JP4990177B2 - 飛行機の翼構造 - Google Patents
飛行機の翼構造 Download PDFInfo
- Publication number
- JP4990177B2 JP4990177B2 JP2008033610A JP2008033610A JP4990177B2 JP 4990177 B2 JP4990177 B2 JP 4990177B2 JP 2008033610 A JP2008033610 A JP 2008033610A JP 2008033610 A JP2008033610 A JP 2008033610A JP 4990177 B2 JP4990177 B2 JP 4990177B2
- Authority
- JP
- Japan
- Prior art keywords
- rib
- stringer
- reinforcing
- spar
- skin
- 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
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/10—Riveting machines
- B21J15/14—Riveting machines specially adapted for riveting specific articles, e.g. brake lining machines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2215/00—Details of workpieces
- B23B2215/04—Aircraft components
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Moulding By Coating Moulds (AREA)
Description
特に、第1、第2補強ビード23A,23Bの下側の端縁を取付フランジ21e,21fのベンドラインの直上に近接して位置させたことにより、上下方向の荷重が作用したときに第1、第2補強ビード23A,23Bと取付フランジ21e,21fのベンドラインとの間の前部リブ21の撓み、あるいは取付フランジ21e,21fのベンドラインの撓みを一層効果的に抑制することができる。
14 フロントスパー(第2スパー)
19 アッパースキン(スキン)
20 ロアスキン(スキン)
20a ストリンガー
21 前部リブ(リブ)
21d ストリンガー貫通孔
21e 取付フランジ
21f 取付フランジ
21k 第1切欠き
21m 第2切欠き
21n 補強フランジ
21o 補強フランジ
21p 補強フランジ
23A 第1補強ビード(補強ビード)
23B 第2補強ビード(補強ビード)
23a 本体部
23b 屈曲部
23c 屈曲部
27 リベット
Claims (4)
- スパン方向に延びる第1、第2スパー(13,14)と、
前記第1、第2スパー(13,14)間に配置されてスパン方向に延びるストリンガー(20a)と、
コード方向に延びて前記第1、第2スパー(13,14)間を接続するリブ(21)と、
前記第1、第2スパー(13,14)、前記ストリンガー(20a)および前記リブ(21)の上面および下面を覆うスキン(19,20)とを備え、
前記リブ(21)の上縁および下縁の少なくとも一方には、前記スキン(20)にリベット(27)で締結される取付フランジ(21e,21f)が形成されるとともに、前記取付フランジ(21e,21f)を切欠いて前記ストリンガー(20a)が貫通するストリンガー貫通孔(21d)が形成され、
かつ前記リブ(21)の上縁および下縁の少なくとも一方の前端および後端には、前記第1、第2スパー(13,14)および前記スキン(20)の接続部に臨む第1、第2切欠き(21k,21m)が形成された飛行機の翼構造であって、
前記リブ(21)は金属板をプレス成形して構成され、前記取付フランジ(21e,21f)に沿って形成された補強ビード(23A,23B)を備えるとともに、前記ストリンガー貫通孔(21d)および前記第1、第2切欠き(21k,21m)の縁からスパン方向に延びて前記取付フランジ(21e,21f)に途切れることなく一体に連なる補強フランジ(21n,21o,21p)を備えることを特徴とする飛行機の翼構造。 - 前記補強ビード(23A,23B)の下側の端縁を前記取付フランジ(21e,21f)のベンドラインの直上に近接して位置させたことを特徴とする、請求項1に記載の飛行機の翼構造。
- 前記補強フランジ(21n,21o,21p)のスパン方向の高さは前記取付フランジ(21e,21f)のスパン方向の高さよりも低いことを特徴とする、請求項1に記載の飛行機の翼構造。
- 前記補強ビード(23A,23B)は、その本体部(23a)の端部から前記ストリンガー貫通孔(21d)あるいは前記第1、第2切欠き(21k,21m)に沿って屈曲する屈曲部(23b,23c)を備えることを特徴とする、請求項1に記載の飛行機の翼構造。
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2008033610A JP4990177B2 (ja) | 2008-02-14 | 2008-02-14 | 飛行機の翼構造 |
US12/368,397 US8056859B2 (en) | 2008-02-14 | 2009-02-10 | Airplane wing structure |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2008033610A JP4990177B2 (ja) | 2008-02-14 | 2008-02-14 | 飛行機の翼構造 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2009190574A JP2009190574A (ja) | 2009-08-27 |
JP4990177B2 true JP4990177B2 (ja) | 2012-08-01 |
Family
ID=41072979
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008033610A Expired - Fee Related JP4990177B2 (ja) | 2008-02-14 | 2008-02-14 | 飛行機の翼構造 |
Country Status (2)
Country | Link |
---|---|
US (1) | US8056859B2 (ja) |
JP (1) | JP4990177B2 (ja) |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0606079D0 (en) * | 2006-03-27 | 2006-05-03 | Airbus Uk Ltd | Aircraft component |
GB0611875D0 (en) * | 2006-06-15 | 2006-07-26 | Airbus Uk Ltd | A stringer for an aircraft wing and a method of forming thereof |
US8910908B2 (en) * | 2006-10-31 | 2014-12-16 | Airbus Operations Gmbh | Two-piece stiffening element |
KR20130016336A (ko) * | 2010-04-12 | 2013-02-14 | 에어버스 오퍼레이션즈 리미티드 | 항공기 고정 날개 |
GB201016278D0 (en) * | 2010-09-28 | 2010-11-10 | Airbus Operations Ltd | Aircraft rib-spar joint |
US8578609B2 (en) * | 2010-10-27 | 2013-11-12 | Airbus Operations S.L. | Manufacturing procedure of a part made out of a composite material introducing a geometric change in one of its faces |
DE102011007235A1 (de) * | 2011-04-12 | 2012-10-18 | Airbus Operations Gmbh | Verfahren und Vorrichtung zur Herstellung eines Faserverbundbauteils und Faserverbundbauteil |
US9341207B2 (en) | 2013-07-30 | 2016-05-17 | Gulfstream Aerospace Corporation | Web component and method of making a web component |
GB2517954B (en) * | 2013-09-05 | 2018-07-04 | Airbus Operations Ltd | Repair of a damaged composite aircraft wing |
US10005565B2 (en) * | 2014-04-29 | 2018-06-26 | Embraer S.A. | Stabilized wing rib components and methods for assembling such stabilized wing rib components with at least one other aircraft airfoil structural component |
GB2528078B (en) * | 2014-07-08 | 2020-07-29 | Airbus Operations Ltd | Structure |
GB2528076B (en) * | 2014-07-08 | 2020-07-29 | Airbus Operations Ltd | Rib foot |
GB2528080A (en) * | 2014-07-08 | 2016-01-13 | Airbus Operations Ltd | Structure |
CN105539812A (zh) * | 2014-10-28 | 2016-05-04 | 中国航空工业集团公司西安飞机设计研究所 | 一种机翼翼梁对接接头 |
US9944402B2 (en) | 2015-06-03 | 2018-04-17 | The Boeing Company | Quick installation fuel dam |
CN106314759A (zh) * | 2016-09-06 | 2017-01-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | 一种飞机机翼的翼梁连接结构 |
JP6638679B2 (ja) * | 2017-03-23 | 2020-01-29 | テイ・エス テック株式会社 | シートバックフレームの補強構造 |
US11059561B2 (en) * | 2018-01-14 | 2021-07-13 | Textron Innovations Inc. | Torque box rib and method for installation thereof |
US11273899B2 (en) * | 2018-01-25 | 2022-03-15 | The Boeing Company | Wing rib, wing having wing rib, and method for manufacturing the same |
GB2575102A (en) * | 2018-06-29 | 2020-01-01 | Airbus Operations Ltd | Duct stringer with bulkhead |
US11180238B2 (en) * | 2018-11-19 | 2021-11-23 | The Boeing Company | Shear ties for aircraft wing |
CN109533278B (zh) * | 2018-12-04 | 2024-03-19 | 南京航空航天大学 | 可实现均匀伸缩变形的翼肋结构 |
CN111597632B (zh) * | 2020-05-08 | 2022-08-19 | 西北工业大学 | 一种基于刚性多连杆机构驱动的变形翼结构设计方法 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2483134A (en) * | 1945-05-01 | 1949-09-27 | Republic Aviat Corp | Airfoil |
JPH07172395A (ja) * | 1993-12-20 | 1995-07-11 | Mitsubishi Heavy Ind Ltd | 航空機のインテグラルタンク |
JP3536448B2 (ja) * | 1995-07-18 | 2004-06-07 | 日産自動車株式会社 | 燃料タンク |
AU2584497A (en) * | 1996-03-22 | 1997-10-10 | Boeing Company, The | Determinant spar assembly |
JPH1199993A (ja) * | 1997-09-29 | 1999-04-13 | Fuji Heavy Ind Ltd | 複合材翼構造およびその製造方法 |
JP4545339B2 (ja) * | 2001-04-05 | 2010-09-15 | 富士重工業株式会社 | 複合材翼およびその製造方法 |
JP4574086B2 (ja) * | 2001-09-03 | 2010-11-04 | 富士重工業株式会社 | 複合材翼の製造方法および複合材翼 |
JP2004025946A (ja) * | 2002-06-24 | 2004-01-29 | Honda Motor Co Ltd | 航空機の翼構造 |
JP4657189B2 (ja) * | 2006-11-02 | 2011-03-23 | 本田技研工業株式会社 | 飛行機の翼構造 |
-
2008
- 2008-02-14 JP JP2008033610A patent/JP4990177B2/ja not_active Expired - Fee Related
-
2009
- 2009-02-10 US US12/368,397 patent/US8056859B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US8056859B2 (en) | 2011-11-15 |
JP2009190574A (ja) | 2009-08-27 |
US20090314892A1 (en) | 2009-12-24 |
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