US20020148271A1 - Process and apparatus for manufacturing products of defined thickness - Google Patents

Process and apparatus for manufacturing products of defined thickness Download PDF

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Publication number
US20020148271A1
US20020148271A1 US10/100,094 US10009402A US2002148271A1 US 20020148271 A1 US20020148271 A1 US 20020148271A1 US 10009402 A US10009402 A US 10009402A US 2002148271 A1 US2002148271 A1 US 2002148271A1
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US
United States
Prior art keywords
product
process according
frame
tool
foregoing
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Abandoned
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US10/100,094
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English (en)
Inventor
Bruno Schiavi
Carlo Massari
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Jobs SpA
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Jobs SpA
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Assigned to JOBS S.P.A. reassignment JOBS S.P.A. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MASSARI, CARLO, SCHIAVI, BRUNO
Publication of US20020148271A1 publication Critical patent/US20020148271A1/en
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
    • B23Q1/01—Frames, beds, pillars or like members; Arrangement of ways
    • B23Q1/012—Portals
    • 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
    • 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
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Definitions

  • the present invention relates to a process for manufacturing products of defined thickness.
  • the present invention relates to a process for mechanically and selectively reducing the thickness of parts of aerospace structures made from metal sheets.
  • Prior art methods for lightening the metal sheeting are based substantially on a process known as “chemical milling”. This consists in spray coating the metal sheet with a masking material (maskant) in such a way as to form a protective layer on it. A pattern is subsequently cut into this coating, manually or with a laser instrument, to distinguish the parts of the metal sheet that have to be lightened from those whose thickness is to be left substantially unchanged. The maskant, which dries to a continuous film, is then removed from the parts to be lightened and the metal sheet is lowered into a tank containing a chemical which erodes the metal in the parts not protected by the maskant.
  • a masking material masking material
  • the metal sheet is left in the tank for a preset time and then lifted out and washed, depending on the amount of material to be removed. This process is carried out gradually. Therefore, if some parts of the metal sheet have to be further lightened, the process is repeated until all parts of it have the required thickness.
  • the present invention therefore has for an object to provide a process for manufacturing products of defined thickness that overcomes the above mentioned disadvantages.
  • the present invention provides a process for manufacturing products of defined thickness used as parts in spacecraft or aircraft structures, the process comprising at least the step of mechanically removing the material of which the product is made at least from defined and separate areas of the product in order to reduce the thickness of and thus lighten the product.
  • FIG. 1 is a schematic perspective view, with some parts cut away in order to better illustrate others, of an apparatus used to manufacture products according to the present invention
  • FIG. 2 is a perspective view of a detail from FIG. 1 and illustrates a step in the work performed by the apparatus
  • FIG. 3 is a front view, with some parts cut away in order to better illustrate others, of the apparatus shown in FIG. 1;
  • FIG. 4 is a front view, with some parts cut away in order to better illustrate others, of another embodiment of the apparatus shown in FIG. 1.
  • the numeral 1 denotes in its entirety an apparatus for manufacturing products 2 and comprising an automatic machine tool 3 and a frame 4 that supports the products 2 being processed.
  • the automatic machine tool 3 comprises a mobile crossbeam 5 that mounts a machining unit 6 .
  • the machining unit 6 can move in three-dimensional space along the three linear axes X, Y and Z of a Cartesian system.
  • the machining unit 6 illustrated schematically in the accompanying drawings, may also have three continuous interpolation axes, or three continuous interpolation axes and two positioning axes, or five or more continuous interpolation axes.
  • the machining unit 6 which is of conventional type and therefore not illustrated in detail, comprises a slide 7 that mounts a tool holder head 8 .
  • the latter is slidably engaged with a supporting element 9 in which it runs in the direction Z.
  • the supporting element 9 can move in the direction Y relative to the crossbeam 5 through customary driving means which are not described in further detail.
  • the crossbeam 5 extends in a principal direction D 1 that is substantially parallel to the Y-axis of the Cartesian reference system.
  • the crossbeam 5 is supported by two longitudinal guides 10 , 11 extending in a principal direction D 2 that is substantially parallel to the direction X, the guides 10 , 11 being supported by a plurality of columns 12 .
  • the columns 12 have respective lower ends 13 connected to a base 14 of the machine tool 3 and respective upper ends 15 connected to the longitudinal guides 10 , 11 .
  • the crossbeam 5 can slide in the longitudinal guides 10 , 11 in the direction D 2 so as to guide the machining unit 6 in the movements the latter is required to perform in order to machine the product 2 in the automatic machine tool 3 .
  • the machine tool 3 further comprises a numerical control unit 16 , located at one of the columns 12 and designed to control the machining unit 6 so that the machine 3 can perform the required machining operations.
  • the product 2 is, for example, a part 17 that will be used to make the fuselage of an airplane and where the openings for the windows of the airplane are labeled 18 .
  • the part 17 has a given curvature previously applied on a substantially flat length of material, such as, for example, a metal sheet using customary forming devices which are not described.
  • the frame 4 supporting the product 2 is positioned inside the space delimited by the columns 12 of the automatic machine tool 3 , under the machining unit 6 .
  • the frame 4 is in the form of a table and comprises a base 19 that is substantially fixed relative to the bed 14 of the machine tool 3 and a detachable part 20 that is connected to the base 19 and having an upper face 21 .
  • a product 2 with a given curvature is positioned on the upper face 21 of the frame 4 , the upper face 21 being shaped to match the curvature of the product 2 .
  • FIG. 4 shows a product 2 that is substantially flat positioned on the upper face 21 of the frame 4 , the upper face 21 also being substantially flat.
  • the frame 4 comprises a plurality of suction holes 22 distributed on its upper face 21 and designed to hold the product 2 down against the face 21 when the product 2 is placed on the frame 4 for machining.
  • suction holes 22 are connected to a customary suction device which is schematically illustrated as a block 23 in the drawings.
  • suction holes 22 and the suction device 23 together constitute suction means 24 .
  • the upper face 21 of the frame 4 thanks to its secure hold on the product 2 through the suction means 24 , constitutes a positioning reference element for the product 2 and a geometric reference for measuring the machining dimensions.
  • FIG. 2 is an enlarged detail view showing a stage in the machining of the product 2 by a tool 25 mounted on the tool holder head 8 of the machining unit 6 .
  • the tool 25 is removing material from a frame 26 of one of the openings 18 for the airplane windows.
  • each frame 26 is reduced to a thickness S 1 starting from an initial thickness S 2 of the product 2 .
  • the difference S 2 -S 1 is therefore the thickness of the material removed from the frame 26 by the machine tool 3 .
  • the 2 also has an edge 27 , whose thickness is substantially the same as the initial thickness S 2 of the product 2 , and a central area 28 , which is delimited by the edge 27 and the frames 26 and which is shown as a dotted surface in the drawing.
  • the edge 27 is the element that will be connected to the other part of the airplane fuselage, whilst the central area 28 , being a simple covering without any other special function, does not need to have equally high mechanical strength. It follows, therefore, that the thickness S 2 -S 3 of the central area 28 is further reduced.
  • the central area 28 is the area from which the tool 25 removes the largest quantity of material.
  • the tool 25 is a milling cutter and the operation of removing material from the product 2 is substantially a milling operation.
  • the milling operation may, as mentioned above, be alternatively performed paraxially, that is to say, using three continuous interpolation axes, or in inclined planes, that is to say, using three continuous interpolation axes plus three positioning axes, or on shapes oriented in any direction, that is to say, using five or more continuous interpolation axes.
  • the machining unit 6 is advantageously driven by linear electric motors.
  • the crossbeam 5 is driven in the direction D 2 by two linear electric motors 29 , 30 .
  • Each of the two linear electric motors 29 , 30 comprises a primary member or rotor 31 and a secondary member or stator 32 .
  • the two primary members 31 are integral with the mobile crossbeam 5 at two ends of it 5 a, 5 b, which are opposite each other in longitudinal direction.
  • the two secondary members 32 consist of two respective parallel slideways 33 , 34 , each extending along one of the longitudinal guides 10 , 11 .
  • the product 2 is positioned on the supporting frame 4 by customary means, which are not illustrated, for gripping and lifting the product 2 .
  • the product 2 is placed on the upper face 21 of the frame 4 and made to adhere perfectly against the upper face 21 by switching on the suction means 24 .
  • the sucking action of the suction holes 22 distributed over the surface of the upper face 21 holds the product 2 down securely against the upper face 21 itself.
  • the control unit 16 can, by resetting the dimension of the surface of the face 21 without the product 2 on it and using this as the reference zero dimension, continuously check the thickness of the material at any point on the product 2 by comparing the height of the material at that point with the previously reset reference zero dimension of the upper face 21 itself.
  • the upper face 21 of the frame's detachable part 20 has a curved shape designed to accommodate a product 2 that has been previously deformed in such a way as to give it a required curvature.
  • the detachable part 20 of the frame 4 is therefore shaped to match the required curvature of the product 2 .
  • the machining dimensions used by the machining unit 6 of the machine tool 3 to perform the subsequent machining operations do not substantially differ from the dimensions of the product 2 in its final working configuration.
  • the shape of the upper face 21 therefore constitutes the matching shape of the frame 4 relative to the product 2 .
  • the upper face 21 of the detachable part 20 of the frame 4 is substantially flat so as to accommodate a product 2 that has not yet been deformed into a required curved shape but that will be deformed during a subsequent process that is not illustrated.
  • the machining dimensions used by the machining unit 6 of the machine tool 3 to perform the subsequent machining operations differ substantially from the dimensions of the product 2 in its final working configuration.
  • the frame 4 supporting the product 2 has a detachable part 20 makes the apparatus 1 extremely versatile because it enables the apparatus to be rapidly set up to machine different products 2 by simply changing the detachable part 20 .
  • the material is removed from the different areas 26 , 27 , 28 of the product 2 in quantities that are substantially inversely proportional to the level of stress that these parts are required to resist when the product 2 is installed.
  • the central area 28 is made lighter than the edge 27 which has to be connected to the corresponding edge of another panel forming part of the fuselage and also lighter than the frames 26 which are required to hold the aircraft windows in place.
  • the apparatus 1 makes it possible to quickly and economically achieve an optimum balance between the need for light weights on the one hand, and high mechanical strength on the other, in the production of parts for the aerospace industry.
  • the machining unit 6 under the control of the same control unit 16 , can be used not only for selectively removing material from the product 2 , but also to perform finishing operations on it such as, for example, boring, countersinking and molding, without having to transfer the product 2 to other machine tools.
  • the movements of the slide 7 relative to the supporting element 9 and of the supporting element 9 relative to the crossbeam 5 are driven by linear electric motors.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Jigs For Machine Tools (AREA)
  • Battery Electrode And Active Subsutance (AREA)
  • Control Of Metal Rolling (AREA)
  • Milling Processes (AREA)
US10/100,094 2001-03-27 2002-03-19 Process and apparatus for manufacturing products of defined thickness Abandoned US20020148271A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT2001BO000180A ITBO20010180A1 (it) 2001-03-27 2001-03-27 Procedimento ed apparecchiatura per la realizzazione di manufatti di spessore determinato
ITBO2001A000180 2001-03-27

Publications (1)

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US20020148271A1 true US20020148271A1 (en) 2002-10-17

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US10/100,094 Abandoned US20020148271A1 (en) 2001-03-27 2002-03-19 Process and apparatus for manufacturing products of defined thickness

Country Status (4)

Country Link
US (1) US20020148271A1 (de)
EP (1) EP1245317A1 (de)
CN (1) CN1377810A (de)
IT (1) ITBO20010180A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2017136929A (ja) * 2016-02-02 2017-08-10 三菱重工業株式会社 形状保持治具及び航空機パネル製造方法
US20190248514A1 (en) * 2015-08-05 2019-08-15 Bae Systems Plc Aircraft part assembly
US20200017238A1 (en) * 2018-07-12 2020-01-16 The Boeing Company Wing panel assembly system and method

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US7093470B2 (en) 2002-09-24 2006-08-22 The Boeing Company Methods of making integrally stiffened axial load carrying skin panels for primary aircraft structure and fuel tank structures
DE10314039A1 (de) * 2003-03-28 2004-10-07 Airbus Deutschland Gmbh Spantbauteil für ein Flugzeug
FR2865954B1 (fr) * 2004-02-10 2006-06-23 Airbus France Procede et dispositif d'usinage par fenetrage de panneaux minces non-developpables
FR2865952B1 (fr) 2004-02-10 2006-06-23 Airbus France Procede et dispositif d'usinage mecanique de panneaux flexibles en particulier de forme complexe
IT1391104B1 (it) * 2008-08-07 2011-11-18 Belotti Spa Macchina utensile a portale
JP5364175B2 (ja) * 2009-02-27 2013-12-11 チタニウム メタルス コーポレイション シート製品をプロファイリングするためのシステムおよび方法
IT1400479B1 (it) 2010-06-03 2013-06-11 Zoppi Banco e metodo di supporto e lavorazione di pezzi a geometria complessa
CN102773715A (zh) * 2012-08-10 2012-11-14 杜双全 立式加工机床的改进型结构
CN105015798A (zh) * 2014-04-29 2015-11-04 哈尔滨飞机工业集团有限责任公司 一种超厚蜂窝数控加工方法
CN109514258B (zh) * 2018-12-14 2024-05-10 北京印刷学院 一种曲面五轴切削及表面喷绘复合处理工装

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US3329065A (en) * 1965-01-18 1967-07-04 Lockheed Aircraft Corp Rotary cutter and method
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Publication number Priority date Publication date Assignee Title
US20190248514A1 (en) * 2015-08-05 2019-08-15 Bae Systems Plc Aircraft part assembly
US10710748B2 (en) * 2015-08-05 2020-07-14 Bae Systems Plc Aircraft part assembly
JP2017136929A (ja) * 2016-02-02 2017-08-10 三菱重工業株式会社 形状保持治具及び航空機パネル製造方法
US20200017238A1 (en) * 2018-07-12 2020-01-16 The Boeing Company Wing panel assembly system and method
US11485519B2 (en) * 2018-07-12 2022-11-01 The Boeing Company Wing panel assembly system and method

Also Published As

Publication number Publication date
ITBO20010180A1 (it) 2002-09-27
CN1377810A (zh) 2002-11-06
EP1245317A1 (de) 2002-10-02
ITBO20010180A0 (it) 2001-03-27

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