US3886023A - Structural panels of the sandwich type - Google Patents

Structural panels of the sandwich type Download PDF

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Publication number
US3886023A
US3886023A US346285A US34628573A US3886023A US 3886023 A US3886023 A US 3886023A US 346285 A US346285 A US 346285A US 34628573 A US34628573 A US 34628573A US 3886023 A US3886023 A US 3886023A
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US
United States
Prior art keywords
resin
coverings
cells
panel
zones
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 - Lifetime
Application number
US346285A
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English (en)
Inventor
Henri Deplante
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.)
Dassault Aviation SA
Original Assignee
Dassault Aviation 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
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Publication of US3886023A publication Critical patent/US3886023A/en
Assigned to CONTINENTAL BANK N.A. reassignment CONTINENTAL BANK N.A. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: UIPE PRODUCTS, INC., A NEVADA CORP.
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D24/00—Producing articles with hollow walls
    • B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
    • B29D24/005—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled the structure having joined ribs, e.g. honeycomb
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/30—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure
    • E04C2/34—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts
    • E04C2/36—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
    • E04C2/365—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels by honeycomb structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L59/00—Thermal insulation in general
    • F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
    • F16L59/029—Shape or form of insulating materials, with or without coverings integral with the insulating materials layered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/02—Cellular or porous
    • B32B2305/024—Honeycomb
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2607/00—Walls, panels
    • 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
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
    • Y10T156/1003—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by separating laminae between spaced secured areas [e.g., honeycomb expanding]
    • 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
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1056—Perforating lamina
    • Y10T156/1057—Subsequent to assembly of laminae
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24149—Honeycomb-like
    • Y10T428/24157—Filled honeycomb cells [e.g., solid substance in cavities, etc.]

Definitions

  • the centre of the nodes thus formed is pierced right through by a hole having substantially the shape and diameter necessary for the passage of a screw or other component.
  • the present invention relates to structural panels of the sandwich type comprising a cellular core of the honey-comb kind, on each side of which there adhere covering plates or sheets which are disposed perpendic' ularly to the partitions of the cellular structure.
  • the invention refers more particularly to the panels of this kind which are intended for the production of light, strong floors and partitions, especially in the construction of air transport vehicles.
  • the cellular structure in the form of a honeycomb is generally made of light metal alloy, while the covering plates or sheets are made of plastics material which is attached to the cross-section of the partitions in the cellular structure.
  • the eyelets are relatively expensive and greatly increase the cost price of the panel. They create a projection on each of the faces of the panel, so that the panels are supported only locally on the framework by the eyelets, thus contributing to bending between the latter under the effect of loads. Furthermore, the projection of the eyelets on the upper face of the panels causes wearing of the moquette with which the floor is generally covered. Finally, the resistance to tearing of eyelets located at the edge of the panels is not always adequate. Because of this the panels are ruined and have to be replaced.
  • the present invention aims to make it possible to avoid these drawbacks and, in particular, to obtain a high degree of strength for the points of attachment of the panels, at minimal cost.
  • the object of the invention is to provide a method of producing attachment zones or locations in a sandwich type panel made up of a cellular structure and of flat coverings disposed on both sides of the said structure and adhering to the latter, wherein, in spaced-out zones of this structure, which are approximately circular and have a diameter which is appreciably greater than that of a screw or other component and is, moreover, sufficiently great for each of the said zones to encompass a plurality of contiguous cells, a hardenable compound is poured into the cells in these zones in such a way as to fill them, while the said structure has still not received at least one of its two coverings, and then, after complete attachment of the said coverings and hardening of the compound, he centre of the nodes thus formed is pierced right through by a hole having substantially the shape and diameter necessary for the passage of a screw or other component.
  • the hardenable compound is preferably based on plastics material.
  • the invention also extends to panels provided with the attachment nodes thus produced.
  • FIG. 1 is a diagrammatic view, in perspective, showing the make-up of a sandwich type panel
  • FIG. 2 shows part of a finished panel
  • FIG. 3 is a cross-section taken along the line llllll in FIG. 2;
  • FIGS. 4, 5 and 6 are views in partial cross-section along the line lV-lV in H6. 2 and show successive phases in the production of an attachment node.
  • FIG. 1 a cellular structure 1 of the honeycomb kind, which is most often made of light, aluminum-based alloy such as for example the alloy known under the designation A0 and of which the cells, which have a hexagonal or other shape, have a relatively small crosssection of the order of a few mm?
  • A0 the alloy known under the designation
  • FIGS. 2 and 3 the panel shown in FIGS. 2 and 3 is obtained.
  • the panels In order to make up a floor or partition with panels of this kind the panels must be attached by their edges to a framework which is usually metal, and the problem consists in providing, along the edges of the panels, at a slight distance from these edges and at suitably dis tributed points 5 and also, if necessary, at other points on the panel, holes intended for the passage of screws or other components which will secure the panel to the framework.
  • the known eyelets comprise, on one of their collars, holes which permit the passage of an injection needle.
  • One method of implementing the present invention involves taking the cellular structure 1, which is not yet provided with the coverings 3 and 4, and placing this structure on a slab 6.
  • a plate or template 7 which is the same size as the panel to be produced is placed on the said structure and is pierced with apertures 8, the axes of which coincide with those of the holes 5 which are to be formed in the panel for the passage of attachment screws.
  • the apertures 8 in the template have a diameter which is very much greater than that of the holes with which the panel is finally to be provided. for example a diameter of about 20 mm. for a hole diameter of between 3 and mm.
  • a moving piston type pressure-injection gun 9 By means of a moving piston type pressure-injection gun 9. the nozzle of which has the same diameter as the aperture 8, there is injected. through each of these apertures. a compound made of plastics material which thus completely fills the cells revealed by the aperture 8, even if the cells remain partly masked at the periphery of this aperture.
  • This compound is such that it has good properties of adhesion to the coverings 3 and 4 which will subsequently be attached to the cellular structure.
  • the said compound is also such that it has thixotropic properties and thus remains in place in the cellular structure without escaping therefrom when the latter is removed from the slab 6 for the purpose of providing it with the coverings 3 and 4, preferably by hot pressing.
  • the compound which has been poured into the cells hardens and the finished panel thus contains. around the geometrical axes ofthe holes which are subsequently to be pierced, types of nodes in which the cells are filled with a hard plastics material between the coverings 3 and 4 (these zones have been shown in dotted lines at 11 in FIG. 2).
  • the panel is then taken and again placed on a slab 6a (FIG. 5) and has superimposed upon it the template 7, the apertures Sin which are thus again located opposite the nodes 11, whereupon. by means of a drilling gun 12 which is successively placed on each of the apertures 8, and of a diamond'tipped bit 13 which is fitted in the said gun.
  • each hole 5 for the passage of an attachment screw is pierced in the centre of each of the nodes 11 which hole may possibly be milled at one or other of its ends.
  • the slab 6a preferably comprises a cut-out portion 6/) permitting the point of the bit 13 to pass through the panel. in the course of the operation. the assembly constituted by the panel and the template 7 is displaced on the slab [after the gun 12 has been raised vertically) in such a way as to bring each of the holes 8 in the template and each of the attachment nodes 11 under the said gun.
  • FIG. 6 shows. in section. one of the panel nodes pierced by the hole 5.
  • a compound which is suitable for pouring into the cells in order to make up the nodes attention may be drawn to a mixture of a fluid resin containing its hardening catalyst. and of a very high proportion of finely ground silica (about 250 parts by weight of silica to l()() parts by weight of resin).
  • the ground silica tranforms the fluid resin into a thixotropic product and gives it, after hardening, exceptional hardness and tensile strength.
  • the resin will advantageously be an epoxy resin in the event of the coverings 3 and 4 themselves containing a resin of this type.
  • an epoxy resin-based compound of this kind is capable of hardening at ambient temperature. which justifies its use for repairs. After polymerisation, the product is self-extinguishing.
  • the use of a special thixotropic compound could be avoided if a start were made by sticking one of the covering plates, for example the plate 4, to one of the faces of the cellu lar structure in such a way that this plate would serve as a base for the pouring of the plastics material into the cells of the honeycomb.
  • a method of producing sandwich panels by applying flat coverings, each including plastic material, on both sides of a cellular honeycomb-like structure the improvement of providing reinforced nodes at selected spaced apart points of the panel for the attachment thereof to a supporting structure. by the steps comprising: while said cellular structure has at least one of its sides uncovered, completely filling each of a plurality of adjoining cells of said structure surrounding each of said points in a zone having the node point as the center thereof with a hardenable fluid resin having good adhesion to the plastic material of the coverings by pouring said resin in liquid state into each of said cells; applying the remaining covering to the cellular structure while plural cells at each such point are filled with said fluid resin; hardening said resin after both said coverings are in place; and thereafter, piercing through the coverings and the filled cellular structure along the axis of each node.
  • said hardenablc fluid resin is a resin epoxy containing a hardening catalyst therefor.
  • a method as claimed in claim 1. in which a template having apertures is superimposed upon the said structure for the pouring of the resin into the spacedapart zones of the cellular structure. the axes of said apertures coinciding with those of the holes to be finally 6 formed in the panel. but having a diameter which is apsaid structure, the holes are formed in said nodes by preciably greater than that of the said holes. means of a drilling gun which is placed on the apertures 7.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Laminated Bodies (AREA)
  • Panels For Use In Building Construction (AREA)
  • Joining Of Building Structures In Genera (AREA)
US346285A 1972-03-31 1973-03-30 Structural panels of the sandwich type Expired - Lifetime US3886023A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7211660A FR2177640B1 (it) 1972-03-31 1972-03-31

Publications (1)

Publication Number Publication Date
US3886023A true US3886023A (en) 1975-05-27

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US346285A Expired - Lifetime US3886023A (en) 1972-03-31 1973-03-30 Structural panels of the sandwich type

Country Status (4)

Country Link
US (1) US3886023A (it)
DE (1) DE2316061A1 (it)
FR (1) FR2177640B1 (it)
GB (1) GB1420009A (it)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4076877A (en) * 1974-05-24 1978-02-28 Vereinigte Flugtechnische Werke - Fokker Gmbh Cellular structure plate
US4265688A (en) * 1977-08-11 1981-05-05 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Method for producing sandwich type structural components
US4416715A (en) * 1978-08-31 1983-11-22 Doralyn Ann Hardy Method and apparatus for fabricating insulative panel
US4510010A (en) * 1980-05-27 1985-04-09 Schramm Arthur G Method and apparatus for fabricating insulative panel
US4715801A (en) * 1981-07-15 1987-12-29 Corning Glass Works Apparatus for high speed manifolding of honeycomb structures
US4964936A (en) * 1988-10-11 1990-10-23 Imi-Tech Corporation Method of making foam-filled cellular structures
US5186999A (en) * 1989-02-17 1993-02-16 Schreiner Luchtvaart Groep B.V. Sandwich material provided with a local reinforcement
US5421935A (en) * 1991-07-12 1995-06-06 Hexcel Corporation Method for making thermally fused thermoplastic honeycomb structures
US20030175491A1 (en) * 2002-03-15 2003-09-18 Joseph Wycech Method for stiffening or reinforcing a member in a cost effective manner and a member which is made in accordance with the method
US20030222377A1 (en) * 2002-05-29 2003-12-04 The Boeing Company Potting compound injection apparatus and method of injecting potting compound into panel cells
US20050208274A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Composite sandwich structure with integrated reinforcement area and method of producing the same
US20050208273A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Locally reinforced core structure for composite sandwich structure and method of producing the same
US20050206035A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Method and apparatus for processing open three-dimensional core structures such as folded honeycomb structures
US20050204693A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Method for sealing edges of a core of a composite sandwich structure
DE102014118514A1 (de) * 2014-12-12 2016-06-16 Ross Design Gmbh Verfahren zur Herstellung von Leichtbauelementen und Leichtbauelemente
EP3396080A1 (de) * 2017-04-24 2018-10-31 Ross Design GmbH Verfahren zur herstellung eines leichtbauelements

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE466299B (sv) * 1983-08-04 1992-01-27 Micropore International Ltd Vaermeisolerande kropp och saett att framstaella den, innefattande en armerande bikakestruktur och ett vaermeisolationsmaterial
FR2591257A1 (fr) * 1985-12-06 1987-06-12 Borie Panneaux de revetement de facade en fibre de verre et polyester
FI982743A (fi) * 1998-12-18 2000-06-19 System 300 Group Oy Keilaradan rakennuselementti ja keilarata
DE102004013146B4 (de) * 2004-03-17 2008-01-24 Airbus Deutschland Gmbh Verfahren zur Verstärkung von Kernstrukturen zur Bildung von beidseitig mit Deckschichten versehenen Kernverbunden
EP2422756A1 (en) * 2010-08-26 2012-02-29 Restored Hearing Ltd. A container comprising a thixotropic material

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US829267A (en) * 1905-09-19 1906-08-21 John K Graham Templet.
US3173520A (en) * 1958-10-06 1965-03-16 Bristol Aerojet Ltd Reinforced skin structures
US3485282A (en) * 1968-01-26 1969-12-23 Hughes Aircraft Co Expandable insert for solid and cellular structures
US3578526A (en) * 1968-01-22 1971-05-11 United Aircraft Corp Method of making reinforced honeycomb sandwich
US3742673A (en) * 1971-03-22 1973-07-03 Rex Chainbelt Inc Panel edge fastening means

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1237054A (fr) * 1958-10-06 1960-07-22 Bristol Aircraft Ltd Revêtement armé, en particulier pour l'aviation
GB994952A (en) * 1963-07-25 1965-06-10 Riegel Textile Corp Laminated textile product and method of manufacture same
US3481427A (en) * 1968-11-29 1969-12-02 Mc Donnell Douglas Corp Acoustical panel structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US829267A (en) * 1905-09-19 1906-08-21 John K Graham Templet.
US3173520A (en) * 1958-10-06 1965-03-16 Bristol Aerojet Ltd Reinforced skin structures
US3578526A (en) * 1968-01-22 1971-05-11 United Aircraft Corp Method of making reinforced honeycomb sandwich
US3485282A (en) * 1968-01-26 1969-12-23 Hughes Aircraft Co Expandable insert for solid and cellular structures
US3742673A (en) * 1971-03-22 1973-07-03 Rex Chainbelt Inc Panel edge fastening means

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4076877A (en) * 1974-05-24 1978-02-28 Vereinigte Flugtechnische Werke - Fokker Gmbh Cellular structure plate
US4265688A (en) * 1977-08-11 1981-05-05 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Method for producing sandwich type structural components
US4416715A (en) * 1978-08-31 1983-11-22 Doralyn Ann Hardy Method and apparatus for fabricating insulative panel
US4510010A (en) * 1980-05-27 1985-04-09 Schramm Arthur G Method and apparatus for fabricating insulative panel
US4715801A (en) * 1981-07-15 1987-12-29 Corning Glass Works Apparatus for high speed manifolding of honeycomb structures
US4964936A (en) * 1988-10-11 1990-10-23 Imi-Tech Corporation Method of making foam-filled cellular structures
US5186999A (en) * 1989-02-17 1993-02-16 Schreiner Luchtvaart Groep B.V. Sandwich material provided with a local reinforcement
US5421935A (en) * 1991-07-12 1995-06-06 Hexcel Corporation Method for making thermally fused thermoplastic honeycomb structures
US5571369A (en) * 1991-07-12 1996-11-05 Hexcel Corporation Apparatus for making thermally fused thermoplastic honeycomb structures
US5635273A (en) * 1991-07-12 1997-06-03 Hexcel Corporation Thermally fused thermoplastic honeycomb structures
US20030175491A1 (en) * 2002-03-15 2003-09-18 Joseph Wycech Method for stiffening or reinforcing a member in a cost effective manner and a member which is made in accordance with the method
US20050112355A1 (en) * 2002-03-15 2005-05-26 Joseph Wycech Method for stiffening or reinforcing a member in a cost effective manner and a member which is made in accordance with the method
US6884055B2 (en) * 2002-05-29 2005-04-26 The Boeing Company Potting compound injection apparatus and method of injecting potting compound into panel cells
US20030222377A1 (en) * 2002-05-29 2003-12-04 The Boeing Company Potting compound injection apparatus and method of injecting potting compound into panel cells
US20050167884A1 (en) * 2002-05-29 2005-08-04 The Boeing Company Method of injecting potting compound into panel cells
US7422715B2 (en) 2002-05-29 2008-09-09 The Boeing Company Method of injecting potting compound into panel cells
US20050208273A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Locally reinforced core structure for composite sandwich structure and method of producing the same
US20050206035A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Method and apparatus for processing open three-dimensional core structures such as folded honeycomb structures
US20050204693A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Method for sealing edges of a core of a composite sandwich structure
US20050208274A1 (en) * 2004-03-17 2005-09-22 Endres Gregor C Composite sandwich structure with integrated reinforcement area and method of producing the same
US7658810B2 (en) 2004-03-17 2010-02-09 Airbus Deutschland Gmbh Method for sealing edges of a core of a composite sandwich structure
US7666493B2 (en) 2004-03-17 2010-02-23 Airbus Deutschland Gmbh Locally reinforced core structure for composite sandwich structure and method of producing the same
US7749420B2 (en) 2004-03-17 2010-07-06 Airbus Deutschland Gmbh Method and apparatus for processing open three-dimensional core structures such as folded honeycomb structures
US8506743B2 (en) 2004-03-17 2013-08-13 Airbus Deutschland Gmbh Composite sandwich structure with integrated reinforcement area and method of producing the same
DE102014118514A1 (de) * 2014-12-12 2016-06-16 Ross Design Gmbh Verfahren zur Herstellung von Leichtbauelementen und Leichtbauelemente
DE102014118514B4 (de) * 2014-12-12 2016-10-06 Ross Design Gmbh Verfahren zur Herstellung von Leichtbauelementen und Leichtbauelemente
EP3396080A1 (de) * 2017-04-24 2018-10-31 Ross Design GmbH Verfahren zur herstellung eines leichtbauelements

Also Published As

Publication number Publication date
DE2316061A1 (de) 1973-10-11
FR2177640A1 (it) 1973-11-09
FR2177640B1 (it) 1975-03-21
GB1420009A (en) 1976-01-07

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