| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | 同軸管類の静電結合 | JP2014533533 | 2012-08-24 | JP5972383B2 | 2016-08-17 | ウォー, グレゴリー エム.; ホルブルック, マイケル ライル; クレメンツ, ロナルド ローレンス |
| 42 | ハットストリンガ終端部取付け具とその作製方法 | JP2015160295 | 2015-08-17 | JP2016043923A | 2016-04-04 | ロルフェス, コーリー エー.; スタルク, ジェフリー エフ. |
| 【課題】ハットストリンガのランアウトトリム位置付近の局所負荷による悪影響を排除する方法を提供する。 【解決手段】ハットストリンガ用の終端部取付け具100は、取付け表面134を有するカバー130を含む。取付け表面は、ハットストリンガの外面の少なくとも一部分と相補関係にある。カバーは、ハットストリンガ外面に結合される。カバーは、ハットストリンガのキャップ部分において画定される間隙を横切って伸びる、第1の部分も含む。終端部取付け具はインサート102も含む。インサートは、ハットストリンガによって画定されるチャネルの内面の少なくとも一部分と実質的に相補関係にある、第1の外周表面103を含む。インサートは、ハットストリンガ終端部分の近傍のチャネル内面に結合される。インサート及びカバーは、クローズアウト部分近傍のハットストリンガの変形を制限するのに適切な剛性を有する。 【選択図】図4 |
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| 43 | 燃料タンク | JP2011053128 | 2011-03-10 | JP5751871B2 | 2015-07-22 | 和久 浩行 |
| 44 | 燃料システム、航空機 | JP2013163987 | 2013-08-07 | JP2015030447A | 2015-02-16 | KOMODA USHIO |
| 【課題】第1タンク内に貯留される燃料の量よりも第2タンク内に貯留される燃料の量を先に減少させる構成を少ない部材で簡素に構成した燃料システムを提供する。【解決手段】燃料システム10は、燃料をそれぞれ貯留するアウタータンク30(第1タンク)およびインナータンク(第2タンク)40と、アウタータンク30およびインナータンク40のうち少なくともアウタータンク30内の燃料を燃料消費部に向けて供給する燃料供給ポンプ31と、インナータンク40内の燃料をアウタータンク30内へと移送する移送ポンプ23と、アウタータンク30内に連通する入口21、およびインナータンク40内に連通する出口22を有する燃料通路20と、を備える。燃料通路20を通じて、アウタータンク30内の燃料をインナータンク40内へとオーバーフローさせる。【選択図】図3 | ||||||
| 45 | 同軸管類の静電結合 | JP2014533533 | 2012-08-24 | JP2015502501A | 2015-01-22 | グレゴリー エム． ウォー，; マイケル ライル ホルブルック，; ロナルド ローレンス クレメンツ， |
| 【課題】同軸管類の静電結合のための方法及び装置を提供する。【解決手段】外側管は、導電性材料を備え、内側表面を有する。内側管は、材料を備え、外側表面を有する。内側管及び外側管は、流路を画定するように位置決めされる。導電性材料を備える橋渡し構造は、当該橋渡し構造が両方の管の上の導電性材料の間に機械的な接触及び静電接続を形成するように位置決めされる。橋渡し構造は、複数の第1のポイントにおいて外側管の内側表面と機械的に接触し、複数の第2のポイントにおいて内側管の外側表面と機械的に接触する。【選択図】図6 | ||||||
| 46 | 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 | JP2012555973 | 2012-02-03 | JP5654055B2 | 2015-01-14 | 雄也 田中; 吉田 愼一; 愼一 吉田; 田中 秀明; 秀明 田中; 鈴木 秀之; 秀之 鈴木; 阿部 俊夫; 俊夫 阿部; 聖絃 柏木 |
| 47 | Fuel tank, main wing, aircraft fuselage, aircraft, and movable body | JP2013064444 | 2013-03-26 | JP2014189070A | 2014-10-06 | KAMIHARA NOBUYUKI; KISHIMOTO KAZUAKI; ABE TOSHIO; KAMINO YUICHIRO |
| PROBLEM TO BE SOLVED: To provide a fuel tank capable of preventing an increase in weight by reducing operation time and cost for quality control, a main wing, an aircraft fuselage, an aircraft, and a movable body.SOLUTION: A fuel tank comprises a structural member that uses carbon fiber-reinforced plastics (CFRP) 15 having a reinforcement material including a carbon fiber, and a matrix including plastics. The structural member is molded in such a manner that a conductive sheet 17 is superposed between prepregs of the carbon fiber-reinforced plastics (CFRP) 15, and a fastening hole 22, to which a bolt 20 is to be fastened, is formed. | ||||||
| 48 | Fuel tank, main wing, aircraft fuselage, aircraft, and movable body | JP2013064443 | 2013-03-26 | JP2014189069A | 2014-10-06 | KAMIHARA NOBUYUKI; KISHIMOTO KAZUAKI; ABE TOSHIO; KAMINO YUICHIRO |
| PROBLEM TO BE SOLVED: To provide a fuel tank capable of preventing an increase in weight by reducing operation time and cost for a manufacturing process, a main wing, an aircraft fuselage, an aircraft, and a movable body.SOLUTION: A fuel tank comprises a structural member that uses carbon fiber-reinforced plastics (CFRP) 15 having a reinforcement material including a carbon fiber, and a matrix including plastics. The structural member is molded in such a manner that a conductive sheet 17 is superposed between prepregs of the carbon fiber-reinforced plastics (CFRP) 15. In this case, a cut surface 11a of the structural member, which is formed by cutting the structural member, can also be exposed on the inside for housing fuel. | ||||||
| 49 | Method of making an article of goods and composite structure of the composite structure | JP2008554566 | 2007-02-17 | JP5579391B2 | 2014-08-27 | ロジャーズ、ウィリアム |
| 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. | ||||||
| 50 | 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 | JP2012555973 | 2012-02-03 | JPWO2012105691A1 | 2014-07-03 | 雄也 田中; 吉田 愼一; 愼一 吉田; 田中 秀明; 秀明 田中; 鈴木 秀之; 秀之 鈴木; 阿部 俊夫; 俊夫 阿部; 聖絃 柏木 |
| 孔の周縁部の応力集中を考慮した上で、軽量化が可能とされた複合材構造体を提供する。複合材構造体である主翼(1)は、一方向に延在するとともにアクセスホール(5)が形成された繊維強化プラスチック製の複合材とされる。主翼(1)の下面外板(3)には、長手方向に引張り荷重が負荷される。アクセスホール(5)の周縁領域(3a)の長手方向における引張り剛性およびが、周縁領域(3a)を取り囲む他領域(3b)の長手方向における引張り剛性よりも小さい。 | ||||||
| 51 | Composite tank, wings, and a method for manufacturing a composite tank | JP2009083366 | 2009-03-30 | JP5237170B2 | 2013-07-17 | 弘晃 山口; 祐一郎 神納; 康一 中村; 徹 橋上 |
| Disclosed is a composite tank that can curb static buildup, corrosion, and strength degradation. Also disclosed are a wing provided with said composite tank and a method for manufacturing the composite tank. The composite tank is characterized by being provided with: a tank body, inside which combustible material is stored, having a first resin part (11, 12) formed from fiber-reinforced resin as well as a metal part formed from metal; a second resin part (22) comprising fiber-reinforced resin and covering at least the arena of the first resin part (11, 12), on the inner surface of the tank body, that adjoins the metal part; and multiple conductive parts (23) that enable transfer of charge to the first resin part (11, 12) from the surface of the second resin part (22) that is in contact with the combustible material. The fibers included in the second resin part (22) have higher electrical resistance than the fibers included in the first resin part (11, 12). The second resin part (22) forms a layer that isolates the first resin part (11, 12) and the metal part from each other. | ||||||
| 52 | Coupling structure for airframe component | JP2011055999 | 2011-03-14 | JP2012192752A | 2012-10-11 | KAWAHARA KOJI; YAMAKOSHI HIDEO; KAMINO YUICHIRO; IYOMASA ATSUHIRO; HASHIGAMI TORU |
| PROBLEM TO BE SOLVED: To provide a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability.SOLUTION: 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. | ||||||
| 53 | Composite material structure and aircraft main wing provided therewith | JP2011023155 | 2011-02-04 | JP2012162148A | 2012-08-30 | TANAKA YUYA; SUZUKI HIDEYUKI; KANAYAMA YUTAKA; SATO KAZUTAKA; HATANO MASATAKE; SAITO AKIRA; WATANABE KOEI; ABE RYO |
| PROBLEM TO BE SOLVED: To provide a composite material structure having holes and enabling weight reduction.SOLUTION: The composite material structure is provided with: a front section 3a that is a composite material made of fiber reinforced plastic, and extends in one direction; a rear section 3c that is a composite material made of fiber reinforced plastic, and extends in the one direction as separated by a predetermined distance from the front section 3a; and an access panel 5 that is provided between the front section 3a and the rear section 3c, and has a shorter dimension in the one direction than the front section 3a and the rear section 3c. The access panel 5 is removable, and disposed as fixed in an orthogonal direction that is substantially orthogonal to the one direction and shiftable in the one direction with respect to the front section 3a and the rear section 3c. | ||||||
| 54 | Skin panel of an aircraft having an ultrasonic measuring instrument | JP2011529624 | 2009-09-22 | JP2012504525A | 2012-02-23 | ビール，ジェイムズ; ペティット，ブリン |
| An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mounted to an inner surface of the skin layer adjacent to the hole in the skin layer; and an access panel which covers the hole and can be removed to gain access to the gauge. | ||||||
| 55 | Composite tank, wing, and manufacturing method of composite tank | JP2009083366 | 2009-03-30 | JP2010235133A | 2010-10-21 | YAMAGUCHI HIROAKI; KAMINO YUICHIRO; NAKAMURA KOICHI; HASHIGAMI TOORU |
| <P>PROBLEM TO BE SOLVED: To provide a composite tank that can curb static buildup, corrosion, and strength degradation, a wing provided with the composite tank, and a method for manufacturing the composite tank. <P>SOLUTION: The composite tank is characterized by being provided with: a tank body, inside which combustible material is stored, having a first resin part 11, 12 formed from fiber-reinforced resin as well as a metal part formed from metal; a second resin part 22 comprising fiber-reinforced resin and covering at least the area of the first resin part 11, 12, on the inner surface of the tank body, that adjoins the metal part; and multiple conductive parts 23 that enable transfer of charge to the first resin part 11, 12 from the surface of the second resin part 22 that is in contact with the combustible material. The fibers included in the second resin part 22 have higher electrical resistance than the fibers included in the first resin part 11, 12. The second resin part 22 forms a layer that isolates the first resin part 11, 12 and the metal part from each other. <P>COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 56 | Fuel tank of aircraft | JP2008306573 | 2008-12-01 | JP2010126133A | 2010-06-10 | YAMAGUCHI HIROAKI; KAMINO YUICHIRO; HASHIGAMI TOORU; OGURI KAZUYUKI |
| PROBLEM TO BE SOLVED: To provide the fuel tank of an aircraft suppressing the occurrence of spark in pipes due to flow of a thunder current upon lightning strike, and suppressing electrostatic charge in the pipes due to flow charge with a fuel. SOLUTION: This fuel tank 1 of the aircraft includes a storage part formed by using a conductive upper outer plate 5, lower outer plate 7, and spars 9. The fuel tank includes the pipes in the fuel tank such as a fuel resupply pipe 17, fuel supply pipe 19, and inert gas pipe 21, that are arranged in the storage part and grounded 27 at a plurality of places, and a pipe outer surface layer 31 with semiconducting characteristics formed integrally on the outer surface of the pipe in the fuel tank such as the fuel resupply pipe 17, fuel supply pipe 19, and inert gas pipe 21. COPYRIGHT: (C)2010,JPO&INPIT | ||||||
| 57 | 密封されたフロー導管を形成するジョイントアッセンブリ | JP2014054097 | 2014-03-17 | JP6436637B2 | 2018-12-12 | エリクソン, マーカス アレクサンダー; チェンガルバ, マヘシュ ケー.; パース, アーロン スティーヴン |
| 58 | 航空機用構造体、航空機用構造体の製造方法及び航空機用構造体の設計情報の作成方法 | JP2015033424 | 2015-02-23 | JP6139582B2 | 2017-05-31 | 川島 愛; 秋葉 公三郎; 駒場 康益; 弘松 悦明; 西 孝裕樹; 藤田 博康 |
| 59 | ベント部材、航空機の主翼 | JP2011285439 | 2011-12-27 | JP6100461B2 | 2017-03-22 | 古茂田 潮; 本橋 秀人 |
| 60 | 構造体用構造材、燃料タンク、主翼及び航空機 | JP2014540861 | 2013-10-09 | JPWO2014057960A1 | 2016-09-05 | 信幸 神原; 阿部 俊夫; 俊夫 阿部; 奥田 晃久; 晃久 奥田; 朗 井加田; 政之 山下; 和昭 岸本; 祐一郎 神納 |
| 製造工程における作業時間やコストを低減し、重量の増加を防止することが可能な構造体用構造材、燃料タンク、主翼及び航空機を提供することを目的とする。構造体用構造材であるリブ(11)は、補強材が炭素繊維を含み、マトリックスがプラスチックを含む炭素繊維強化プラスチックを備え、炭素繊維強化プラスチックの表面に、導電性が付与されている低粘度の表面保護材(18)が塗布されたことを特徴とする。 | ||||||
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