FR3094255B1 - method of assembling structural parts - Google Patents

method of assembling structural parts Download PDF

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Publication number
FR3094255B1
FR3094255B1 FR1903176A FR1903176A FR3094255B1 FR 3094255 B1 FR3094255 B1 FR 3094255B1 FR 1903176 A FR1903176 A FR 1903176A FR 1903176 A FR1903176 A FR 1903176A FR 3094255 B1 FR3094255 B1 FR 3094255B1
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FR
France
Prior art keywords
structural parts
structural
connecting part
assembling structural
parts
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.)
Active
Application number
FR1903176A
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French (fr)
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FR3094255A1 (en
Inventor
Elodie Bonhomme
Jacques Bouriquet
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 FR1903176A priority Critical patent/FR3094255B1/en
Publication of FR3094255A1 publication Critical patent/FR3094255A1/en
Application granted granted Critical
Publication of FR3094255B1 publication Critical patent/FR3094255B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/418—Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS], computer integrated manufacturing [CIM]
    • G05B19/41805—Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS], computer integrated manufacturing [CIM] characterised by assembly
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23B—TURNING; BORING
    • B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/01—Aircraft parts
    • 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
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

Abstract

PROCEDE D’ASSEMBLAGE DE PIECES STRUCTURELLES L’invention concerne un procédé d’assemblage de trois pièces structurelles (110, 120, 150a-d). Le procédé d’assemblage consiste à réaliser des empreintes (114, 122) sur les deux premières pièces structurelles (110, 120), à numériser chaque nuage de ces empreintes (114, 122) et des surfaces de contact, à réaliser numériquement une mise en position virtuelle de ces deux nuages ce qui permet de déterminer les dimensions que doit avoir chaque pièce structurelle de liaison (150a-d), à usiner chaque pièce structurelle de liaison (150a-d) à partir de cette mise en position virtuelle en y incorporant les perçages (152) correspondant aux empreintes (114, 122), puis à positionner et fixer les trois pièces structurelles (110, 120, 150a-d). Un tel procédé permet un gain de temps car la numérisation et la réalisation de la pièce structurelle de liaison se font avant la mise en place des deux premières pièces structurelles et la pièce structurelle de liaison est alors prête à être mise en place en même temps que les autres. Fig. 2The invention relates to a method for assembling three structural parts (110, 120, 150a-d). The assembly process consists of making impressions (114, 122) on the first two structural parts (110, 120), digitizing each cloud of these impressions (114, 122) and contact surfaces, digitally performing a in virtual position of these two clouds, which makes it possible to determine the dimensions that each structural connecting part (150a-d) must have, to machine each structural connecting part (150a-d) from this setting in virtual position in y incorporating the holes (152) corresponding to the cavities (114, 122), then to position and fix the three structural parts (110, 120, 150a-d). Such a method saves time because the digitization and the production of the structural connecting part are done before the installation of the first two structural parts and the structural connecting part is then ready to be put in place at the same time as others. Fig. 2

FR1903176A 2019-03-27 2019-03-27 method of assembling structural parts Active FR3094255B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1903176A FR3094255B1 (en) 2019-03-27 2019-03-27 method of assembling structural parts

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1903176A FR3094255B1 (en) 2019-03-27 2019-03-27 method of assembling structural parts
FR1903176 2019-03-27

Publications (2)

Publication Number Publication Date
FR3094255A1 FR3094255A1 (en) 2020-10-02
FR3094255B1 true FR3094255B1 (en) 2022-07-01

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
FR1903176A Active FR3094255B1 (en) 2019-03-27 2019-03-27 method of assembling structural parts

Country Status (1)

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FR (1) FR3094255B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE1029348B1 (en) * 2021-10-07 2022-11-28 Sonaca QUICK ATTACHMENT FOR A MOBILE FLAP MODULE OF AN AIRCRAFT WING

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0519364D0 (en) 2005-09-22 2005-11-02 Airbus Uk Ltd Assembly of aircraft components
US9586667B2 (en) * 2014-12-02 2017-03-07 The Boeing Company Splice assembly for joining structural components
US9857789B2 (en) * 2015-05-04 2018-01-02 The Boeing Company Model-based definition for machining aircraft parts
US10521551B2 (en) * 2015-11-16 2019-12-31 The Boeing Company Methods for shimming flexible bodies
US9952580B2 (en) * 2016-01-29 2018-04-24 The Boeing Company Method and an apparatus for machining a part for an assembly
US10934020B2 (en) * 2017-01-25 2021-03-02 The Boeing Company Method and system for joining structures

Also Published As

Publication number Publication date
FR3094255A1 (en) 2020-10-02

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