JP2015016660A - 補強構造体の製造方法 - Google Patents
補強構造体の製造方法 Download PDFInfo
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- JP2015016660A JP2015016660A JP2013146641A JP2013146641A JP2015016660A JP 2015016660 A JP2015016660 A JP 2015016660A JP 2013146641 A JP2013146641 A JP 2013146641A JP 2013146641 A JP2013146641 A JP 2013146641A JP 2015016660 A JP2015016660 A JP 2015016660A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 33
- 239000000463 material Substances 0.000 claims abstract description 76
- 230000001681 protective effect Effects 0.000 claims abstract description 54
- 239000000835 fiber Substances 0.000 claims abstract description 41
- 229920005989 resin Polymers 0.000 claims abstract description 22
- 239000011347 resin Substances 0.000 claims abstract description 22
- 239000002131 composite material Substances 0.000 claims abstract description 5
- 230000003014 reinforcing effect Effects 0.000 claims description 38
- 239000000853 adhesive Substances 0.000 claims description 21
- 230000001070 adhesive effect Effects 0.000 claims description 21
- 238000000034 method Methods 0.000 claims description 17
- 239000004918 carbon fiber reinforced polymer Substances 0.000 claims description 12
- 230000002787 reinforcement Effects 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 239000002828 fuel tank Substances 0.000 description 6
- 229920001187 thermosetting polymer Polymers 0.000 description 6
- 239000003733 fiber-reinforced composite Substances 0.000 description 5
- 239000011241 protective layer Substances 0.000 description 4
- 239000011810 insulating material Substances 0.000 description 2
- 239000003566 sealing material Substances 0.000 description 2
- 239000004065 semiconductor Substances 0.000 description 2
- 239000004925 Acrylic resin Substances 0.000 description 1
- 229920000178 Acrylic resin Polymers 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000004753 textile Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/02—Lightning protectors; Static dischargers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
- B29K2105/08—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2307/00—Use of elements other than metals as reinforcement
- B29K2307/04—Carbon
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
- B29K2995/0003—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds having particular electrical or magnetic properties, e.g. piezoelectric
- B29K2995/0005—Conductive
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
【解決手段】補強構造体の製造方法は、繊維露出面を有するストリンガーを準備する工程と、繊維露出面の少なくとも一部を覆うように、導電性保護材を配置する工程と、未硬化の樹脂成分を有するスキン上に、ストリンガーを配置する工程と、ストリンガーを配置する工程の後に、スキンを硬化させる工程とを有する。導電性保護材は、樹脂成分と導電性の繊維成分とが組み合わされた複合材料を有する。スキンを硬化させる工程は、スキンと導電性保護材とを同時に硬化させる工程を含んでいる。
【選択図】図2
Description
以下、図面を参照しつつ、実施形態について説明する。
まず、硬化済みのストリンガー3が準備される。ストリンガー3は、既述のように、繊維成分と樹脂成分とを含んでおり、繊維成分は樹脂成分に含浸されている。ストリンガー3の表面は樹脂成分に覆われている。硬化済みのストリンガー3は、寸法の調整などを目的として、加工される。本実施形態では、端面6が加工される。これにより、端面6が繊維露出面になる。
次いで、図4に示されるように、ストリンガー3に、導電性保護材9が適用(配置)される。導電性保護材9は、端面6の少なくとも一部を覆うように、貼り付けられる。
続いて、図6に示されるように、ストリンガー3が未硬化のスキン2上に配置される。具体的には、まず、接着面5に接着剤10が適用される。その後、接着面5がスキン2に接着するように、ストリンガー3がスキン2上に配置させられる。
次いで、スキン2及び導電性保護材9が同時に硬化させられる。すなわち、スキン2及び導電性保護材9のそれぞれの樹脂成分が、同時に硬化させられる。スキン2及び導電性保護材9は、例えば、熱及び圧力により、硬化させられる。この際、接着剤10も硬化させられる。これにより、ストリンガー3がスキン2に一体に結合し、補強構造体1が得られる。
続いて、第2の実施形態について説明する。本実施形態では、第1の実施形態と比較し、導電性保護材9の適用位置が変更されている。その他の点については、第1の実施形態と同様の構成を採用することができるので、詳細な説明は省略する。
2(2−1、2−2) スキン
3 ストリンガー
4 板部分
5 接着面
6 端面
7 シール部材
8 保護層
9 導電性保護材
10 接着剤
12−1 被覆領域
12−2 露出領域
13 樹脂成分
14 繊維成分
15 燃料タンク
16 スパー
20 主翼部材
Claims (8)
- 繊維露出面を有するストリンガーを準備する工程と、
前記繊維露出面の少なくとも一部を覆うように、導電性保護材を配置する工程と、
未硬化の樹脂成分を有するスキン上に、前記ストリンガーを配置する工程と、
前記ストリンガーを配置する工程の後に、前記スキンを硬化させる工程と、
を具備し、
前記導電性保護材は、樹脂成分と導電性の繊維成分とが組み合わされた複合材料を有し、
前記スキンを硬化させる工程は、前記スキンと前記導電性保護材とを同時に硬化させる工程を含んでいる
補強構造体の製造方法。 - 請求項1に記載された補強構造体の製造方法であって、
前記ストリンガーは、板部分を有し、
前記板部分は、
前記スキンに接着させられる接着面と、
端面とを有しており、
前記繊維露出面は、前記板部分の端面に設けられている
補強構造体の製造方法。 - 請求項2に記載された補強構造体の製造方法であって、
前記導電性保護材を配置する工程は、前記導電性保護材と前記接着面とが離隔するように、前記端面の一部に前記導電性保護材を配置する工程を含んでいる
補強構造体の製造方法。 - 請求項2に記載された補強構造体の製造方法であって、
前記導電性保護材を配置する工程は、前記端面を包み込むように、前記導電性保護材を配置する工程を含んでいる
補強構造体の製造方法。 - 請求項1乃至4のいずれかに記載された補強構造体の製造方法であって、
前記繊維成分は、炭素繊維を含んでいる
補強構造体の製造方法。 - 請求項1乃至5のいずれかに記載された補強構造体の製造方法であって、
前記ストリンガーを準備する工程は、
硬化済みの炭素繊維強化プラスチック材を準備する工程と、
前記硬化済みの炭素繊維強化プラスチック材の一部を加工することにより、前記ストリンガーを得る工程とを含んでいる
補強構造体の製造方法。 - 請求項1乃至6のいずれかに記載された補強構造体の製造方法であって、
前記スキンは、炭素繊維強化プラスチック材を含んでいる
補強構造体の製造方法。 - 請求項1乃至7のいずれかに記載された補強構造体の製造方法であって、
前記スキンを硬化させる工程は、熱及び圧力により、前記スキン及び前記導電性保護材を硬化させる工程を含んでいる
補強構造体の製造方法。
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2013146641A JP6204092B2 (ja) | 2013-07-12 | 2013-07-12 | 補強構造体の製造方法 |
PCT/JP2014/067008 WO2015005125A1 (ja) | 2013-07-12 | 2014-06-26 | 補強構造体の製造方法 |
CA2917796A CA2917796C (en) | 2013-07-12 | 2014-06-26 | Manufacturing method of reinforced structure |
BR112015032624A BR112015032624A2 (pt) | 2013-07-12 | 2014-06-26 | método de fabricação de uma estrutura de reforço |
EP14823339.8A EP3020540A4 (en) | 2013-07-12 | 2014-06-26 | Method for producing reinforcing structure |
US14/901,822 US9849965B2 (en) | 2013-07-12 | 2014-06-26 | Manufacturing method of reinforced structure |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2013146641A JP6204092B2 (ja) | 2013-07-12 | 2013-07-12 | 補強構造体の製造方法 |
Publications (3)
Publication Number | Publication Date |
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JP2015016660A true JP2015016660A (ja) | 2015-01-29 |
JP2015016660A5 JP2015016660A5 (ja) | 2016-08-25 |
JP6204092B2 JP6204092B2 (ja) | 2017-09-27 |
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JP2013146641A Active JP6204092B2 (ja) | 2013-07-12 | 2013-07-12 | 補強構造体の製造方法 |
Country Status (6)
Country | Link |
---|---|
US (1) | US9849965B2 (ja) |
EP (1) | EP3020540A4 (ja) |
JP (1) | JP6204092B2 (ja) |
BR (1) | BR112015032624A2 (ja) |
CA (1) | CA2917796C (ja) |
WO (1) | WO2015005125A1 (ja) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
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JP6204093B2 (ja) | 2013-07-12 | 2017-09-27 | 三菱重工業株式会社 | 補強構造体の製造方法 |
JP6204092B2 (ja) | 2013-07-12 | 2017-09-27 | 三菱重工業株式会社 | 補強構造体の製造方法 |
US10472473B2 (en) * | 2015-05-26 | 2019-11-12 | The Boeing Company | Enhancing z-conductivity in carbon fiber reinforced plastic composite layups |
DE102017126052A1 (de) | 2017-11-08 | 2019-05-09 | Airbus Operations Gmbh | Versteifungsanordnung für eine Öffnung in einer Flugzeugstruktur |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US20080128430A1 (en) * | 2006-10-13 | 2008-06-05 | The Boeing Company | Edge seals for composite structure fuel tanks |
JP2010523357A (ja) * | 2007-03-30 | 2010-07-15 | エアバス・オペレーションズ・ゲーエムベーハー | 構造部品の製造方法 |
JP2012162147A (ja) * | 2011-02-04 | 2012-08-30 | Mitsubishi Heavy Ind Ltd | 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 |
Family Cites Families (12)
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JP4786426B2 (ja) * | 2005-10-06 | 2011-10-05 | 三菱重工業株式会社 | ファスナ |
CA2660326A1 (en) | 2006-08-17 | 2008-02-21 | Airbus Deutschland Gmbh | Production method for a workpiece composed of a fibre-composite material, and a fibre-composite component in the form of a profile with a profile cross section which varies over its length |
FR2909919B1 (fr) * | 2006-12-13 | 2012-12-07 | Eads Ccr | Procede de fabrication d'une piece complexe en materiau composite a fibres longues et a matrice thermodurcissable |
US8834668B2 (en) * | 2008-11-19 | 2014-09-16 | The Boeing Company | Staged cocuring of composite structures |
EP2251250A1 (en) * | 2009-05-05 | 2010-11-17 | Sika Technology AG | Bonding with adhesive beads or plots |
GB0912015D0 (en) * | 2009-07-10 | 2009-08-19 | Airbus Operations Ltd | Stringer |
DE102010042970A1 (de) | 2010-05-12 | 2011-11-17 | Airbus Operations Gmbh | Strukturbauteil mit verbesserter Leitfähigkeit und mechanischer Festigkeit sowie Verfahren zu dessen Herstellung |
JP5751871B2 (ja) * | 2011-03-10 | 2015-07-22 | 三菱重工業株式会社 | 燃料タンク |
ES2415773B1 (es) | 2011-12-29 | 2014-09-02 | Airbus Operations S.L. | Método de fabricación de piezas de material compuesto con cambios de espesor |
JP6204092B2 (ja) | 2013-07-12 | 2017-09-27 | 三菱重工業株式会社 | 補強構造体の製造方法 |
JP6204093B2 (ja) | 2013-07-12 | 2017-09-27 | 三菱重工業株式会社 | 補強構造体の製造方法 |
US9403350B2 (en) * | 2013-12-16 | 2016-08-02 | The Nordam Group, Inc. | Flash control metal bonding |
-
2013
- 2013-07-12 JP JP2013146641A patent/JP6204092B2/ja active Active
-
2014
- 2014-06-26 US US14/901,822 patent/US9849965B2/en active Active
- 2014-06-26 CA CA2917796A patent/CA2917796C/en not_active Expired - Fee Related
- 2014-06-26 WO PCT/JP2014/067008 patent/WO2015005125A1/ja active Application Filing
- 2014-06-26 EP EP14823339.8A patent/EP3020540A4/en not_active Withdrawn
- 2014-06-26 BR BR112015032624A patent/BR112015032624A2/pt not_active IP Right Cessation
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080128430A1 (en) * | 2006-10-13 | 2008-06-05 | The Boeing Company | Edge seals for composite structure fuel tanks |
JP2010523357A (ja) * | 2007-03-30 | 2010-07-15 | エアバス・オペレーションズ・ゲーエムベーハー | 構造部品の製造方法 |
JP2012162147A (ja) * | 2011-02-04 | 2012-08-30 | Mitsubishi Heavy Ind Ltd | 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 |
Also Published As
Publication number | Publication date |
---|---|
US9849965B2 (en) | 2017-12-26 |
CA2917796A1 (en) | 2015-01-15 |
EP3020540A4 (en) | 2017-03-29 |
CA2917796C (en) | 2017-10-17 |
US20160368583A1 (en) | 2016-12-22 |
JP6204092B2 (ja) | 2017-09-27 |
WO2015005125A1 (ja) | 2015-01-15 |
BR112015032624A2 (pt) | 2017-07-25 |
EP3020540A1 (en) | 2016-05-18 |
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