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FR2977296B1 - METHOD OF CONNECTION BETWEEN OVERLAPPING PIECES ON SEVERAL PLANS AND APPLICATION TO AN AIRCRAFT FUSELAGE PANEL - Google Patents

METHOD OF CONNECTION BETWEEN OVERLAPPING PIECES ON SEVERAL PLANS AND APPLICATION TO AN AIRCRAFT FUSELAGE PANEL

Info

Publication number
FR2977296B1
FR2977296B1 FR1155738A FR1155738A FR2977296B1 FR 2977296 B1 FR2977296 B1 FR 2977296B1 FR 1155738 A FR1155738 A FR 1155738A FR 1155738 A FR1155738 A FR 1155738A FR 2977296 B1 FR2977296 B1 FR 2977296B1
Authority
FR
France
Prior art keywords
parts
flanges
aircraft fuselage
connection
application
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
Application number
FR1155738A
Other languages
French (fr)
Other versions
FR2977296A1 (en
Inventor
Anais Markowski
Christophe Mialhe
Denis Soula
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Priority to FR1155738A priority Critical patent/FR2977296B1/en
Publication of FR2977296A1 publication Critical patent/FR2977296A1/en
Application granted granted Critical
Publication of FR2977296B1 publication Critical patent/FR2977296B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • B64C1/12—Construction or attachment of skin panels
    • 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
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Road Paving Structures (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Connection Of Plates (AREA)

Abstract

The method involves attaching flanges (42) of a first set of parts (4) to a positioning plane (3). A second set of parts (2) is formed with perforation zones at intervals. Extensions (5) are formed with central openings (53) at periphery of projections (41) of the first set of parts while positioning flanges (22) of the second set of parts on the positioning plane. The extensions partially attached to the flanges of the second set of parts and positioned to support flanges of the first set of parts are attached with the positioning plane through the flanges of the second set of parts. An independent claim is also included for an aircraft fuselage skin panel.
FR1155738A 2011-06-28 2011-06-28 METHOD OF CONNECTION BETWEEN OVERLAPPING PIECES ON SEVERAL PLANS AND APPLICATION TO AN AIRCRAFT FUSELAGE PANEL Expired - Fee Related FR2977296B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1155738A FR2977296B1 (en) 2011-06-28 2011-06-28 METHOD OF CONNECTION BETWEEN OVERLAPPING PIECES ON SEVERAL PLANS AND APPLICATION TO AN AIRCRAFT FUSELAGE PANEL

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1155738A FR2977296B1 (en) 2011-06-28 2011-06-28 METHOD OF CONNECTION BETWEEN OVERLAPPING PIECES ON SEVERAL PLANS AND APPLICATION TO AN AIRCRAFT FUSELAGE PANEL

Publications (2)

Publication Number Publication Date
FR2977296A1 FR2977296A1 (en) 2013-01-04
FR2977296B1 true FR2977296B1 (en) 2013-08-02

Family

ID=44543479

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1155738A Expired - Fee Related FR2977296B1 (en) 2011-06-28 2011-06-28 METHOD OF CONNECTION BETWEEN OVERLAPPING PIECES ON SEVERAL PLANS AND APPLICATION TO AN AIRCRAFT FUSELAGE PANEL

Country Status (1)

Country Link
FR (1) FR2977296B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104339290A (en) * 2013-08-01 2015-02-11 空中客车运营简化股份公司 Tool to hold several mounting clamps simultaneously against an aircraft fuselage frame element

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3009274A1 (en) * 2013-08-01 2015-02-06 Airbus Operations Sas AIRCRAFT FUSELAGE FRAME ELEMENT INTEGRATING TABS FOR ATTACHING STIFFENERS
FR3009352B1 (en) 2013-08-01 2016-01-01 Airbus Operations Sas TOOLING FOR THE SIMULTANEOUS MAINTENANCE OF SEVERAL FASTENING CLIPS AGAINST AN AIRCRAFT FUSELAGE FRAME ELEMENT
WO2015094059A1 (en) * 2013-12-20 2015-06-25 Saab Ab Stiffening element and reinforced structure
ES2707864T3 (en) 2013-12-31 2019-04-05 Airbus Operations Sl Structure of an aircraft made of composite material

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2489779A1 (en) * 1980-09-09 1982-03-12 Aerospatiale FUSELAGE STRUCTURE FOR AN AIRCRAFT RESISTANT TO THE LONGITUDINAL BREAKAGE OF THE EXTERIOR COATING
JP4318381B2 (en) * 2000-04-27 2009-08-19 本田技研工業株式会社 Manufacturing method of fuselage structure made of fiber reinforced composite material, and fuselage structure manufactured thereby
US6648273B2 (en) * 2001-10-30 2003-11-18 The Boeing Company Light weight and high strength fuselage
US7159822B2 (en) * 2004-04-06 2007-01-09 The Boeing Company Structural panels for use in aircraft fuselages and other structures
DE102007029500B4 (en) * 2007-06-25 2013-02-14 Airbus Operations Gmbh Method for coupling stiffening profile elements and structural component

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104339290A (en) * 2013-08-01 2015-02-11 空中客车运营简化股份公司 Tool to hold several mounting clamps simultaneously against an aircraft fuselage frame element
CN104339290B (en) * 2013-08-01 2017-09-26 空中客车运营简化股份公司 Several installs fixtures are maintained to the instrument on aircraft fuselage frame element simultaneously

Also Published As

Publication number Publication date
FR2977296A1 (en) 2013-01-04

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