CA2408779A1 - Integration of self-locating feature into detail parts - Google Patents

Integration of self-locating feature into detail parts

Info

Publication number
CA2408779A1
CA2408779A1 CA002408779A CA2408779A CA2408779A1 CA 2408779 A1 CA2408779 A1 CA 2408779A1 CA 002408779 A CA002408779 A CA 002408779A CA 2408779 A CA2408779 A CA 2408779A CA 2408779 A1 CA2408779 A1 CA 2408779A1
Authority
CA
Canada
Prior art keywords
component parts
self
assembly tool
integration
detailed part
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
CA002408779A
Other languages
French (fr)
Other versions
CA2408779C (en
Inventor
John S. Killian
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.)
Lockheed Martin Corp
Original Assignee
Lockheed Martin Corporation
John S. Killian
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 Lockheed Martin Corporation, John S. Killian filed Critical Lockheed Martin Corporation
Publication of CA2408779A1 publication Critical patent/CA2408779A1/en
Application granted granted Critical
Publication of CA2408779C publication Critical patent/CA2408779C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • 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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • 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
    • G05B2219/00—Program-control systems
    • G05B2219/30—Nc systems
    • G05B2219/31—From computer integrated manufacturing till monitoring
    • G05B2219/31034—Component identifier and location indicator corresponding to component
    • 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
    • G05B2219/00—Program-control systems
    • G05B2219/30—Nc systems
    • G05B2219/31—From computer integrated manufacturing till monitoring
    • G05B2219/31066—Virtual assembly disassembly planning
    • 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
    • G05B2219/00—Program-control systems
    • G05B2219/30—Nc systems
    • G05B2219/37—Measurements
    • G05B2219/37097—Marker on workpiece to detect reference position
    • 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

The present invention provides systems and methods for orienting or assembling a detailed part in a predetermined orientation in which the detailed part is made up of a plurality of component parts. First, a location and alignment are defined by a virtual assembly tool. Next, a unique combination of self-locating features are disposed on the individual component parts in which the unique combination corresponds to the location and alignment defined by the virtual assembly tool. Thus, the virtual assembly tool is integrated into the assembled detailed part. In practice the individual component parts are engaged with predetermined corresponding components parts using the self-locating features. The act of engaging the individual component parts is repeated until all component parts are engaged with each respective corresponding component parts.
CA002408779A 2000-05-17 2001-05-14 Integration of self-locating feature into detail parts Expired - Fee Related CA2408779C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US09/572,807 US6496745B1 (en) 2000-05-17 2000-05-17 Integration of self-locating feature into detail parts
US09/572,807 2000-05-17
PCT/US2001/015715 WO2001088646A1 (en) 2000-05-17 2001-05-14 Integration of self-locating feature into detail parts

Publications (2)

Publication Number Publication Date
CA2408779A1 true CA2408779A1 (en) 2001-11-22
CA2408779C CA2408779C (en) 2007-01-30

Family

ID=24289431

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002408779A Expired - Fee Related CA2408779C (en) 2000-05-17 2001-05-14 Integration of self-locating feature into detail parts

Country Status (9)

Country Link
US (1) US6496745B1 (en)
EP (1) EP1285316B1 (en)
JP (1) JP2003533406A (en)
KR (1) KR100540003B1 (en)
AT (1) ATE272230T1 (en)
AU (1) AU2001266582A1 (en)
CA (1) CA2408779C (en)
DE (1) DE60104544T2 (en)
WO (1) WO2001088646A1 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10314039A1 (en) * 2003-03-28 2004-10-07 Airbus Deutschland Gmbh Frame component for an aircraft
US6793183B1 (en) * 2003-04-10 2004-09-21 The Boeing Company Integral node tubular spaceframe
DE04775785T1 (en) * 2004-02-20 2007-02-22 Bell Helicopter Textron, Inc., Fort Worth PROCESS FOR PRODUCING INTERCHANGEABLE AND REPLACEABLE PARTS
US6883753B1 (en) * 2004-03-25 2005-04-26 The Boeing Company Overhead bin and monument attachment support system
US20080072527A1 (en) * 2006-08-01 2008-03-27 Honda Motor Co., Ltd. Fiber-reinforced composite member and method for producing structure using same
JP4825750B2 (en) * 2006-08-01 2011-11-30 本田技研工業株式会社 Manufacturing method of structure using fiber reinforced composite parts
JP4657191B2 (en) * 2006-11-02 2011-03-23 本田技研工業株式会社 Aircraft main wing structure
US9162436B2 (en) 2013-01-04 2015-10-20 The Boeing Company Method and apparatus for accurate registration of composite laminates
WO2015038041A1 (en) * 2013-09-11 2015-03-19 Saab Ab A fixture device for manufacture of aeronautical structures and a method for applying the device
WO2017098469A1 (en) * 2015-12-11 2017-06-15 Onshape Inc. Replication of components through geometric element matching

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2086290T3 (en) 1987-04-14 1996-07-01 Northrop Grumman Corp MANUFACTURING SYSTEM USING GRAPHIC MODELS IN THREE DIMENSIONS.
US5106290A (en) * 1987-04-14 1992-04-21 Northrop Corporation Assembly data model tool system
US5588554A (en) * 1992-09-21 1996-12-31 The Boeing Company Feeding fasteners to a workpiece
US5560102A (en) * 1992-10-13 1996-10-01 The Boeing Company Panel and fuselage assembly
US5910894A (en) * 1994-01-11 1999-06-08 Sensor Adaptive Machines, Inc. Sensor based assembly tooling improvements
DE69633924T2 (en) 1995-06-28 2005-12-22 The Boeing Co., Seattle STATISTICAL TOLERANCE MEASUREMENT
US5715167A (en) 1995-07-13 1998-02-03 General Electric Company Fixture for calibrated positioning of an object
US6170157B1 (en) * 1996-03-22 2001-01-09 The Boeing Company Determinant spar assembly
CN1089049C (en) 1996-03-22 2002-08-14 波音公司 Determinant spar assembly

Also Published As

Publication number Publication date
EP1285316B1 (en) 2004-07-28
WO2001088646A8 (en) 2002-02-14
DE60104544D1 (en) 2004-09-02
DE60104544T2 (en) 2005-08-04
US6496745B1 (en) 2002-12-17
WO2001088646A1 (en) 2001-11-22
AU2001266582A1 (en) 2001-11-26
EP1285316A2 (en) 2003-02-26
JP2003533406A (en) 2003-11-11
KR20020094058A (en) 2002-12-16
KR100540003B1 (en) 2006-01-10
ATE272230T1 (en) 2004-08-15
CA2408779C (en) 2007-01-30

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Legal Events

Date Code Title Description
EEER Examination request
MKLA Lapsed