| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | 燃料タンク、主翼、航空機胴体、航空機及び移動体 | JP2014507684 | 2013-03-15 | JP5972967B2 | 2016-08-17 | 神原 信幸; 山下 政之; 阿部 俊夫; 神納 祐一郎 |
| 62 | 航空機用複合材構造体、これを備えた航空機主翼および航空機胴体 | JP2011023154 | 2011-02-04 | JP5808111B2 | 2015-11-10 | 田中 雄也; 鈴木 秀之; 金山 豊; 佐藤 一貴; 波多野 正剛; 齋藤 暁; 渡邉 晃永; 安倍 良 |
| 63 | 連続的に湾曲した桁および製造方法 | JP2014071154 | 2014-03-31 | JP2015155290A | 2015-08-27 | ジョンソン, マイケル パターソン; アッカーマン, ジェームズ エフ.; イーストランド, クリストファー シー.; ダニエルズ, ディルク エル.; バーポ, スティーヴン ジェー. |
| 【課題】一般に飛行体構造桁に関し、より詳細には、飛行体の複合エアフォイルにおける連続的に湾曲した構造桁、およびこれを製造する方法に関する。 【解決手段】エアフォイル14内に配設された1つまたは複数の燃料格納領域28と、エアフォイルの付け根端部からエアフォイルの先端部に向かって延びる1つまたは複数の連続的に湾曲した桁26とを有する。少なくとも1つの連続的に湾曲した桁は、一体形状を有し、連続的に湾曲した桁に沿って1つまたは複数の連続曲線を有し、1つまたは複数の燃料格納領域の少なくとも1つの構造壁29b、29dを形成する部分を有する、または1つまたは複数の燃料格納領域の内部に存在する。 【選択図】図5A |
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| 64 | 航空機燃料タンク不活性システム | JP2015509403 | 2013-04-29 | JP2015515940A | 2015-06-04 | アシュトン ドミニク; ウッド ジョン; フォスター ジョン |
| 航空機燃料タンク・システムは、少なくとも1つの燃料タンク(20)を具え、少なくとも1つの燃料タンク(20)は、複数の相互接続された室と、大気(32)が内部に通気するように構成された通気孔と、を具え、システムは、内部に通気した空気(32)を通気ダクト(36、42)に沿って導くように構成され、通気ダクト(36、42)は、内部に通気した空気(32)を、実質的に相互接続された室の各々に運ぶように構成されている。 | ||||||
| 65 | 燃料タンク用ダム、及び閉塞方法 | JP2013188338 | 2013-09-11 | JP2015054581A | 2015-03-23 | YAMAGUCHI EIZABURO; OKUDA AKIHISA |
| 【課題】シール性を高めることができる、燃料タンク用ダム、及び閉塞方法を提供する。【解決手段】燃料タンク用ダムは、第1構造部品と第2構造部品との間に形成される隙間を閉塞する。燃料タンク用ダムは、第1構造部品側に配置される第1部分8と、第2構造部品側に配置される第2部分9と、一端で第1部分に支持され、他端で第2部分に支持され、第1部分と第2部分との間に形成される隙間を閉塞する、弾性部材10と、第1部分と弾性部材との間をシールするシール機構13−1、2とを備える。【選択図】図3 | ||||||
| 66 | 超音波計測器を備えた航空機のスキンパネル | JP2011529624 | 2009-09-22 | JP5628813B2 | 2014-11-19 | ペティット，ブリン; ビール，ジェイムズ |
| 67 | Joint assembly to form sealed flow conduit | JP2014054097 | 2014-03-17 | JP2014181033A | 2014-09-29 | ERICKSON MARCUS ALEXANDER CLARENCE; MAHESH K CHENGALVA; AARON STEPHEN PAHS |
| PROBLEM TO BE SOLVED: To provide a joint assembly of structures modified to function as conduits for fuel venting.SOLUTION: An apparatus comprises an elongated structure 402, 406, a first plate 410, and a second plate 412. The elongated structure has a channel. The elongated structure is configured to be associated with a primary structure 404, 408 on a first side of the primary structure. The first plate is configured to be connected to the primary structure at a joint and cover a portion of the elongated structure. The first plate is connected to the primary structure on the first side of the primary structure. The second plate is configured to be connected to the primary structure on a second side of the primary structure. | ||||||
| 68 | Closure member of the opening | JP2010112782 | 2010-05-17 | JP5529624B2 | 2014-06-25 | 和希 橘 |
| 69 | Closure member of the opening, aircraft | JP2010027672 | 2010-02-10 | JP5378260B2 | 2013-12-25 | 秀人 本橋 |
| An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. A door body 30, a clamp ring 40 made of a composite material, and an opening 12 of a wing panel 11 made of the composite material 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. | ||||||
| 70 | Composite material structure, aircraft wing and aircraft fuselage having the same, and method for manufacturing the composite material structure | JP2012044757 | 2012-02-29 | JP2013180627A | 2013-09-12 | KASHIWAGI MASAHIRO; NONAKA YOSHINORI; ABE TOSHIO |
| PROBLEM TO BE SOLVED: To provide a composite material structure reducible in weight after considering so as to hardly cause breakage at an easily broken part while easing a strain concentration rate around a hole, and to provide an aircraft wing and an aircraft fuselage having the composite material structure, and a method for manufacturing the composite material structure.SOLUTION: A composite material structure 3 formed of a composite material made of fiber-reinforced plastics and formed with holes 5 while extending in one direction is loaded with tensile load and/or compressive load in one direction. In the composite material structure 3, tension rigidity and/or compression rigidity in one direction of a peripheral edge region 3a of the hole 5 are smaller than tension rigidity and/or compression rigidity in the one direction of another region 3b surrounding the peripheral edge region 3a, and the peripheral edge region 3a in a direction orthogonal to the one direction is defined to a width at most 1.1 times as large as the diameter of the hole 5 in the direction orthogonal to the one direction. | ||||||
| 71 | Closure member for opening part | JP2010027671 | 2010-02-10 | JP2011162081A | 2011-08-25 | MOTOHASHI HIDETO |
| PROBLEM TO BE SOLVED: To provide a closure member for an opening part excellent in thunder-resistant performance and capable of being manufactured at low cost. SOLUTION: In a door body 30, an outer surface 31a of a plate part 31 is formed by a composite material layer 60, and an inner surface 31b side and a flange part 32 are formed by a metal material layer 61. Further, the door body 30, a clamp ring 40 and an opening part 12 of a wing surface panel 11 are electrically connected to each other on an abutment portion of an abutment surface 34 of the door body 30 and a taper surface 40c of the clamp ring 40 and an abutment portion of a taper surface 40d of the clamp ring 40 and an abutment surface 14 of the opening part 12 by surface-bonding of mutual conductive materials. COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 72 | Fuel tank for aircraft | JP2009083361 | 2009-03-30 | JP2010234900A | 2010-10-21 | YAMAGUCHI HIROAKI; KAMINO YUICHIRO; HASHIGAMI TOORU; OGURI KAZUYUKI; NAKAMURA KOICHI |
| <P>PROBLEM TO BE SOLVED: To provide a fuel tank for an aircraft, capable of suppressing electrostatic charge, for example, caused by flow electrification with fuel. <P>SOLUTION: The fuel tank for an aircraft includes an upper outer plate 5 and a lower outer plate 7 which have electric conductivity and form part of a container for housing fuel, an inner structure 19 which is formed of metal, and an inner surface layer 15 which has a semiconductor property or an insulation property and is formed integrally on the inner surfaces of the upper outer plate 5 and the lower outer plate 7 in a location where the inner structure 19, and the upper outer plate 5 and the lower outer plate 7 are in contact with each other and in a surrounding portion thereof, wherein the inner surface layer 15 at least in the surrounding portion is formed of a material having the semiconductor property. <P>COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 73 | Method of making an article of goods and composite structure of the composite structure | JP2008554566 | 2007-02-17 | JP2009533238A | 2009-09-17 | ロジャーズ、ウィリアム |
| モールドで製造された物品であって、複数のプラスチック層の構造用複合材でできており、内部空間を規定し、この空間中に中身を保持するための壁を具備し、この壁は、プラスチック材料の少なくとも２つの層により形成されており、これら層の第１の層は、熱可塑性プラスチック材料でできており、また、少なくとも第２の層は、熱硬化性樹脂と繊維層とでできている物品。 | ||||||
| 74 | IMPROVED WING STRUCTURE | PCT/GB2010050555 | 2010-03-31 | WO2010116170A2 | 2010-10-14 | TUCKER MICHAEL; SANDERSON TIMOTHY |
| A wing structure (10) is provided, wherein the wing structure comprises; an upper covering (13), a lower covering (14), and a spar (20), the spar comprising; a spar web (21), an upper spar cap (22) attached to the upper covering, and a lower spar cap (23) 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 (70) 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. | ||||||
| 75 | OPTIMIZED AIRCRAFT MANHOLE | PCT/EP2008068301 | 2008-12-26 | WO2009083575A2 | 2009-07-09 | ZUNIGA SAGREDO JUAN |
| The present invention relates to an aircraft manhole comprising a skin panel (1) of the aircraft structure, an outer door (6) and an inner door (5) of the aircraft manhole being positioned on the mentioned skin panel (1), further comprising stringers (3) installed on the skin panel (1) positioned on and attached to the skin (1), fixing edges (8) partially projecting through the manhole on the side for positioning the outer door (6) and inner door (5), further comprising reinforcements (4) arranged between the outer door (6) and the inner door (5) of the manhole that are attached to the skin (1), said reinforcements (4) forming the fixing edges (8) on one of its sides, and a cavity (7) arranged in the skin (1) to allow installing the outer door (6), thus maintaining the aerodynamic surface of the assembly as well as its tightness. | ||||||
| 76 | Composite material structure, aircraft wing and aircraft fuselage provided with same, and method for manufacturing composite material structure | US15117895 | 2015-03-17 | US10137664B2 | 2018-11-27 | Masahiro Kashiwagi; Yoshinori Nonaka; Toshio Abe |
| In a composite material structure, which is configured as a fiber-reinforced plastic composite material extending in one direction and having a plurality of holes defined at intervals in a row in the one direction and which is subjected to a tensile load and/or a compressive load in the one direction, a peripheral region around the holes comprises a first area obtained by bending composite material, which is reinforced using continuous fibers that have been made even in a longitudinal direction, so that a center line of a width of the composite material weaves between adjacent holes and zigzags in the one direction. A tensile rigidity and/or a compressive rigidity in the one direction of the peripheral region around the holes is lower than a tensile rigidity and/or a compressive rigidity in the one direction of other regions that surround the peripheral region. | ||||||
| 77 | Deformable Clips for an Aircraft Fuel System | US15496257 | 2017-04-25 | US20180305037A1 | 2018-10-25 | James Everett Kooiman; Charles David Hogue; George Ryan Decker; Andrew G. Baines; Douglas Kirk Wolfe |
| A fuel system for an aircraft includes a fuel cell having a plurality of sides including a first side and at least one deformable clip having a secured end and a free end. The secured end is coupled to the first side of the fuel cell and the free end overlapping the airframe of the aircraft such that the first side of the fuel cell is positioned adjacent to the airframe. The at least one deformable clip is deformable to allow the fuel cell to move independently of the airframe in response to an impact of the aircraft, thereby protecting the fuel cell from damage resulting from the impact. | ||||||
| 78 | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body | US14779465 | 2014-02-18 | US10046849B2 | 2018-08-14 | Nobuyuki Kamihara; Kazuaki Kishimoto; Toshio Abe; Yuichiro Kamino |
| The purpose of the present invention is to provide a fuel tank, main wings, an aircraft fuselage, an aircraft, and a moving body, which enable working hours and costs involved in a manufacturing process to be reduced, and weight increases to be prevented. The fuel tank includes a structural member in which carbon fiber reinforced plastic (CFRP) is used, the carbon fiber reinforced plastic (CFRP) including a reinforcing material that includes carbon fibers and a matrix that includes plastic. The structural member is formed by laminating a conductive sheet between prepregs of the carbon fiber reinforced plastic (CFRP). In this case, a cut surface of the structural member formed by cutting the structural member may be exposed on the inside in which fuel is stored. | ||||||
| 79 | Low speed airfoil design for aerodynamic improved performance of UAVs | US14865851 | 2015-09-25 | US09868525B2 | 2018-01-16 | Bradley M. Hopping; Timothy M. Garrett |
| An airfoil configured for low speed performance in an unmanned aerial vehicle includes an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord and a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. The chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil. | ||||||
| 80 | Electrical raft assembly | US13716808 | 2012-12-17 | US09826575B2 | 2017-11-21 | 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. | ||||||
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