JP4657194B2 - 前縁スキンの段差調整構造および前縁スキンの組付方法 - Google Patents
前縁スキンの段差調整構造および前縁スキンの組付方法 Download PDFInfo
- Publication number
- JP4657194B2 JP4657194B2 JP2006312660A JP2006312660A JP4657194B2 JP 4657194 B2 JP4657194 B2 JP 4657194B2 JP 2006312660 A JP2006312660 A JP 2006312660A JP 2006312660 A JP2006312660 A JP 2006312660A JP 4657194 B2 JP4657194 B2 JP 4657194B2
- Authority
- JP
- Japan
- Prior art keywords
- skin
- spar
- edge skin
- front edge
- leading edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49764—Method of mechanical manufacture with testing or indicating
- Y10T29/49771—Quantitative measuring or gauging
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Description
14 フロントスパー(スパー)
14b 前部フランジ(フランジ)
14f 雌ねじ
17 アッパースキン(本体スキン)
18 ロアスキン(本体スキン)
19 前縁スキン
22 ファスナー
23 ファスナー
23 ファスナー
25 段差調整部材
25a シム部
25b 弾性支持部
26 段差調整部材
26a 雄ねじ
26b ファスナー孔
26c 端面
Claims (4)
- 飛行機の翼(12)のスパー(14)に本体スキン(17,18)および前縁スキン(19)を突き合わせてファスナー(22,23,24)で固定する際に、本体スキン(17,18)の前端と前縁スキン(19)の後端との間の段差を調整すべく、スパー(14)に段差調整部材(25)を介して前縁スキン(19)の後端を固定する前縁スキンの段差調整構造において、
前記段差調整部材(25)は、板材をJ字状あるいはU字状に形成してシム部(25a)および弾性支持部(25b)が相互に対向するように構成され、シム部(25a)および弾性支持部(25b)でスパー(14)のフランジ(14b)を弾性的に挟持するように装着され、フランジ(14b)との間にシム部(25a)を介在させた状態で前縁スキン(19)がフランジ(14b)にファスナー(22)で固定されることを特徴とする前縁スキンの段差調整構造。 - 飛行機の翼(12)のスパー(14)に本体スキン(17,18)および前縁スキン(19)を突き合わせてファスナー(22,23,24)で固定する際に、本体スキン(17,18)の前端と前縁スキン(19)の後端との間の段差を調整すべく、スパー(14)に段差調整部材(26)を介して前縁スキン(19)の後端を固定する前縁スキンの段差調整構造において、
前記段差調整部材(26)は、スパー(14)のフランジ(14b)に形成した雌ねじ(14f)に任意量螺合可能な雄ねじ(26a)が外周面に形成されて中心をファスナー孔(26b)が貫通する円筒状の部材であり、フランジ(14b)の表面から所定量突出する段差調整部材(26)の端面(26c)に前縁スキン(19)当接させた状態で、ファスナー孔(26b)を貫通するファスナー(22)で前縁スキン(19)がフランジ(14b)に固定されることを特徴とする前縁スキンの段差調整構造。 - 請求項1に記載された前縁スキンの段差調整構造を用いた前縁スキンの組付方法であって、
本体スキン(17,18)が固定されたスパー(14)に前縁スキン(19)を仮組みする工程と、
翼(12)のスパン方向の複数個所で本体スキン(17,18)の前端と前縁スキン(19)の後端との間の段差を測定する工程と、
前記段差に応じた厚さのシム部(25a)を有する段差調整部材(25)を選択する工程と、
翼(12)のスパン方向の複数個所で選択した段差調整部材(25)をスパー(14)に仮装着する工程と、
仮装着した段差調整部材(25)を介してスパー(14)に前縁スキン(19)を装着してファスナー(22)で本組みする工程と、
を含むことを特徴とする前縁スキンの組付方法。 - 請求項2に記載された前縁スキンの段差調整構造を用いた前縁スキンの組付方法であって、
本体スキン(17,18)が固定されたスパー(14)に前縁スキン(19)を仮組みする工程と、
翼(12)のスパン方向の複数個所で本体スキン(17,18)の前端と前縁スキン(19)の後端との間の段差を測定する工程と、
翼(12)のスパン方向の複数個所でスパー(14)に段差調整部材(26)を装着する工程と、
スパー(14)の表面からの段差調整部材(26)の端面(26c)の突出量を前記段差に応じて調整する工程と、
段差調整部材(26)を介してスパー(14)に前縁スキン(19)を装着してファスナー(22)で本組みする工程と、
を含むことを特徴とする前縁スキンの組付方法。
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2006312660A JP4657194B2 (ja) | 2006-11-20 | 2006-11-20 | 前縁スキンの段差調整構造および前縁スキンの組付方法 |
US11/984,539 US7992822B2 (en) | 2006-11-20 | 2007-11-19 | Leading edge skin height difference adjusting structure and method of assembling leading edge skin |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2006312660A JP4657194B2 (ja) | 2006-11-20 | 2006-11-20 | 前縁スキンの段差調整構造および前縁スキンの組付方法 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008126793A JP2008126793A (ja) | 2008-06-05 |
JP4657194B2 true JP4657194B2 (ja) | 2011-03-23 |
Family
ID=39553076
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2006312660A Expired - Fee Related JP4657194B2 (ja) | 2006-11-20 | 2006-11-20 | 前縁スキンの段差調整構造および前縁スキンの組付方法 |
Country Status (2)
Country | Link |
---|---|
US (1) | US7992822B2 (ja) |
JP (1) | JP4657194B2 (ja) |
Families Citing this family (29)
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GB0525896D0 (en) * | 2005-12-20 | 2006-02-01 | Airbus Uk Ltd | A joint for use in aircraft construction |
GB0805963D0 (en) * | 2008-04-02 | 2008-05-07 | Airbus Uk Ltd | Aircraft structure |
US9586367B2 (en) * | 2008-11-04 | 2017-03-07 | Lockheed Martin Corporation | Composite laminate thickness compensation |
GB0901640D0 (en) * | 2009-02-03 | 2009-03-11 | Airbus Uk Ltd | Joint |
GB0905818D0 (en) * | 2009-04-06 | 2009-05-20 | Airbus Uk Ltd | Coupling assembly |
WO2011043346A1 (ja) * | 2009-10-08 | 2011-04-14 | 三菱重工業株式会社 | 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 |
US9186849B2 (en) | 2009-12-10 | 2015-11-17 | Michael Spellman | Composite part manufacturing compensation system and method |
GB201008858D0 (en) * | 2010-05-27 | 2010-07-14 | Airbus Uk Ltd | Packer assembly |
ES2396327B1 (es) * | 2010-06-10 | 2014-02-06 | Airbus Operations, S.L. | Procedimiento para la fabricación de piezas grandes de material compuesto controlando el espesor de sus bordes |
DE102010026839A1 (de) | 2010-07-12 | 2012-01-12 | Airbus Operations Gmbh | Aerodynamische Verkleidungsvorrichtung, Flugzeug-Bauteilanordnung mit einer aerodynamischen Verkleidungsvorrichtung sowie Verfahren zur Montage eines solchen Verkleidungsteils |
US8752795B2 (en) * | 2010-11-23 | 2014-06-17 | John Ralph Stewart, III | Inlet nose cowl with a locally thickened fastening portion to enable an uninterrupted airflow surface |
ES2396881B1 (es) * | 2010-11-30 | 2014-01-29 | Airbus Operations, S.L. | Disposición de interfaz entre dos componentes de una estructura de una aeronave usando una pieza de sellado. |
DE102011108883B4 (de) * | 2011-07-28 | 2017-06-14 | Airbus Operations Gmbh | Strömungskörper mit einem Basiskörper und einer Vorderkante |
GB201120707D0 (en) | 2011-12-01 | 2012-01-11 | Airbus Operations Ltd | Leading edge structure |
ES2426111B1 (es) * | 2012-04-17 | 2015-03-24 | Airbus Operations S.L. | Interfaz para superficie de sustentación de aeronave |
US9676469B2 (en) * | 2014-04-10 | 2017-06-13 | Lockheed Martin Corporation | System and method for fastening structures |
US9896190B1 (en) * | 2014-05-07 | 2018-02-20 | The Boeing Company | Wing leading edge architecture suitable for laminar flow |
US10329009B2 (en) * | 2014-09-17 | 2019-06-25 | The Boeing Company | Composite wing edge attachment and method |
EP3199455B1 (en) * | 2016-01-29 | 2020-04-22 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Rotary aircraft with an interface frame joining the fuselage tail boom and the tail cone |
CN105710270B (zh) * | 2016-04-01 | 2018-03-02 | 中航飞机股份有限公司西安飞机分公司 | 一种消除飞机薄腹板铆接间隙的工艺方法 |
GB2550175A (en) * | 2016-05-11 | 2017-11-15 | Airbus Operations Ltd | Aircraft joint |
US10266248B2 (en) * | 2016-07-20 | 2019-04-23 | The Boeing Company | Leading edge systems and methods for aerospace vehicles |
GB201719790D0 (en) * | 2017-11-28 | 2018-01-10 | Airbus Operations Gmbh | Aircraft joint with a curable composite bushing |
JP6662938B2 (ja) * | 2018-03-30 | 2020-03-11 | 株式会社ホンダアクセス | 取付構造及び取付方法 |
CN109372884B (zh) * | 2018-12-07 | 2023-08-25 | 江西洪都航空工业集团有限责任公司 | 一种旋转自拉式骨架垫片 |
US11383820B2 (en) * | 2019-06-11 | 2022-07-12 | The Boeing Company | Aerodynamic surface lap splice |
CN111069514B (zh) * | 2019-12-31 | 2021-04-13 | 湖北三江航天红阳机电有限公司 | 一种空气舵铆接工艺方法 |
US11325691B2 (en) * | 2020-02-06 | 2022-05-10 | The Boeing Company | Joint assembly having shimmed bosses and associated method of making the joint assembly |
CN113460287A (zh) * | 2021-09-03 | 2021-10-01 | 中国商用飞机有限责任公司 | 缝翼滑轨组件及其组装方法 |
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US5845872A (en) * | 1994-06-02 | 1998-12-08 | British Aerospace Plc | Method and arrangement for fastening composite aircraft skins |
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US3217773A (en) * | 1964-08-24 | 1965-11-16 | Bishop & Babcock Corp | Sheet metal clip with nut means and spacing embossures |
US6073899A (en) * | 1998-08-18 | 2000-06-13 | Omrani; Shahram Shawn | Universal tissue box hanger |
US7374141B2 (en) * | 2003-09-24 | 2008-05-20 | David Holden | J-clip |
GB0525896D0 (en) * | 2005-12-20 | 2006-02-01 | Airbus Uk Ltd | A joint for use in aircraft construction |
-
2006
- 2006-11-20 JP JP2006312660A patent/JP4657194B2/ja not_active Expired - Fee Related
-
2007
- 2007-11-19 US US11/984,539 patent/US7992822B2/en not_active Expired - Fee Related
Patent Citations (6)
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US2496024A (en) * | 1946-03-12 | 1950-01-31 | Grumman Aircraft Engineering C | Airplane wing structure |
GB845138A (en) * | 1957-02-20 | 1960-08-17 | Konink Nl Vliegtuigenfabriek F | Method for the manufacture of an aircraft part, and aircraft part made according to this method |
US5845872A (en) * | 1994-06-02 | 1998-12-08 | British Aerospace Plc | Method and arrangement for fastening composite aircraft skins |
JP2004520209A (ja) * | 1999-08-21 | 2004-07-08 | ビ−エイイ− システムズ パブリック リミテッド カンパニ− | 構造物の製造とアッセンブリィ |
JP2004025946A (ja) * | 2002-06-24 | 2004-01-29 | Honda Motor Co Ltd | 航空機の翼構造 |
US20050103942A1 (en) * | 2003-07-23 | 2005-05-19 | Abrams Mark D. | Composite seal and window assembly |
Also Published As
Publication number | Publication date |
---|---|
US20080164376A1 (en) | 2008-07-10 |
US7992822B2 (en) | 2011-08-09 |
JP2008126793A (ja) | 2008-06-05 |
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