US20090266936A1 - Aircraft fuselage structural components and methods of making same - Google Patents

Aircraft fuselage structural components and methods of making same Download PDF

Info

Publication number
US20090266936A1
US20090266936A1 US12/111,825 US11182508A US2009266936A1 US 20090266936 A1 US20090266936 A1 US 20090266936A1 US 11182508 A US11182508 A US 11182508A US 2009266936 A1 US2009266936 A1 US 2009266936A1
Authority
US
United States
Prior art keywords
friction stir
rigidly
reinforcement
frame
stir weld
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.)
Abandoned
Application number
US12/111,825
Other languages
English (en)
Inventor
Fernando Ferreira Fernandez
Sadao Takanashi
Lucio Camargo Fortes
Marcio Cruz
Marcelo Galvao do Prado
Clovis Augusto Eca Ferreira
Jose Donizette Aguiar
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Embraer SA
Original Assignee
Embraer SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Embraer SA filed Critical Embraer SA
Priority to US12/111,825 priority Critical patent/US20090266936A1/en
Assigned to EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A. reassignment EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AGUIAR, JOSE DONIZETTE, CRUZ, MARCIO, DO PRADO, MARCELO GALVAO, ECA FERREIRA, CLOVIS AUGUSTO, FERNANDEZ, FERNANDO FERREIRA, FORTES, LUCIO CAMARGO, TAKANASHI, SADAO
Priority to BRPI0822244-4A priority patent/BRPI0822244B1/pt
Priority to EP08874076.6A priority patent/EP2280864B1/en
Priority to PCT/BR2008/000376 priority patent/WO2009132402A2/en
Publication of US20090266936A1 publication Critical patent/US20090266936A1/en
Assigned to Embraer S.A. reassignment Embraer S.A. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A.
Priority to US13/645,398 priority patent/US8844871B2/en
Abandoned legal-status Critical Current

Links

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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic 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
    • 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
    • Y10T29/49616—Structural member making
    • Y10T29/49622—Vehicular structural member making

Definitions

  • the present invention relates generally to structural components for aircraft fuselages and methods of making the same.
  • the present invention relates to structural panels for aircraft fuselages formed of transversal frame members and longitudinal stringers whereby stringer holes through the frame members are structurally reinforced.
  • An aircraft fuselage is typically constructed as a series of longitudinally spaced circumferential frame members which define the general transversal (cross-sectional) fuselage shape, and a series of spaced stringer members running longitudinally with respect to the aircraft fuselage which contribute to the stiffness of the external skin.
  • the frames and stringers constitute a robust internal structure that provides support to the external fuselage skin.
  • the fuselage skin covers various members of the internal support structure and is typically formed of a single piece or separate pieces of relatively thin material joined to the internal frames and stingers with skin splice straps.
  • the frames and stringers are attached to the skin using different techniques.
  • the stringers are installed to the skin in an earlier stage of the manufacturing cycle, using rivets and/or adhesives, to form stiffened skin panels.
  • the stiffened skin panels are spliced and attached to the frames.
  • the corresponding segments of the frames may be installed with each stiffened skin panel, forming framed stiffened skin panels.
  • the framed stiffened skin panels are assembled, and the skins and frames spliced to form a fuselage section. These stages are repeated until the fuselage is constructed.
  • the present invention is embodied in aircraft fuselage structures having reinforcement members in the vicinity of the stringer openings formed in frame members and rigidly lap joined to a surface region of the frame members by a friction stir weld region (e.g., a weld region formed by a friction stir welding process).
  • a friction stir weld region e.g., a weld region formed by a friction stir welding process
  • an aircraft fuselage structural component which comprises plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, and plural longitudinally oriented stringers positioned within respective ones of the stringer holes of the frame member.
  • the reinforcement members are most preferably formed of the same metal as the frame members to whom they are joined.
  • the reinforcement members are lap joined to corresponding surfaces of frame members in a vicinity of the stringer holes in such a way that the reinforcement members are joined rigidly to the corresponding surfaces of the frame members by a friction stir weld region.
  • Certain embodiments of the invention will include reinforcement members which comprise a continuous or discontinuous structure.
  • a fuselage skin may be attached to the frame members and/or stringers.
  • the friction stir weld region is a continuous friction stir weld line.
  • spot and/or discontinuous friction stir welds may be employed.
  • the reinforcement members comprise an L-shaped flanged structure having one flange rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region.
  • the reinforcement members comprise one of a curved plate rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region.
  • the reinforcement members may be in the form of a reverse S-shaped structural member having a flange rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region.
  • the flange of the S-shaped structural member may be rigidly lap joined to flange of the frame member.
  • the flange of the S-shaped structural member may be rigidly lap joined to a center span of the frame member.
  • the reinforcement members may alternatively or additionally comprise a reinforcement bar positioned laterally of a stringer opening and rigidly lap joined to a corresponding surface region of the frame member by the friction stir weld region.
  • methods of making an aircraft fuselage structural component comprise providing plural longitudinally spaced-apart frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a plurality of stringer holes therethrough, positioning plural longitudinally oriented stringers within respective ones of the stringer holes of the frame members.
  • stringer holes are structurally reinforced by lap joining reinforcement members to corresponding surfaces of frame members in the vicinity of the stringer holes.
  • the reinforcement members are friction stir welded rigidly to the corresponding surfaces of the frame members to form a friction stir weld region therebetween.
  • FIG. 1 is a perspective view of an aircraft which includes a structural panel in accordance with an embodiment of the present invention
  • FIG. 2 is more detailed perspective view of a structural panel portion in accordance with an embodiment of the present invention.
  • FIG. 3 is a cross-sectional elevational view of the structural panel depicted in FIG. 2 as taken along line 3 - 3 therein;
  • FIGS. 4-7 are cross-sectional elevational views comprising other exemplary embodiments of a structural panel in accordance with the present invention.
  • FIG. 8 is a perspective view of another structural panel portion in accordance with another embodiment of the present invention.
  • FIG. 9 is an enlarged cross-sectional view of the aircraft structural panel shown in FIG. 8 taken along line 9 - 9 therein.
  • FIG. 1 depicts an aircraft 10 which includes a fuselage 12 constructed of a number of conjoined structural panels 12 a which embody the present invention. It is understood of course that FIG. 1 only shows a representative number of such panels 12 a. Thus, substantially the entirety of the fuselage will be formed of panels 12 a joined together.
  • each structural panel 12 a is formed of longitudinally spaced-apart circumferential frame members 14 which define the general transversal (cross-sectional) shape of the fuselage 12 , and a series of spaced apart stringer members 16 running longitudinally with respect to the aircraft fuselage 12 .
  • the frame and stringer members 14 , 16 are attached directly to the fuselage skin 18 by any suitable means, such as riveting, bonding and the like.
  • a stringer opening 20 is defined in the frame members 14 in registry with the location of individual stringer members 16 so as to allow the latter to pass physically through the former.
  • a reinforcement member 22 is overlapped with a corresponding surface region of the frame member 14 in the vicinity of the opening 20 thereby forming a lap joint.
  • the reinforcement member 22 is shown in FIG. 3 in the form of a flanged L-shaped structure, but as will become evident from the discussion below, other structural forms of reinforcement members 22 are equally effective.
  • One flange of the reinforcement member 22 is thus lap joined with and rigidly affixed to an overlapped surface region of the frame member 14 by means of a friction stir welding (FSW) process along a lap joined weld region 24 .
  • the other flange of the reinforcement member extends outwardly at right angle from the overlapped surface region of the frame member 14 . In such a manner, structural reinforcement is provided to the frame member 14 in the vicinity of the stringer opening 20 .
  • the reinforcement members 22 may be discontinuous as shown in solid line in FIGS. 2 and 3 in which case they are located superiorly adjacent to a respective opening 20 .
  • the reinforcement member 22 may be a continuous structural member coextensive with the frame members 14 .
  • the friction stir weld region 24 is a continuous weld which may or may not include a corresponding FSW process tool exit hole.
  • the friction stir weld region 24 is formed without a tool exit hole, that is, having the tool exit hole filled (e.g., as disclosed in U.S. Pat. No. 6,722,556, the entire content of which is expressly incorporated hereinto by reference).
  • Friction stir spot welding FSSW
  • SFSW segmented friction stir welding
  • Suitable FSW processes to form lap joined friction stir weld regions are more fully disclosed in U.S. Pat. Nos. 7,225,966 and 7,240,821, the entire content of each being expressly incorporated hereinto by reference.
  • FIGS. 4-9 Alternative embodiments of frame reinforcement structures are depicted in accompanying FIGS. 4-9 .
  • the reinforcement member 22 a is lap joined to the surface of the frame member 14 a in the form of a curved plate superiorly adjacent to the frame opening 20 .
  • a centrally located lap joined friction stir weld region 24 a thus rigidly joins the reinforcement member 22 a to a surface region of the frame member 14 a.
  • the frame member 14 b has a generally S-shaped cross-section (as compared to the generally C-shaped cross-section of frame member 14 depicted in FIGS. 2 and 3 ).
  • a mirror image (reverse) S-shaped cross-section reinforcement member 22 b is positioned above the frame member 14 b and includes a flange surface region lap joined by means of a FSW process to an overlapped flange surface region of the frame member 14 b to thereby form a friction stir weld region 24 b.
  • a frame member 14 c having a generally C-shaped cross-section includes a reinforcement bar 22 c lap joined to a surface thereof.
  • the thus lap joined reinforcement bar 22 c and frame member 14 c are rigidly joined to one another laterally adjacent the stringer hole 20 (not shown in FIG. 6 , but see FIG. 3 for reference).
  • FIG. 7 includes a cross-sectionally reverse S-shaped reinforcement member 22 d overlapped with a center span region of a cross-sectionally reverse C-shaped frame member 14 d by means of a lap joined friction stir weld region 24 b formed with a FSW process.
  • the structural panel 12 a′ depicted in accompanying FIG. 8 is formed of longitudinally spaced-apart frame members 14 e defining respective stringer openings through which respective longitudinal stringers 16 pass.
  • the frame members 14 e and stringers 16 are attached to the fuselage skin 18 by any suitable means, such as riveting, bonding and the like.
  • the frame members 14 e are most preferably a C-shaped structural element.
  • a continuous reinforcement bar 25 is rigidly attached to an inner surface of the frame member 14 e by means of a FSW process to thereby form a friction stir weld region 24 e.
  • the stringer opening through which the frame member 14 e passes is structurally reinforced by the reinforcement bar 25 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
US12/111,825 2008-04-29 2008-04-29 Aircraft fuselage structural components and methods of making same Abandoned US20090266936A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US12/111,825 US20090266936A1 (en) 2008-04-29 2008-04-29 Aircraft fuselage structural components and methods of making same
BRPI0822244-4A BRPI0822244B1 (pt) 2008-04-29 2008-12-05 'componentes estruturais de fuselagem de aeronave e método de produzir os mesmos
EP08874076.6A EP2280864B1 (en) 2008-04-29 2008-12-05 Aircraft fuselage structural components and methods of making same
PCT/BR2008/000376 WO2009132402A2 (en) 2008-04-29 2008-12-05 Aircraft fuselage structural components and methods of making same
US13/645,398 US8844871B2 (en) 2008-04-29 2012-10-04 Aircraft fuselage structural components and methods of making same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/111,825 US20090266936A1 (en) 2008-04-29 2008-04-29 Aircraft fuselage structural components and methods of making same

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US13/645,398 Division US8844871B2 (en) 2008-04-29 2012-10-04 Aircraft fuselage structural components and methods of making same

Publications (1)

Publication Number Publication Date
US20090266936A1 true US20090266936A1 (en) 2009-10-29

Family

ID=41214045

Family Applications (2)

Application Number Title Priority Date Filing Date
US12/111,825 Abandoned US20090266936A1 (en) 2008-04-29 2008-04-29 Aircraft fuselage structural components and methods of making same
US13/645,398 Active US8844871B2 (en) 2008-04-29 2012-10-04 Aircraft fuselage structural components and methods of making same

Family Applications After (1)

Application Number Title Priority Date Filing Date
US13/645,398 Active US8844871B2 (en) 2008-04-29 2012-10-04 Aircraft fuselage structural components and methods of making same

Country Status (4)

Country Link
US (2) US20090266936A1 (pt)
EP (1) EP2280864B1 (pt)
BR (1) BRPI0822244B1 (pt)
WO (1) WO2009132402A2 (pt)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090294018A1 (en) * 2008-05-29 2009-12-03 Airbus Deutschland Gmbh Method for joining aircraft fuselage elements by friction stir welding (FSW)
US20090311549A1 (en) * 2008-06-16 2009-12-17 Fernando Ferreira Fernandez Friction stir welding (fsw) methods and systems and friction stir welded components made thereby
US20100243804A1 (en) * 2009-03-25 2010-09-30 Airbus Espana, S.L. Joint arrangement for composite-material structural members
US20100320321A1 (en) * 2008-02-20 2010-12-23 Axel Sauermann Method for joining two fuselage sections by creating a transverse butt joint as well as transverse butt joint connection
US20130087068A1 (en) * 2010-06-04 2013-04-11 Tangshan Railway Vehicle Co., Ltd Driver's cab of magnetically levitated train and manufacturing method thereof
EP2749491A1 (en) * 2012-12-28 2014-07-02 Airbus Operations, S.L. Aircraft structure with integrated reinforcing elements
WO2015094059A1 (en) * 2013-12-20 2015-06-25 Saab Ab Stiffening element and reinforced structure
US20150336656A1 (en) * 2014-04-10 2015-11-26 The Boeing Company Vent stringer fitting
US20160052617A1 (en) * 2014-08-20 2016-02-25 The Boeing Company Hat stringer closeout fitting and method of making same
US20160075451A1 (en) * 2014-09-17 2016-03-17 The Boeing Company Fuselage Manufacturing System
US20160074926A1 (en) * 2014-09-17 2016-03-17 The Boeing Company Fuselage Manufacturing System
US20160184921A1 (en) * 2014-12-26 2016-06-30 Toyota Jidosha Kabushiki Kaisha Friction stir spot welding structure
EP3216691A1 (en) * 2016-03-07 2017-09-13 Airbus Operations GmbH Airframe component and methods for manufacturing an airframe component
US9927227B2 (en) 2014-09-17 2018-03-27 The Boeing Company Metrology system for generating measurements of fuselage sections
US10220935B2 (en) * 2016-09-13 2019-03-05 The Boeing Company Open-channel stiffener
CN112763166A (zh) * 2020-12-29 2021-05-07 中国航空工业集团公司西安飞机设计研究所 一种矩形机身舱体大开口结构侧向刚度确定方法
US11273930B2 (en) 2014-09-17 2022-03-15 The Boeing Company Cradle system for shaping fuselage sections
US11465731B2 (en) * 2018-06-29 2022-10-11 Airbus Operations Limited Duct stringer with bulkhead

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10093406B2 (en) 2014-12-10 2018-10-09 The Boeing Company Aircraft frame for tailstrike angle enhancement
DE102016218431A1 (de) 2016-09-26 2018-03-29 Ford Global Technologies, Llc Verfahren zum Reparieren fehlerhafter Verbindungen
USD1016717S1 (en) * 2022-01-31 2024-03-05 Embraer S.A. Airplane

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4310132A (en) * 1978-02-16 1982-01-12 Nasa Fuselage structure using advanced technology fiber reinforced composites
US5242523A (en) * 1992-05-14 1993-09-07 The Boeing Company Caul and method for bonding and curing intricate composite structures
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
US6302315B1 (en) * 2000-05-01 2001-10-16 General Tool Company Friction stir welding machine and method
US6511570B2 (en) * 2000-04-27 2003-01-28 Honda Giken Kogyo Kabushiki Kaisha Method for producing body structure of fiber-reinforced composite, and body structure produced thereby
US6648273B2 (en) * 2001-10-30 2003-11-18 The Boeing Company Light weight and high strength fuselage
US6722556B2 (en) * 1999-11-18 2004-04-20 Gkss Forschungszentrum Geesthacht Gmbh Method and device for joining at least two adjoining work pieces by friction welding
US20050247756A1 (en) * 2004-03-31 2005-11-10 Frazer James T Connection mechanism and method
US20060054666A1 (en) * 2004-09-14 2006-03-16 Pechiney Rhenalu Welded structural member and method and use thereof
US7074474B2 (en) * 2000-12-22 2006-07-11 Fuji Jukogyo Kabushiki Kaisha Composite material-stiffened panel and manufacturing method thereof
US7134629B2 (en) * 2004-04-06 2006-11-14 The Boeing Company Structural panels for use in aircraft fuselages and other structures
US7225966B2 (en) * 2002-08-07 2007-06-05 Eclipse Aviation Corporation Welded joints with polymer sealant
US7240821B2 (en) * 2005-07-21 2007-07-10 The Boeing Company Method for joining at least two adjoining work-pieces by friction stir and/or friction stir spot welding
US20100237195A1 (en) * 2007-09-18 2010-09-23 Airbus Operations Gmbh Structural component and method for stiffening an external skin
US7967250B2 (en) * 2008-05-12 2011-06-28 EMBRAER—Empresa Brasileira de Aeronáutica Hybrid aircraft fuselage structural components and methods of making same

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH058316A (ja) * 1991-07-05 1993-01-19 Mitsubishi Heavy Ind Ltd 複合材製構造体の製造方法
GB9713209D0 (en) * 1997-06-20 1997-08-27 British Aerospace Friction welding metal components
DE19960909A1 (de) * 1999-09-03 2001-06-21 Eads Airbus Gmbh Großflächiges Strukturbauteil für ein Flugzeug und Verfahren zur Herstellung des Strukturbauteils
DE10301445B4 (de) * 2003-01-16 2005-11-17 Airbus Deutschland Gmbh Leichtbau-Strukturbauteil insbesondere für Flugzeuge und Verfahren zu seiner Herstellung
DE102006026918B4 (de) * 2006-06-09 2017-01-12 Airbus Operations Gmbh Rumpfstruktur
FR2914622B1 (fr) * 2007-04-04 2009-05-15 Airbus France Sas Aeronef comprenant une structure assurant les fonctions structurale et electrique

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4310132A (en) * 1978-02-16 1982-01-12 Nasa Fuselage structure using advanced technology fiber reinforced composites
US5242523A (en) * 1992-05-14 1993-09-07 The Boeing Company Caul and method for bonding and curing intricate composite structures
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
US6722556B2 (en) * 1999-11-18 2004-04-20 Gkss Forschungszentrum Geesthacht Gmbh Method and device for joining at least two adjoining work pieces by friction welding
US6511570B2 (en) * 2000-04-27 2003-01-28 Honda Giken Kogyo Kabushiki Kaisha Method for producing body structure of fiber-reinforced composite, and body structure produced thereby
US6302315B1 (en) * 2000-05-01 2001-10-16 General Tool Company Friction stir welding machine and method
US7074474B2 (en) * 2000-12-22 2006-07-11 Fuji Jukogyo Kabushiki Kaisha Composite material-stiffened panel and manufacturing method thereof
US6648273B2 (en) * 2001-10-30 2003-11-18 The Boeing Company Light weight and high strength fuselage
US7225966B2 (en) * 2002-08-07 2007-06-05 Eclipse Aviation Corporation Welded joints with polymer sealant
US20050247756A1 (en) * 2004-03-31 2005-11-10 Frazer James T Connection mechanism and method
US7134629B2 (en) * 2004-04-06 2006-11-14 The Boeing Company Structural panels for use in aircraft fuselages and other structures
US20060054666A1 (en) * 2004-09-14 2006-03-16 Pechiney Rhenalu Welded structural member and method and use thereof
US7240821B2 (en) * 2005-07-21 2007-07-10 The Boeing Company Method for joining at least two adjoining work-pieces by friction stir and/or friction stir spot welding
US20100237195A1 (en) * 2007-09-18 2010-09-23 Airbus Operations Gmbh Structural component and method for stiffening an external skin
US7967250B2 (en) * 2008-05-12 2011-06-28 EMBRAER—Empresa Brasileira de Aeronáutica Hybrid aircraft fuselage structural components and methods of making same

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9187167B2 (en) * 2008-02-20 2015-11-17 Airbus Operations Gmbh Method for joining two fuselage sections by creating a transverse butt joint as well as transverse butt joint connection
US20100320321A1 (en) * 2008-02-20 2010-12-23 Axel Sauermann Method for joining two fuselage sections by creating a transverse butt joint as well as transverse butt joint connection
US8100316B2 (en) * 2008-05-29 2012-01-24 Airbus Operations Gmbh Method for joining aircraft fuselage elements by friction stir welding (fsw)
US20090294018A1 (en) * 2008-05-29 2009-12-03 Airbus Deutschland Gmbh Method for joining aircraft fuselage elements by friction stir welding (FSW)
US20090311549A1 (en) * 2008-06-16 2009-12-17 Fernando Ferreira Fernandez Friction stir welding (fsw) methods and systems and friction stir welded components made thereby
US7857191B2 (en) * 2008-06-16 2010-12-28 Embraer-Empresa Brasileira De Aeronautica S.A. Friction stir welding (FSW) methods and systems and friction stir welded components made thereby
US20100243804A1 (en) * 2009-03-25 2010-09-30 Airbus Espana, S.L. Joint arrangement for composite-material structural members
US8291671B2 (en) * 2009-03-25 2012-10-23 Airbus Operations S.L. Joint arrangement for composite-material structural members
US20130087068A1 (en) * 2010-06-04 2013-04-11 Tangshan Railway Vehicle Co., Ltd Driver's cab of magnetically levitated train and manufacturing method thereof
US9771140B2 (en) 2012-12-28 2017-09-26 Airbus Operations S.L. Aircraft structure with integrated reinforcing elements
CN103910058A (zh) * 2012-12-28 2014-07-09 空中客车西班牙运营有限责任公司 具有集成加强元件的飞行器结构
EP2749491A1 (en) * 2012-12-28 2014-07-02 Airbus Operations, S.L. Aircraft structure with integrated reinforcing elements
US9840041B2 (en) 2013-12-20 2017-12-12 Saab Ab Stiffening element and reinforced structure
WO2015094059A1 (en) * 2013-12-20 2015-06-25 Saab Ab Stiffening element and reinforced structure
US9399509B2 (en) * 2014-04-10 2016-07-26 The Boeing Company Vent stringer fitting
US20150336656A1 (en) * 2014-04-10 2015-11-26 The Boeing Company Vent stringer fitting
US9399510B2 (en) * 2014-08-20 2016-07-26 The Boeing Company Hat stringer closeout fitting and method of making same
US20160052617A1 (en) * 2014-08-20 2016-02-25 The Boeing Company Hat stringer closeout fitting and method of making same
US11131982B2 (en) * 2014-09-17 2021-09-28 The Boeing Company Fuselage manufacturing system
US9682788B2 (en) * 2014-09-17 2017-06-20 The Boeing Company Fuselage manufacturing system
US20160074926A1 (en) * 2014-09-17 2016-03-17 The Boeing Company Fuselage Manufacturing System
US20160075451A1 (en) * 2014-09-17 2016-03-17 The Boeing Company Fuselage Manufacturing System
US9927227B2 (en) 2014-09-17 2018-03-27 The Boeing Company Metrology system for generating measurements of fuselage sections
US11273930B2 (en) 2014-09-17 2022-03-15 The Boeing Company Cradle system for shaping fuselage sections
US10730641B2 (en) 2014-09-17 2020-08-04 The Boeing Company Fuselage manufacturing system
US20160184921A1 (en) * 2014-12-26 2016-06-30 Toyota Jidosha Kabushiki Kaisha Friction stir spot welding structure
US9868176B2 (en) * 2014-12-26 2018-01-16 Toyota Jidosha Kabushiki Kaisha Friction stir spot welding structure
EP3216691A1 (en) * 2016-03-07 2017-09-13 Airbus Operations GmbH Airframe component and methods for manufacturing an airframe component
US10220935B2 (en) * 2016-09-13 2019-03-05 The Boeing Company Open-channel stiffener
US11465731B2 (en) * 2018-06-29 2022-10-11 Airbus Operations Limited Duct stringer with bulkhead
CN112763166A (zh) * 2020-12-29 2021-05-07 中国航空工业集团公司西安飞机设计研究所 一种矩形机身舱体大开口结构侧向刚度确定方法

Also Published As

Publication number Publication date
EP2280864B1 (en) 2018-04-25
US8844871B2 (en) 2014-09-30
BRPI0822244A2 (pt) 2019-10-08
EP2280864A4 (en) 2013-10-09
US20130043346A1 (en) 2013-02-21
WO2009132402A2 (en) 2009-11-05
EP2280864A2 (en) 2011-02-09
WO2009132402A3 (en) 2010-02-04
BRPI0822244B1 (pt) 2020-12-01

Similar Documents

Publication Publication Date Title
US8844871B2 (en) Aircraft fuselage structural components and methods of making same
RU2479466C2 (ru) Система из двух секций фюзеляжа самолета и соединительной структуры для соединения обшивок фюзеляжа
EP2727821B1 (en) Circumference splice for joining shell structures
US8567722B2 (en) Splice and associated method for joining fuselage sections
JP6250312B2 (ja) 複合材胴体セクションをウインドウベルトに沿って連結する作業
US6595467B2 (en) Aircraft fuselage shell component with crack propagation resistance
US7875333B2 (en) Laminate sheet, in particular for fuselage skin sheets for aircrafts
US6648273B2 (en) Light weight and high strength fuselage
US8910908B2 (en) Two-piece stiffening element
US9314875B2 (en) Method for producing a composite skin in the field of aeronautics and astronautics
US9963218B2 (en) Lightweight structural panel
US7487901B2 (en) Friction stir welding of joints with shims
US8766138B2 (en) Method for producing large-sized shell segments as well as shell segment
US20140294489A1 (en) Member joining method and member joining structure
US7775477B2 (en) Floor panel assembly, system, and associated method
JP2009539673A (ja) 航空機胴体用構造体およびその製造方法
CA2613492A1 (en) Method of forming a lightweight structure by connecting sheet-like formations, along with a connection and lightweight structure made thereby
JP2013544692A (ja) 補強材の逃げ部
US20160318594A1 (en) Fuselage section and transverse butt joint connecting two fuselage sections of an aircraft or spacecraft
US20050210820A1 (en) Frame and method for fabricating the same
US11167835B2 (en) Aircraft rear fuselage section and manufacturing method thereof
JP2018119570A (ja) 複合板の接合構造
US20080105786A1 (en) Stringer for an aircraft wing and a method of reinforcing thereof
JP2001048095A (ja) 複合材翼
JP2002364624A (ja) アルミパネルの締結部位構造

Legal Events

Date Code Title Description
AS Assignment

Owner name: EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A.,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FERNANDEZ, FERNANDO FERREIRA;TAKANASHI, SADAO;FORTES, LUCIO CAMARGO;AND OTHERS;REEL/FRAME:020874/0917

Effective date: 20080428

AS Assignment

Owner name: EMBRAER S.A., BRAZIL

Free format text: CHANGE OF NAME;ASSIGNOR:EMBRAER - EMPRESA BRASILEIRA DE AERONAUTICA S.A.;REEL/FRAME:028363/0062

Effective date: 20101119

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION