JP6000276B2 - 重ね継ぎおよび胴体セクションを結合するための関連する方法 - Google Patents
重ね継ぎおよび胴体セクションを結合するための関連する方法 Download PDFInfo
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- JP6000276B2 JP6000276B2 JP2013544479A JP2013544479A JP6000276B2 JP 6000276 B2 JP6000276 B2 JP 6000276B2 JP 2013544479 A JP2013544479 A JP 2013544479A JP 2013544479 A JP2013544479 A JP 2013544479A JP 6000276 B2 JP6000276 B2 JP 6000276B2
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- 238000000034 method Methods 0.000 title claims description 20
- 239000002131 composite material Substances 0.000 claims description 40
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 26
- 239000010936 titanium Substances 0.000 claims description 26
- 229910052719 titanium Inorganic materials 0.000 claims description 26
- 239000000945 filler Substances 0.000 claims description 18
- 239000000463 material Substances 0.000 description 23
- 210000001503 joint Anatomy 0.000 description 20
- 229910052751 metal Inorganic materials 0.000 description 15
- 239000002184 metal Substances 0.000 description 15
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 12
- 239000011151 fibre-reinforced plastic Substances 0.000 description 12
- 238000005553 drilling Methods 0.000 description 7
- 238000010168 coupling process Methods 0.000 description 6
- 150000002739 metals Chemical class 0.000 description 6
- 230000008878 coupling Effects 0.000 description 5
- 238000005859 coupling reaction Methods 0.000 description 5
- 229910001026 inconel Inorganic materials 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 239000000835 fiber Substances 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 241001529936 Murinae Species 0.000 description 1
- 229910018487 Ni—Cr Inorganic materials 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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- 229910000601 superalloy Inorganic materials 0.000 description 1
Images
Classifications
-
- 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
- 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
- B64C1/068—Fuselage sections
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Clamps And Clips (AREA)
- Bridges Or Land Bridges (AREA)
- Connection Of Plates (AREA)
- Vehicle Step Arrangements And Article Storage (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Moulding By Coating Moulds (AREA)
Description
Claims (12)
- 胴体セクション(12)を結合するための重ね継ぎ(28)であって、
胴体セクション(12)の間を埋めるよう構成されている帯板(30)と、
帯板(30)上に配置された複数の取り付け具(32)と、
帯板(30)の上に重なるシヤタイ(38)であって、円周方向に互いに離間する複数の脚部(40)を含むシヤタイ(38)と、を含み、
帯板(30)とシヤタイ(38)の各脚部(40)の全てとが離間するように、複数の取り付け具(32)の一つが帯板(30)とシヤタイ(38)の複数の脚部(40)の各々との間に位置付けられ、各取り付け具(32)が、帯板(30)のそれぞれ反対側を超えて長手方向に延在している第1および第2のセクションを有し、第1および第2のセクションのそれぞれが、それぞれの胴体セクション(12)の少なくとも2本の縦通材(14)の上に重なるよう構成されている、重ね継ぎ(28)。 - シヤタイ(38)および複数の取り付け具(32)が、複合材料から構成されている請求項1に記載の重ね継ぎ(28)。
- 取り付け具(32)は、第1および第2のセクションのそれぞれが、互いに離間され、かつ、それぞれの縦通材(14)の上に重なる第1部材および第2部材を含むようなH字形である請求項1又は2に記載の重ね継ぎ(28)。
- 各取り付け具(32)が、シヤタイ(38)が据え付けられている第1および第2のセクション間の中間部をさらに含む請求項1に記載の重ね継ぎ(28)。
- シヤタイ(38)の各脚部(40)が、それぞれの取り付け具(32)の中間部上に据え付けられ、かつ、帯板(30)の一部が隣接した取り付け具(32)の間から見えるように複数の取り付け具(32)が互いに離間されている請求項1に記載の重ね継ぎ(28)。
- シヤタイ(38)に接続され、かつ、シヤタイ(38)の機内側にある内側コード(44)をさらに含む請求項1から5のいずれか一項に記載の重ね継ぎ(28)。
- 取り付け具(32)の第1および第2のセクションのそれぞれと縦通材(14)との間に位置付けられている第1および第2充填材(37)をさらに含む請求項1から6のいずれか一項に記載の重ね継ぎ(28)。
- 胴体セクション(12)を結合するための方法であって、
間を埋めるように胴体セクション(12)上に帯板(30)を位置付けること、
各取り付け具(32)の第1および第2のセクションが帯板(30)のそれぞれ反対側を超えて長手方向に延在するように帯板(30)上に複数の取り付け具(32)を位置付けることであって、取り付け具(32)の前記位置付けが、第1および第2のセクションのそれぞれがそれぞれの胴体セクション(12)の少なくとも2本の縦通材(14)の上に重なるように取り付け具(32)を位置付けることを含む、位置付けること、
取り付け具(32)上でシヤタイ(38)を位置付けることであって、前記シヤタイ(38)は円周方向に互いに離間する複数の脚部(40)を含み、帯板(30)とシヤタイ(38)の各脚部(40)の全てとが離間するように、複数の取り付け具(32)の一つが帯板(30)とシヤタイ(38)の複数の脚部(40)の各々との間に位置付けられる、位置付けること、および、
シヤタイ(38)、取り付け具(32)、帯板(30)および胴体セクション(12)を複数の締結具により接続すること、
を含む方法。 - 帯板(30)および取り付け具(32)が、複合材料から構成されており、かつ、シヤタイ(38)、取り付け具(32)および胴体セクション(12)を接続することが、シヤタイ(38)、取り付け具(32)および胴体セクション(12)を複数のチタン製締結具により接続することを含む請求項8に記載の方法。
- 各取り付け具(32)の第1および第2のセクションのそれぞれと、それぞれの胴体セクション(12)の縦通材(14)との間に第1および第2充填材(37)を位置付けることをさらに含む請求項8又は9に記載の方法。
- 内側コード(44)をシヤタイ(38)に接続することをさらに含む請求項8から10のいずれか一項に記載の方法。
- 取り付け具(32)を位置付けることが、帯板(30)の一部が隣接した取り付け具(32)の間から見えるように離間させて帯板(30)上に複数の取り付け具(32)を位置付けることを含み、かつ、取り付け具(32)上にシヤタイ(38)を位置付けることが、シヤタイ(38)の各脚部(40)がそれぞれの取り付け具(32)の中間部上に据え付けられるように複数の取り付け具(32)上にシヤタイ(38)を位置付けることを含む請求項8から11のいずれか一項に記載の方法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/968,732 | 2010-12-15 | ||
US12/968,732 US8567722B2 (en) | 2010-12-15 | 2010-12-15 | Splice and associated method for joining fuselage sections |
PCT/US2011/059422 WO2012082254A1 (en) | 2010-12-15 | 2011-11-04 | Splice and associated method for joining fuselage sections |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2014500185A JP2014500185A (ja) | 2014-01-09 |
JP2014500185A5 JP2014500185A5 (ja) | 2014-10-23 |
JP6000276B2 true JP6000276B2 (ja) | 2016-09-28 |
Family
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Application Number | Title | Priority Date | Filing Date |
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JP2013544479A Active JP6000276B2 (ja) | 2010-12-15 | 2011-11-04 | 重ね継ぎおよび胴体セクションを結合するための関連する方法 |
Country Status (10)
Country | Link |
---|---|
US (1) | US8567722B2 (ja) |
EP (1) | EP2651757B1 (ja) |
JP (1) | JP6000276B2 (ja) |
KR (1) | KR101872043B1 (ja) |
CN (2) | CN103261020B (ja) |
AU (1) | AU2011341598B2 (ja) |
CA (1) | CA2817735C (ja) |
ES (1) | ES2544051T3 (ja) |
RU (1) | RU2564561C2 (ja) |
WO (1) | WO2012082254A1 (ja) |
Families Citing this family (17)
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US7325771B2 (en) * | 2004-09-23 | 2008-02-05 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
FR2976916B1 (fr) * | 2011-06-27 | 2013-07-26 | Airbus Operations Sas | Dispositif et procede d'assemblage de deux troncons de fuselage d'aeronef |
US8740151B1 (en) * | 2012-01-03 | 2014-06-03 | The Boeing Company | Adjustable splice fitting for shimless connection of structual members |
US8684311B2 (en) * | 2012-03-07 | 2014-04-01 | The Boeing Company | Bonded splice joint |
US8960606B2 (en) * | 2012-10-31 | 2015-02-24 | The Boeing Company | Circumference splice for joining shell structures |
EP2781450B1 (en) | 2013-03-19 | 2018-05-02 | Airbus Operations GmbH | System and method for interconnecting composite structures |
WO2015094059A1 (en) * | 2013-12-20 | 2015-06-25 | Saab Ab | Stiffening element and reinforced structure |
US9527572B2 (en) * | 2014-06-26 | 2016-12-27 | The Boeing Company | Elongated structures and related assemblies |
GB2528080A (en) * | 2014-07-08 | 2016-01-13 | Airbus Operations Ltd | Structure |
US9682429B2 (en) | 2015-04-22 | 2017-06-20 | The Boeing Company | Reaction tool and method for forming openings in an aircraft fuselage joint |
US10392132B2 (en) | 2016-07-29 | 2019-08-27 | The Boeing Company | Curved aircraft substructure repair systems and methods |
US10308342B2 (en) * | 2016-09-07 | 2019-06-04 | The Boeing Company | Method of repairing damage to fuselage barrel and associated apparatus and system |
RU2655585C2 (ru) * | 2016-11-22 | 2018-05-28 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Узел стыка отсеков фюзеляжа с сетчатой и традиционной конструктивно-силовыми схемами |
US11524761B2 (en) * | 2016-12-09 | 2022-12-13 | The Boeing Company | Stringer-frame intersection of aircraft body |
US20200122816A1 (en) * | 2018-10-22 | 2020-04-23 | The Boeing Company | Bulkhead joint assembly |
US11180238B2 (en) * | 2018-11-19 | 2021-11-23 | The Boeing Company | Shear ties for aircraft wing |
GB2615755A (en) * | 2022-02-15 | 2023-08-23 | Airbus Operations Ltd | Fuel tank stringer with flow passage |
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SU1376424A1 (ru) * | 1985-11-19 | 1995-10-27 | Г.Г. Демьяненко | Стык фюзеляжа с центропланом летательного аппарата |
US5518208A (en) * | 1993-12-28 | 1996-05-21 | The Boeing Company | Optimum aircraft body frame to body skin shear tie installation pattern for body skin/stringer circumferential splices |
US5893534A (en) * | 1995-12-22 | 1999-04-13 | The Boeing Company | Structural apparatus and design to prevent oil can movement of webs in aircraft pressure bulkheads |
US7159822B2 (en) * | 2004-04-06 | 2007-01-09 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
US7325771B2 (en) | 2004-09-23 | 2008-02-05 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US7503368B2 (en) * | 2004-11-24 | 2009-03-17 | The Boeing Company | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
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FR2931720B1 (fr) | 2008-06-02 | 2010-12-17 | Airbus France | Procede d'assemblage orbital de troncons d'aeronef en materiau composite |
-
2010
- 2010-12-15 US US12/968,732 patent/US8567722B2/en active Active
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2011
- 2011-11-04 KR KR1020137010495A patent/KR101872043B1/ko active IP Right Grant
- 2011-11-04 RU RU2013132316/11A patent/RU2564561C2/ru active
- 2011-11-04 EP EP11788267.0A patent/EP2651757B1/en active Active
- 2011-11-04 AU AU2011341598A patent/AU2011341598B2/en active Active
- 2011-11-04 JP JP2013544479A patent/JP6000276B2/ja active Active
- 2011-11-04 WO PCT/US2011/059422 patent/WO2012082254A1/en active Application Filing
- 2011-11-04 CN CN201180060281.4A patent/CN103261020B/zh active Active
- 2011-11-04 CN CN201511019399.9A patent/CN105644767B/zh active Active
- 2011-11-04 ES ES11788267.0T patent/ES2544051T3/es active Active
- 2011-11-04 CA CA2817735A patent/CA2817735C/en active Active
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Publication number | Publication date |
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CA2817735C (en) | 2016-12-06 |
CA2817735A1 (en) | 2012-06-21 |
EP2651757A1 (en) | 2013-10-23 |
RU2013132316A (ru) | 2015-01-20 |
ES2544051T3 (es) | 2015-08-27 |
US20120153082A1 (en) | 2012-06-21 |
JP2014500185A (ja) | 2014-01-09 |
WO2012082254A1 (en) | 2012-06-21 |
AU2011341598B2 (en) | 2016-03-10 |
KR20130138359A (ko) | 2013-12-18 |
KR101872043B1 (ko) | 2018-06-27 |
CN105644767B (zh) | 2018-06-12 |
CN103261020B (zh) | 2016-01-20 |
RU2564561C2 (ru) | 2015-10-10 |
CN105644767A (zh) | 2016-06-08 |
CN103261020A (zh) | 2013-08-21 |
US8567722B2 (en) | 2013-10-29 |
EP2651757B1 (en) | 2015-07-22 |
AU2011341598A1 (en) | 2013-05-23 |
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