 103 | FUEL TANK, MAIN WING, AIRCRAFT FUSELAGE, AIRCRAFT, AND MOBILE BODY | US14382961 | 2013-03-15 | US20150041592A1 | 2015-02-12 | Nobuyuki Kamihara; Masayuki Yamashita; Toshio Abe; Yuichiro Kamino |
| A fuel tank in which it is possible to reduce working hours or cost in a manufacturing process and prevent an increase in weight in, a main wing, an aircraft fuselage, an aircraft, and a mobile body. The fuel tank is provided with a structural member using carbon fiber reinforced plastic in which a reinforcing material includes carbon fibers and a matrix includes plastic, wherein the matrix has electrical conductivity applied thereto. Furthermore, a cut surface of the structural member, which is formed by cutting the structural member, may be exposed to the inside in which fuel is accommodated, of a fuel tank. | ||||||
| 104 | OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT | US14136725 | 2013-12-20 | US20140191085A1 | 2014-07-10 | Marcos Alazraki; Jose Sanz Torrijos |
| An outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft are provided. In one example, an outer fuel tank access cover (FTAC) (4) of an aircraft includes an inner surface and an outer surface. The outer FTAC is to cover the outer opening of a void area of a manhole for accessing the interior of a wing of an aircraft in which the interior of the wing comprises a fuel tank. The outer FTAC comprises absorption means adapted for absorbing the impact energy due to an object impacting against the outer FTAC. | ||||||
| 105 | COUPLING STRUCTURE FOR AIRFRAME COMPONENTS | US14102890 | 2013-12-11 | US20140096991A1 | 2014-04-10 | Koji KAWAHARA; Hideo YAMAKOSHI; Yuichiro KAMINO; Atsuhiro IYOMASA; Toru HASHIGAMI |
| Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved. | ||||||
| 106 | Closing member for opening | US13511496 | 2011-05-11 | US08684216B2 | 2014-04-01 | Kazuki Tachibana |
| An object is to provide a closing member for an opening, the closing member capable of more reliably maintaining a lightning-protective function. In addition to a first insulator 63, a second insulator 65 is provided between a door body 30 and a wing inner surface 11b around an opening 12. When the first insulator 63 falls off, the second insulator 65 becomes interposed between an inner peripheral planar part 64 and the wing inner surface 11b. With the first insulator 63 being tightly interposed between an outer peripheral planar part 62 and the wing inner surface 11b, the second insulator 65 faces the wing inner surface 11b with a predetermined clearance C therebetween. The outer peripheral planar part 62 is formed at a position further away from the wing inner surface 11b than an apical surface 65a of the second insulator 65 mounted on the inner peripheral planar part 64. | ||||||
| 107 | Coupling structure for airframe components | US13418865 | 2012-03-13 | US08634177B2 | 2014-01-21 | Koji Kawahara; Hideo Yamakoshi; Yuichiro Kamino; Atsuhiro Iyomasa; Toru Hashigami |
| Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved. | ||||||
| 108 | Portable sealant dispense system | US12512238 | 2009-07-30 | US08562888B2 | 2013-10-22 | James A. Kelley; Michael B. Weaver; David Schultz; Jason O'Rustus LeFever |
| A system and method for dispensing a sealant over aircraft fasteners secured to a surface in the aircraft. The system includes a nozzle tip having a shroud configured for placement over the fasteners. Sealant is metered to the shroud via an orifice within the nozzle tip. The shroud is sized to leave a space between it and the fastener to control the amount of sealant applied to the fastener upper surface and along the interface between the fastener and aircraft surface. Pressurized fluid urges the sealant through the orifice. | ||||||
| 109 | STRUCTURAL ARRANGEMENT FOR ACCESS WINDOW TO FUEL TANK WITH COMPOSITE COATING | US13729416 | 2012-12-28 | US20130205667A1 | 2013-08-15 | Aroldo PONTES; Danilo Seixas VICTORAZZO; Douglas Carrari FIRMINO; Erich Robert SCHAAY; Fabiano LOBATO; Flavio Yoiti SASAKI; Sidney Osses NUNES; Silvio Luiz Francisco OSORIO |
| There is disclosed a structural arrangement (10) for an access window (30) to a fuel tank (20) with composite coating (40), this structural arrangement (10) comprising an external lid (11) associated to the access window (30) by fastening means (12), the structural arrangement (10) for an access window (30) to a fuel tank (20) with composite coating (40) further comprising a continuous metal frame (31) disposed on an internal portion of the fuel tank (20), fastened to the composite coating (40) internally and perimetrally circumventing the access window (30), the continuous metal frame (31) being cooperative with the external lid (11) in the conduction of an electric current. | ||||||
| 110 | ELECTRICAL CONNECTORS | US13716254 | 2012-12-17 | US20130161094A1 | 2013-06-27 | Paul BROUGHTON; Richard PEACE; Gary Alan SKINNER; Michael Christopher WILLMOT; Robin Charles KENNEA |
| An electrical raft 200 comprising electrical conductors 252 embedded in a rigid material are provided to a gas turbine engine. The raft 200 is used to transport electrical signals (which may be, for example power and/or control signals) around a gas turbine engine. The electrical raft 200 has an electrical connector 700 embedded therein which is used to connect the electrical raft to an electrical unit, such as an EEC of a gas turbine engine The electrical connector 700 is resiliently biased so as to ensure a reliable electrical connection. | ||||||
| 111 | ELECTRICAL RAFT ASSEMBLY | US13716808 | 2012-12-17 | US20130160458A1 | 2013-06-27 | Michael Christopher WILLMOT; Paul BROUGHTON; Richard PEACE; Gary Alan SKINNER; Robin Charles KENNEA |
| An electrical raft assembly for a gas turbine engine is provided. The raft assembly comprises a rigid electrical raft formed of a rigid material that includes an electrical system comprising electrical conductors embedded in the rigid material. The raft assembly further comprises an engine component that is mounted to the electrical raft. The electrical raft includes one or more integral cooling passages which guide a coolant fluid through the raft to cool the engine component | ||||||
| 112 | ARTICLES OF COMPOSITE CONSTRUCTION AND METHODS OF MANUFACTURE THEREOF | US13763076 | 2013-02-08 | US20130156981A1 | 2013-06-20 | William RODGERS |
| An article manufactured in a mould and which comprises a structural composite of plastics layers, the article having a wall defining an internal space for holding contents therein; wherein, the wall is formed from at least two layers of plastics materials; wherein a first of said layers comprises a thermoplastics material and at least a second layer comprises a thermosetting resin and a fibrous layer. | ||||||
| 113 | Electrostatic Bonding of Coaxial Tubing | US13248756 | 2011-09-29 | US20130081734A1 | 2013-04-04 | Gregory M. Waugh; Michael Lyle Holbrook; Ronald Lawrence Clements |
| A method and apparatus for electrostatically bonding coaxial tubing. An outer tube comprises an electrically conductive material and has an inner surface. An inner tube comprises material and has an outer surface. The inner tube and the outer tube are positioned to define a channel. A bridging structure comprising an electrically conductive material is positioned such that the bridging structure forms mechanical contact and an electrostatic connection between electrically conductive material on the tubes. The bridging structure is in mechanical contact with the inner surface of the outer tube at a first plurality of points and in mechanical contact with the outer surface of the inner tube at a second plurality of points. | ||||||
| 114 | Aircraft spillover fuel tank | US12199069 | 2008-08-27 | US08172182B2 | 2012-05-08 | Richard Bruce Tanner |
| Apparatus and methods described herein provide for a spillover tank to extend the fuel capacity of the main wing tank of an aircraft. The spillover tank is located in the wing of the aircraft adjacent to the main wing tank. At least one aperture exists through the shared barrier between the main wing tank and the spillover tank that allows fuel to flow passively between the tanks. A scavenge pump mechanism driven by motive flow from the main fuel pumps continuously pumps fuel from the spillover tank into the main wing tank. | ||||||
| 115 | Autophagous multifunction structure-power system | US11217851 | 2005-09-01 | US08141822B2 | 2012-03-27 | James P. Thomas; Jared N. Baucom; William R. Pogue, III; Siddiq M. Qidwai |
| A vehicle including at least one bladder for containing a two-phase liquid-gas fuel at a predetermined pressure, with a bladder outlet arranged to releasing vapor fuel from the bladder. The fuel provides energy for propulsion of the vehicle, and the vapor pressure of the fuel provides initial structural integrity of the vehicle, by rigidizing and stiffening the beam assembly to resist inward buckling until the liquid fuel is expended. In an exemplary embodiment, the vehicle is an unmanned aerial vehicle. A combustion chamber and thermoelectric conversion module can generate electricity for a propeller and battery. | ||||||
| 116 | Cover for an aircraft access opening | US11897007 | 2007-08-28 | US08016235B2 | 2011-09-13 | Gonzalo Ramirez Blanco; Jose Luis Lozano Garcia; Daniel Barroso Vloedgraven |
| The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover (18) arranged on the outer part of the aircraft skin (28), the carbon fiber layers (14) forming the skin (28) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin (28) for the seating of the outer cover (18). a composite material plate (15) arranged in the outer part of the skin (28) and surrounding the area for installing the outer cover (18); an inner cover (27) arranged on the inner part of the aircraft skin (28). | ||||||
| 117 | Clamp for securing an object to a structure | US11947427 | 2007-11-29 | US07770848B2 | 2010-08-10 | Richard K. Johnson; Jon P. Michel; Kevin E. Clark; Michael L. Gilbertson |
| Apparatus and methods provide an electrically isolating clamp that is suitable for use, among other locations, within a composite wing structure and other fuel environments. According to embodiments described herein, the clamp includes a clamp body and cushion. The clamp body is manufactured from a non-conductive material and includes a strap and a base. The cushion may be manufactured from a different non-conductive material to provide at least two layers of electrical isolation between the tube or other object being secured and a structure. The cushion material allows for axial movement of the tube through the cushion. The cushion is disposed between the strap and the base. Shoulder flanges prevent axial movement of the cushion with respect to the clamp body. The clamp may have a cushion retention mechanism to secure the cushion within the strap prior to installation around the tube. | ||||||
| 118 | AIRCRAFT SPILLOVER FUEL TANK | US12199069 | 2008-08-27 | US20100051749A1 | 2010-03-04 | Richard Bruce Tanner |
| Apparatus and methods described herein provide for a spillover tank to extend the fuel capacity of the main wing tank of an aircraft. The spillover tank is located in the wing of the aircraft adjacent to the main wing tank. At least one aperture exists through the shared barrier between the main wing tank and the spillover tank that allows fuel to flow passively between the tanks. A scavenge pump mechanism driven by motive flow from the main fuel pumps continuously pumps fuel from the spillover tank into the main wing tank. | ||||||
| 119 | Articles of Composite Construction and Methods of Manufacture Thereof | US12279755 | 2007-02-17 | US20090304962A1 | 2009-12-10 | William Rodgers |
| An article manufactured in a mould and which comprises a structural composite of plastics layers, the article having a wall defining an internal space for holding contents therein; wherein, the wall is formed from at least two layers of plastics materials; wherein a first of said layers comprises a thermoplastics material and at least a second layer comprises a thermosetting resin and a fibrous layer. | ||||||
| 120 | Cover for an aircraft access opening | US11897007 | 2007-08-28 | US20090294591A1 | 2009-12-03 | Gonzalo Ramirez Blanco; Jose Luis Lozano Garcia; Daniel Barroso Vloedgraven |
| The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements:an outer cover (18) arranged on the outer part of the aircraft skin (28), the carbon fiber layers (14) forming the skin (28) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin (28) for the seating of the outer cover (18).a composite material plate (15) arranged in the outer part of the skin (28) and surrounding the area for installing the outer cover (18);an inner cover (27) arranged on the inner part of the aircraft skin (28). | ||||||
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