JP2012101787A5 - - Google Patents

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Publication number
JP2012101787A5
JP2012101787A5 JP2011245427A JP2011245427A JP2012101787A5 JP 2012101787 A5 JP2012101787 A5 JP 2012101787A5 JP 2011245427 A JP2011245427 A JP 2011245427A JP 2011245427 A JP2011245427 A JP 2011245427A JP 2012101787 A5 JP2012101787 A5 JP 2012101787A5
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JP
Japan
Prior art keywords
fuselage
skin
composite
fuselage structure
frame members
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.)
Granted
Application number
JP2011245427A
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English (en)
Japanese (ja)
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JP2012101787A (ja
JP6039175B2 (ja
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Publication date
Priority claimed from US12/944,113 external-priority patent/US8752791B2/en
Application filed filed Critical
Publication of JP2012101787A publication Critical patent/JP2012101787A/ja
Publication of JP2012101787A5 publication Critical patent/JP2012101787A5/ja
Application granted granted Critical
Publication of JP6039175B2 publication Critical patent/JP6039175B2/ja
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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JP2011245427A 2010-11-11 2011-11-09 多機能頂部を用いる胴体とその作製方法 Active JP6039175B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/944,113 2010-11-11
US12/944,113 US8752791B2 (en) 2010-11-11 2010-11-11 Fuselage employing multifunctional crown and method of making the same

Publications (3)

Publication Number Publication Date
JP2012101787A JP2012101787A (ja) 2012-05-31
JP2012101787A5 true JP2012101787A5 (enExample) 2014-11-27
JP6039175B2 JP6039175B2 (ja) 2016-12-07

Family

ID=44905700

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2011245427A Active JP6039175B2 (ja) 2010-11-11 2011-11-09 多機能頂部を用いる胴体とその作製方法

Country Status (4)

Country Link
US (1) US8752791B2 (enExample)
EP (1) EP2452872B1 (enExample)
JP (1) JP6039175B2 (enExample)
CN (1) CN102530234B (enExample)

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DE102007050422B4 (de) * 2007-10-22 2012-03-08 Airbus Operations Gmbh Flugzeugkomponentenmontagesystem
USD732459S1 (en) * 2013-05-21 2015-06-23 Airbus Corporate Jet Centre Aircraft cabin
EP2979975B1 (en) * 2014-07-30 2017-09-27 AIRBUS HELICOPTERS DEUTSCHLAND GmbH An aircraft with a framework structure that comprises at least one hollow frame.
CA2979158A1 (en) * 2015-03-23 2016-09-29 Bombardier Inc. Simulation of loads on aerostructures during aircraft assembly
WO2018061281A1 (ja) 2016-09-29 2018-04-05 株式会社Ｓｕｂａｒｕ 複合材構造体及び複合材構造体の製造方法
CN106596003B (zh) * 2016-11-29 2019-04-23 中国航空工业集团公司沈阳飞机设计研究所 一种复合材料飞机机身段充压试验方法
DE102017112594A1 (de) * 2017-06-08 2018-12-13 Airbus Operations Gmbh Luftverteilungssystem für eine Flugzeugkabine
US11220353B2 (en) * 2019-04-18 2022-01-11 The Boeing Company Method of fabricating a composite structure
US11866200B2 (en) * 2020-11-18 2024-01-09 The Boeing Company Pulsed line fabrication for a fuselage using work stations
US11872780B2 (en) 2022-06-02 2024-01-16 The Boeing Company Methods and tool for cutting an uncured composite material
DE102022133280A1 (de) * 2022-12-14 2024-06-20 Airbus Operations Gmbh Bauteil mit Hohlleiter, Datenübertragungssystem und Luftfahrzeug

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04329125A (ja) * 1991-04-30 1992-11-17 Mitsubishi Heavy Ind Ltd 複合材料一体成形方法
JPH1016085A (ja) * 1996-07-04 1998-01-20 Mitsubishi Heavy Ind Ltd 航空機の胴体外板の製造方法
JP4318381B2 (ja) * 2000-04-27 2009-08-19 本田技研工業株式会社 繊維強化複合材からなる胴体構造体の製造方法、及びそれにより製造される胴体構造体
DE10154063B4 (de) * 2001-11-02 2013-11-28 Airbus Operations Gmbh Doppelwandiger Kernverbund, vorzugsweise Faserverbund
US7380752B2 (en) * 2003-10-17 2008-06-03 The Boeing Company Aircraft interior architecture
US7252267B2 (en) 2003-10-17 2007-08-07 The Boeing Company Aircraft archway architecture
US7228611B2 (en) * 2003-11-18 2007-06-12 The Boeing Company Method of transferring large uncured composite laminates
US7166251B2 (en) * 2004-12-01 2007-01-23 The Boeing Company Segmented flexible barrel lay-up mandrel
USD539210S1 (en) 2005-04-28 2007-03-27 The Boeing Company Modular archway for an aircraft
JP4800672B2 (ja) * 2005-06-09 2011-10-26 株式会社竹中工務店 経路構造
DE102005043898A1 (de) * 2005-09-14 2007-03-22 Airbus Deutschland Gmbh Fenster-Anordnung zum Einrichten größerer Flugzeugfenster
US9359061B2 (en) * 2005-10-31 2016-06-07 The Boeing Company Compliant stiffener for aircraft fuselage
DE102005054869A1 (de) * 2005-11-17 2007-05-31 Airbus Deutschland Gmbh Verfahren zur Herstellung einer Rumpfzelle eines Luftfahrzeugs
DE102006002248B4 (de) * 2006-01-17 2008-01-03 Airbus Deutschland Gmbh Strukturgebende Konstruktion für einen Flugzeugrumpf
JP2008028549A (ja) * 2006-07-19 2008-02-07 Taisei Corp 通信波搬送導波管
DE102006039292B4 (de) * 2006-08-22 2010-07-22 Airbus Deutschland Gmbh Rahmenelement, Flugzeugklimatisierungssystem sowie Verfahren zur Montage eines Rahmenelements in einem Flugzeug
US7735779B2 (en) * 2006-11-02 2010-06-15 The Boeing Company Optimized fuselage structure
US7861970B2 (en) 2006-11-02 2011-01-04 The Boeing Company Fuselage structure including an integrated fuselage stanchion
DE102007003277B4 (de) * 2007-01-23 2012-08-02 Airbus Operations Gmbh Rumpf eines Luft- oder Raumfahrzeuges in CFK-Metall Hybridbauweise mit einem Metallrahmen
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US7879276B2 (en) * 2007-11-08 2011-02-01 The Boeing Company Foam stiffened hollow composite stringer
US8040243B2 (en) 2008-11-18 2011-10-18 The Boeing Company RFID-based corrosion and moisture detection
US8421692B2 (en) * 2009-02-25 2013-04-16 The Boeing Company Transmitting power and data
US8500066B2 (en) * 2009-06-12 2013-08-06 The Boeing Company Method and apparatus for wireless aircraft communications and power system using fuselage stringers
US8570152B2 (en) * 2009-07-23 2013-10-29 The Boeing Company Method and apparatus for wireless sensing with power harvesting of a wireless signal

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