JP2012531341A - 胴体セグメント及び接合手段を含む胴体要素 - Google Patents
胴体セグメント及び接合手段を含む胴体要素 Download PDFInfo
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- JP2012531341A JP2012531341A JP2012516817A JP2012516817A JP2012531341A JP 2012531341 A JP2012531341 A JP 2012531341A JP 2012516817 A JP2012516817 A JP 2012516817A JP 2012516817 A JP2012516817 A JP 2012516817A JP 2012531341 A JP2012531341 A JP 2012531341A
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- fuselage
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- 238000005304 joining Methods 0.000 title claims abstract description 64
- 239000003351 stiffener Substances 0.000 claims abstract description 30
- 238000010586 diagram Methods 0.000 description 13
- 230000008901 benefit Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 238000013459 approach Methods 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
- 239000002184 metal Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000007667 floating Methods 0.000 description 2
- 238000007373 indentation Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000013521 mastic Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 238000012546 transfer Methods 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
- B64C1/061—Frames
-
- 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
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
- Moulding By Coating Moulds (AREA)
- Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
- Orthopedics, Nursing, And Contraception (AREA)
- Golf Clubs (AREA)
Abstract
Description
Claims (10)
- スキン(3a、3a’、3a’’、3a’’’、300a)を有する胴体セグメント(1a、1a’、1a’’、1a’’’、100a、100a’)と、該セグメント(1a、1a’、1a’’、1a’’’、100a、100a’)のスキンを隣接するセグメント(1b、1b’、1b’’、1b’’’)に連結することができる接合手段(6a、6、6’、6’’、6’’’)とを含む胴体要素であって、
前記セグメント(1a、1a’、1a’’、1a’’’)が胴体の長手方向の軸線(X)に沿って延在しており、前記スキン(3a、3a’、3a’’、3a’’’、300a)が前記セグメント(1a、1a’、1a’’、1a’’’、100a、100a’)の少なくとも一方の端部に少なくとも1つの第1の区分(10、100)を含み、前記胴体セグメント(1a、1a’、1a’’、1a’’’、100a、100a’)が胴体の長手方向の少なくとも1つのスチフナ要素(5a、5a’、5a’’、5a’’’、50a’)を含む、胴体要素において、
前記接合手段(6a、6、6’、6’’、6’’’)が、前記スキン(3a、3a’、3a’’、3a’’’、300a、300a’)の第1の区分(10、100)の外面(30)と接触した状態で置かれ、前記スチフナ要素(5a、5a’、5a’’、5a’’’、50a’)が、前記長手方向の軸線(X)に沿って、前記接合手段(6a、6、6’、6’’、6’’’)において部分的に延在していることを特徴とする、胴体要素。 - 前記スキンが、前記接合手段と接触していない第2の区分(11、110)を含み、前記接合手段(6a、6、6’、6’’、6’’’)の外面(70)が前記スキン(3a、3a’、3a’’、3a’’’、300a、300a’)の第2の区分の外面(32)と面一に位置付けられるように、前記スキン(3a、3a’、3a’’、3a’’’、300a、300a’)の少なくとも1つの第1の区分(10、100)の外面(30)が前記スキン(3a、3a’、3a’’、3a’’’、300a、300a’)の第2の区分(11、110)の外面(32)との関係において前記胴体の長手方向の軸線(X)に対して横断方向にずれていることを特徴とする、請求項1に記載の胴体要素。
- 胴体のスチフナフレーム(4、4’、4’’、4’’’、40、40’’)を含むことを特徴とする、請求項1または2に記載の胴体要素。
- 前記スチフナ要素(5a、5a’、5a’’、5a’’’、50a’)の一方の端部が前記フレーム(4、4’、4’’、4’’’、40)に隣接することを特徴とする、請求項3に記載の胴体要素。
- 前記胴体のスチフナフレーム(4、4’、4’’、4’’’、40、40’’)が、前記胴体の長手方向の軸線(X)に対して横断方向の平面内に延在する本体(4b、4b’、4b’’、4b’’’)と、前記胴体の長手方向の軸線(X)に対して長手方向の平面内に延在するベースプレート(4a、4a’、4a’’)とを含むことを特徴とする、請求項3または4に記載の胴体要素。
- 前記接合手段(6a、6、6’、6’’、6’’’)の内面(71、71’)が前記スチフナフレーム(4、4’、40’’)のベースプレート(4a、4a’)上に固定されていることを特徴とする、請求項5に記載の胴体要素。
- 前記接合手段(6a、6、6’、6’’、6’’’)が接合要素(7a、7’、7’’、7’’’)を含むことを特徴とする、請求項1〜6のいずれか1項に記載の胴体要素。
- 前記接合手段(6a、6、6’、6’’、6’’’)が、前記隣接する胴体セグメントの端部に位置するスキン(300b、300b’’)の一区分を含むことを特徴とする、請求項1〜6のいずれか1項に記載の胴体要素。
- 請求項1〜8のいずれか1項に記載の胴体要素と、隣接する第2の胴体セグメント(1b、1b’、1b’’、1b’’’)とを含み、該第2の胴体セグメント(1b、1b’、1b’’、1b’’’)のスキン(3b、3b’、3b’’、3b’’’)が前記胴体要素の胴体セグメント(1a、1a’、1a’’、1a’’’)のスキン(3a、3a’、3a’’、3a’’’)に連結されていることを特徴とする、胴体部分。
- 請求項9に記載の胴体部分を含むことを特徴とする、航空機。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0954626A FR2947523B1 (fr) | 2009-07-03 | 2009-07-03 | Element de fuselage comportant un troncon de fuselage et des moyens de jonction |
FR0954626 | 2009-07-03 | ||
PCT/FR2010/000489 WO2011001050A1 (fr) | 2009-07-03 | 2010-07-02 | Element de fuselage comportant un troncon de fuselage et des moyens de jonction |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2012531341A true JP2012531341A (ja) | 2012-12-10 |
Family
ID=41728590
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2012516817A Pending JP2012531341A (ja) | 2009-07-03 | 2010-07-02 | 胴体セグメント及び接合手段を含む胴体要素 |
Country Status (9)
Country | Link |
---|---|
US (1) | US9371125B2 (ja) |
EP (1) | EP2448814B1 (ja) |
JP (1) | JP2012531341A (ja) |
CN (1) | CN102612466B (ja) |
BR (1) | BR112012000048A2 (ja) |
CA (1) | CA2766007C (ja) |
FR (1) | FR2947523B1 (ja) |
RU (1) | RU2560949C2 (ja) |
WO (1) | WO2011001050A1 (ja) |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7325771B2 (en) * | 2004-09-23 | 2008-02-05 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
FR2983826B1 (fr) * | 2011-12-12 | 2013-12-20 | Airbus Operations Sas | Structure avant d'avion perfectionnee a compartiment pour train d'atterrissage. |
ES2426111B1 (es) * | 2012-04-17 | 2015-03-24 | Airbus Operations S.L. | Interfaz para superficie de sustentación de aeronave |
EP2706008A1 (en) * | 2012-09-07 | 2014-03-12 | Airbus Operations GmbH | Structural component |
US8960606B2 (en) * | 2012-10-31 | 2015-02-24 | The Boeing Company | Circumference splice for joining shell structures |
ES2819076T3 (es) * | 2013-04-30 | 2021-04-14 | Airbus Operations Sl | Estructura compuesta para una aeronave y procedimiento de fabricación de la misma |
FR3006297B1 (fr) | 2013-05-29 | 2016-07-15 | Airbus Operations Sas | Procede d'assemblage de deux panneaux comportant des raidisseurs a l'aide d'eclisses et aeronef comprenant une zone de jonction amelioree entre une poutre ventrale et une barque avant |
US10093406B2 (en) * | 2014-12-10 | 2018-10-09 | The Boeing Company | Aircraft frame for tailstrike angle enhancement |
CN104724276A (zh) * | 2015-04-14 | 2015-06-24 | 中航沈飞民用飞机有限责任公司 | 一种复合材料蒙皮防侵蚀的机身环向对接结构 |
US10421528B2 (en) | 2016-08-16 | 2019-09-24 | The Boeing Company | Planked stringers that provide structural support for an aircraft wing |
US10207789B2 (en) * | 2016-08-16 | 2019-02-19 | The Boeing Company | Aircraft composite wingbox integration |
US10220935B2 (en) * | 2016-09-13 | 2019-03-05 | The Boeing Company | Open-channel stiffener |
US11383820B2 (en) * | 2019-06-11 | 2022-07-12 | The Boeing Company | Aerodynamic surface lap splice |
NL2023459B1 (en) * | 2019-07-08 | 2021-02-02 | Kok & Van Engelen Composite Structures B V | Fuselage structure of an aircraft and method for manufacturing the same |
FR3101611B1 (fr) * | 2019-10-02 | 2022-02-25 | Airbus Operations Sas | Panneau renforcé à structure alvéolaire comprenant au moins une zone de liaison présentant une surépaisseur et aéronef comprenant au moins un tel panneau renforcé |
US11919617B2 (en) * | 2020-12-17 | 2024-03-05 | The Boeing Company | Circumferential lap splices for sections of fuselage |
JP2022150609A (ja) * | 2021-03-26 | 2022-10-07 | 株式会社Subaru | 複合材構造およびその製造方法 |
US20230139014A1 (en) * | 2021-10-28 | 2023-05-04 | The Boeing Company | Aircraft pressure panel assemblies |
GB2612958B (en) * | 2021-11-08 | 2023-12-20 | Airbus Operations Ltd | Panel assembly |
Citations (5)
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JPH05286493A (ja) * | 1992-04-08 | 1993-11-02 | Honda Motor Co Ltd | 航空機の胴体構造 |
WO1998058759A1 (en) * | 1997-06-20 | 1998-12-30 | British Aerospace Public Limited Company | Friction welding metal components |
US20050183260A1 (en) * | 2003-12-10 | 2005-08-25 | Cedric Meyer | Device for assembly of several elements by riveting and procedure for assembly of panels especially for aircraft fuselages by means of said device |
US20080067289A1 (en) * | 2006-09-15 | 2008-03-20 | Airbus France | Splice plate for stringers and orbital joining device |
US20090020646A1 (en) * | 2007-04-25 | 2009-01-22 | Airbus France | Assembly of panels of an airplane fuselage |
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WO2009048881A2 (en) * | 2007-10-12 | 2009-04-16 | Abe Karem | Composite bulkhead and skin construction |
GB0805268D0 (en) * | 2008-03-25 | 2008-04-30 | Airbus Uk Ltd | Composite joint protection |
FR2933066B1 (fr) * | 2008-06-26 | 2010-09-10 | Airbus France | Element de fuselage d'aeronef |
US8356771B2 (en) * | 2008-07-21 | 2013-01-22 | Airbus Operations Gmbh | Coupling for joining two frame segments |
US8714488B2 (en) * | 2009-01-08 | 2014-05-06 | The Boeing Company | Elastic aircraft joint fairing |
US8282042B2 (en) * | 2009-06-22 | 2012-10-09 | The Boeing Company | Skin panel joint for improved airflow |
EP2415662B1 (en) * | 2010-08-02 | 2012-07-18 | Eurocopter Deutschland GmbH | Fuselage structure made of composite material |
-
2009
- 2009-07-03 FR FR0954626A patent/FR2947523B1/fr not_active Expired - Fee Related
-
2010
- 2010-07-02 BR BR112012000048A patent/BR112012000048A2/pt not_active IP Right Cessation
- 2010-07-02 US US13/381,673 patent/US9371125B2/en active Active
- 2010-07-02 EP EP10734191.9A patent/EP2448814B1/fr active Active
- 2010-07-02 RU RU2012103607/11A patent/RU2560949C2/ru not_active IP Right Cessation
- 2010-07-02 CA CA2766007A patent/CA2766007C/fr not_active Expired - Fee Related
- 2010-07-02 JP JP2012516817A patent/JP2012531341A/ja active Pending
- 2010-07-02 WO PCT/FR2010/000489 patent/WO2011001050A1/fr active Application Filing
- 2010-07-02 CN CN201080029814.8A patent/CN102612466B/zh active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH05286493A (ja) * | 1992-04-08 | 1993-11-02 | Honda Motor Co Ltd | 航空機の胴体構造 |
WO1998058759A1 (en) * | 1997-06-20 | 1998-12-30 | British Aerospace Public Limited Company | Friction welding metal components |
US20050183260A1 (en) * | 2003-12-10 | 2005-08-25 | Cedric Meyer | Device for assembly of several elements by riveting and procedure for assembly of panels especially for aircraft fuselages by means of said device |
US20080067289A1 (en) * | 2006-09-15 | 2008-03-20 | Airbus France | Splice plate for stringers and orbital joining device |
US20090020646A1 (en) * | 2007-04-25 | 2009-01-22 | Airbus France | Assembly of panels of an airplane fuselage |
Also Published As
Publication number | Publication date |
---|---|
FR2947523A1 (fr) | 2011-01-07 |
US20120104170A1 (en) | 2012-05-03 |
CN102612466B (zh) | 2015-08-05 |
FR2947523B1 (fr) | 2011-07-22 |
RU2560949C2 (ru) | 2015-08-20 |
RU2012103607A (ru) | 2013-08-10 |
EP2448814A1 (fr) | 2012-05-09 |
US9371125B2 (en) | 2016-06-21 |
CN102612466A (zh) | 2012-07-25 |
BR112012000048A2 (pt) | 2016-03-15 |
WO2011001050A1 (fr) | 2011-01-06 |
CA2766007C (fr) | 2017-10-17 |
CA2766007A1 (fr) | 2011-01-06 |
EP2448814B1 (fr) | 2018-09-05 |
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