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WO2008148537A1 - Noyau en nid d'abeille particulier à un composant de type sandwich constitué d'au moins deux parties de noyau en nid d'abeille reliées l'une à l'autre et procédé de fabrication dudit noyau en nid d'abeille - Google Patents

Noyau en nid d'abeille particulier à un composant de type sandwich constitué d'au moins deux parties de noyau en nid d'abeille reliées l'une à l'autre et procédé de fabrication dudit noyau en nid d'abeille Download PDF

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Publication number
WO2008148537A1
WO2008148537A1 PCT/EP2008/004444 EP2008004444W WO2008148537A1 WO 2008148537 A1 WO2008148537 A1 WO 2008148537A1 EP 2008004444 W EP2008004444 W EP 2008004444W WO 2008148537 A1 WO2008148537 A1 WO 2008148537A1
Authority
WO
WIPO (PCT)
Prior art keywords
honeycomb
core
projections
another
elements
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.)
Ceased
Application number
PCT/EP2008/004444
Other languages
English (en)
Inventor
Christian Wolf
Oleg Graf
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 GmbH
Original Assignee
Airbus Operations GmbH
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 GmbH filed Critical Airbus Operations GmbH
Publication of WO2008148537A1 publication Critical patent/WO2008148537A1/fr
Anticipated expiration legal-status Critical
Ceased 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
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/02—Preparation of the material, in the area to be joined, prior to joining or welding
    • B29C66/022—Mechanical pre-treatments, e.g. reshaping
    • B29C66/0224—Mechanical pre-treatments, e.g. reshaping with removal of material
    • B29C66/02241—Cutting, e.g. by using waterjets, or sawing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/114—Single butt joints
    • B29C66/1142—Single butt to butt joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/20—Particular design of joint configurations particular design of the joint lines, e.g. of the weld lines
    • B29C66/22—Particular design of joint configurations particular design of the joint lines, e.g. of the weld lines said joint lines being in the form of recurring patterns
    • B29C66/227—Particular design of joint configurations particular design of the joint lines, e.g. of the weld lines said joint lines being in the form of recurring patterns being in the form of repetitive interlocking undercuts, e.g. in the form of puzzle cuts
    • B29C66/2272—Teardrop-like, waterdrop-like or mushroom-like interlocking undercuts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/725—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs
    • B29C66/7254—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs honeycomb structures
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/01—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/565—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits involving interference fits, e.g. force-fits or press-fits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/731—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the intensive physical properties of the material of the parts to be joined
    • B29C66/7313—Density
    • B29C66/73132—Density of different density, i.e. the density of one of the parts to be joined being different from the density of the other part
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/07—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of multiple interengaging protrusions on the surfaces, e.g. hooks, coils

Definitions

  • Honeycomb core particularly for a sandwich-type component, consisting of at least two honeycomb-core parts connected to one another, and method of manufacturing said honeycomb core
  • the present invention relates to a honeycomb core consisting of at least two honeycomb-core parts which are connected to one another, and to a method of manufacturing a honeycomb core of this kind.
  • honeycomb cores which are also called “honeycomb inserts” are an essential part of sandwich-type components, for example sandwich panels.
  • Sandwich panels which consist of a honeycomb core provided with thin-walled coverings, show high stiffness and bending strength albeit low weight. Because of these properties, sandwich panels are used in many fields of technology, for example aircraft construction, vehicle manufacture, astronautics and building. Sandwich panels are particularly important, for example, for fitting-out the inside of aircraft.
  • the walls, for instance, of the luggage storage systems in the passenger cabin of an aircraft, which are usually constructed as overhead luggage bins, consist of sandwich panels in which a honeycomb core made of paper honeycombs impregnated with synthetic resin is disposed between two covering panels made of glass fibre-reinforced and/or carbon fibre-reinforced composite laminates impregnated with synthetic resin.
  • Sandwich panels or sandwich-type components produced in this way are very light and yet robust.
  • the desire still remains, even with respect to sandwich-type components of this kind, to produce these in a still more light-weight manner than hitherto, without thereby impairing their robustness in practical use.
  • the underlying object of the invention is to indicate a solution to this problem.
  • this object is achieved, starting from a honeycomb core which consists of at least two honeycomb-core parts which are connected to one another, in that two honeycomb-core parts at a time are joined together or fitted together, at edges that face towards one another, by means of a honeycomb-core interlocking system.
  • Two honeycomb-core parts, respectively, which have been fitted together in this way accordingly form, at their edges which have been joined together, a connection which leads, because of the interlocking system, to a shear- resistant connection of the two honeycomb-core parts, without it being necessary to bond said two honeycomb-core parts to one another, as has hitherto been customary, at their connecting point, which is also referred to as the "abutment point".
  • honeycomb core according to the invention can be additionally secured, at the connecting point or points between honeycomb-core parts, with a thin layer of adhesive which is much thinner than adhesive joints which have hitherto been customary, however this is not essential in order to obtain a shear-resistant connection of the honeycomb-core parts to one another.
  • the honeycomb-core interlocking system is preferably constructed as an undercut form-locking (positive engagement) connection.
  • undercutting means, in particular, an undercut portion in the region of the lateral flanks of the honeycomb-core interlocking system, i.e. the undercut portion is produced in such a way that two honeycomb-core parts which are joined together in one plane cannot be detached from one another by a tensile load occurring in the said plane, because the positive engagement between the two honeycomb-core parts which is produced by the undercut portion prevents this.
  • the invention also makes it possible to markedly reduce their weight by using honeycomb-core parts having densities which differ from one another. For example, use may be made, in those regions of a sandwich-type component in which the requirements as regards strength are lower than in other regions, of honeycomb-core parts having a lower density and, accordingly, a lower tensile strength or compressive strength, without this having detrimental effects upon the practically relevant robustness of the component as a whole.
  • Honeycomb cores which consist of a number of honeycomb- core parts having different weights per unit area therefore combine the advantage of eliminating an adhesive joint between said parts with the advantage of a design of said honeycomb-core parts which is selected in an optimum manner in dependence upon the loading, and thus make it possible to produce, in particular, large sandwich- type components so as to be markedly lighter in weight than hitherto.
  • the honeycomb-core parts are substantially flat, as is generally customary in the case of sandwich-type components, i.e. their height is small in relation to their length and breadth.
  • the honeycomb-core parts preferably consist of synthetic-resin-impregnated paper honeycombs, which may be reinforced with aramide fibres.
  • the paper honeycombs preferably have a rectangular or hexagonal cross-section; however other honeycomb cross-sections are possible.
  • the honeycomb-core interlocking system consists of projections and of corresponding recesses which are associated with said projections. Accordingly, there is associated with each projection on the edge of a honeycomb-core part a corresponding recess on that edge of the other honeycomb-core part which faces towards it.
  • the profile which is produced in this way projects the connecting point between two honeycomb-core parts onto an area, so that any loading in the plane of the honeycomb core is distributed over a connecting region.
  • the abutting edge between two honeycomb-core parts that are connected to one another therefore no longer acts as a preset breaking point, as in the prior art, in which the connecting point between two honeycomb-core parts forms a straight line.
  • the projections are disposed on the edge of one honeycomb-core part, and the corresponding recesses are disposed on that edge of the other honeycomb-core part which faces it.
  • those edges of the honeycomb-core parts which face towards one another consist, at least in certain sections, of projections and recesses which immediately succeed one another and are disposed in an alternating manner, wherein the recesses correspond with the projections on the opposing edge.
  • said projections are advantageously slightly larger, at least locally, on at least one of the two edges to be connected, than the corresponding recesses.
  • the shape of the projections, and of the recesses that correspond with the latter, may be multifarious, so long as the abovedescribed interlocking system in the plane of the honeycomb-core parts which are to be connected to one another is ensured.
  • the projections are tongue-shaped. Notches at the connecting point of the two honeycomb-core parts which are to be connected are to be avoided.
  • a recess may be circle-shaped in the region of its base, while the contour of the projection associated with the said recess has a defined oversize in this region, i.e. the associated projection is slightly larger than the recess, at least in certain sections.
  • said tongue-shaped projections preferably have an oversize of this kind, with respect to the corresponding recess, in the region of the point of their tongue.
  • the oversize of a projection with respect to the recess associated with it may, however, also be produced by a deviation in the shape of the projection with respect to the corresponding recess.
  • the point of the tongue of a tongue-shaped projection may be of slightly oval construction and be associated with a recess whose opening in this region is bounded by a circular section.
  • an identically-shaped oversize of the projection can also be combined with a certain deviation in shape with respect to the corresponding recess, i.e. a projection may have, with respect to the recess associated with it, both a certain identically-shaped oversize and also a certain deviation in shape.
  • the strength of the connecting point is the greater, the better the two honeycomb- core parts interlock with one another, if possible along their entire butt joint, and the fewer points said butt joint has which are not filled up.
  • individual recesses or all the recesses have, at the edge at which individual projections or all the projections have an oversize, an undersize compared to the corresponding projection.
  • the object initially mentioned is also achieved, according to the invention, by means of a method of manufacturing a honeycomb core which consists of two honeycomb- core parts which are connected to one another, wherein said method comprises the following steps: shaping of elements on one edge of a first honeycomb-core part and of counter-elements on an edge of a second honeycomb-core part that faces towards said edge of the first honeycomb-core part such that the elements and counter- elements are adapted to be joined together forming a honeycomb-core interlocking system; and inserting or fitting into one another of the edges, that have been constructed in such a way, of the two honeycomb-core parts to form the honeycomb core.
  • the elements and counter-elements of the at least two honeycomb-core parts may be formed in any suitable way.
  • the elements and counter-elements are shaped by cutting the relevant edge of the honeycomb-core part, the cutting operation preferably taking place by means of water-jet cutting.
  • the shape of the elements and counter-elements may be chosen in almost any desired manner, so long as it is ensured that the two or more honeycomb-core parts interlock with one another after their edges have been joined or fitted together.
  • the interlocking system is preferably provided with undercut portions, i.e. the honeycomb-core interlocking system has undercut portions by means of which the two honeycomb-core parts hook into one another, so that the pulling-apart of two honeycomb-core parts which are connected to one another is prevented in the plane of said parts.
  • the elements are tongue-shaped projections and the counter-elements are tongue-shaped recesses which are constructed so as to correspond with said tongue-shaped projections.
  • the undercut portions are preferably produced in the region of the flanks of the elements and counter- elements.
  • At least one of the joining partners is slightly deformed, at least locally, for example by compressing or crushing. This ensures satisfactory interlocking of the two edges of the honeycomb-core parts in the region of the butt joint and faultless filling-up of said butt joint, a fact which strengthens the mechanical bonding at the connecting point.
  • honeycomb core according to the invention and the method of manufacturing make it possible, particularly in the case of sandwich-type components of large area, to optimise the honeycomb-core material in lightly loaded regions of the said components, e.g. regions without bending stresses, by using a honeycomb-core material which is lighter with respect to the overall weight. It is likewise possible to dispense with conventional connection of the honeycomb cores by means of relatively thick adhesive joints, and also with the extra weight this causes. All in all, it is thereby possible to achieve a considerable saving in weight, without reducing the durability of the sandwich-type component.
  • figure 1 is a three-dimensional view of two honeycomb-core parts which are to be connected to one another and whose edges that face towards one another are provided with a honeycomb-core interlocking system according to the invention;
  • figure 2 shows a detail view of the connecting point of the two honeycomb-core parts from figure 1, in the connected state
  • figure 3 is a plan view, similar to figure 2, which shows the undulating path of the butt joint and the interlocking of individual honeycomb elements in the region of said butt joint on the basis of a slight oversize of one joining partner.
  • Figure 1 shows a honeycomb core, which is designated generally by 10, for a panel- shaped sandwich-type component of which no further representation is given and which consists of a first honeycomb-core part 12 and a second honeycomb-core part 14.
  • the two honeycomb-core parts 12, 14 are, themselves, panel-shaped parts and 5 consist, in the embodiment shown, of synthetic-resin-impregnated paper honeycombs reinforced with aramide fibres, each honeycomb having a hexagonal cross-section (in this connection, see also figure 3).
  • the two honeycomb-core parts 12, 14 are to be connected to one another to form ao large honeycomb core 10.
  • the first honeycomb-core part 12 in the example shown consists of a material whose density is greater than the density of the material of which the second honeycomb-core part 14 consists. More precisely, thes material of the first honeycomb-core part 12 has a density of 48 kg/m 3 and the material of the second honeycomb-core part 14, a density of 29 kg/m 3 .
  • a lower density of the honeycomb material used for manufacturing a honeycomb-core part usually also results in lower strength.
  • the honeycomb core 10 After the connection of the two honeycomb- core parts 12, 14 to form a honeycomb core 10, the honeycomb core 10 thus0 obtained is covered on both sides with a layer of a composite laminate material in order to form a sandwich panel from which it is then possible to produce components, for example for fitting-out the inside of aircraft.
  • the composite laminate used for covering purposes may be, for example, a glass fibre-reinforced or carbon fibre-reinforced, synthetic-resin-impregnated composite laminate.
  • the honeycomb core 10 acts as a shear web and keeps the two layers of composite laminate apart.
  • edges of the twoo honeycomb-core parts 12, 14 which face towards one another are constructed in an undulating profile fashion.
  • one edge 16 of the first honeycomb-core part 12 has a series of projections 18 which correspond with corresponding recesses 20 which are constructed on an opposing edge 22 of the second honeycomb-core part 14.
  • the edge 16 has recesses 20' which are disposed in a manner 5 alternating with the projections 18 and which correspond with projections 18 1 on the edge 22.
  • Each edge 16, 22 is therefore represented, at least in certain sections, as a succession of projections 18 and recesses 20', or projections 18' and recesses 20.
  • the projections 18, 18' are of tongue-shaped construction in the embodiment shown, with recesses 20, 20' which correspond with said projections, so that, after the two edges 16, 22 have been joined together or inserted into one another, there is produced, between the two honeycomb-core parts 12, 14, a honeycomb-core interlocking system 24 which, in the embodiment shown, is produced as an undercut form-locking connection. More precisely, each projection 18, 18' is initially of narrower design at its base which is connected to the corresponding honeycomb-core part 12 or 14, respectively, and then merges into a broader head part which converges at the point of the tongue.
  • Figure 2 shows a plan view of part of the honeycomb-core interlocking system 24 of figure 1 on an enlarged scale and in the connected state. So that the butt joint between the two edges 16 and 22 is completely filled up with material of the honeycomb-core parts 12, 14, and so that the individual honeycombs hook together with one another satisfactorily in the region of said butt joint, the projections 18 on the first honeycomb-core part 12 are constructed with a certain oversize compared to the corresponding recesses 20 in the second honeycomb-core part 14. Moreover, the recesses 20' in the first honeycomb-core part 12 are constructed with a certain undersize with respect to the corresponding projections 18" on the second honeycomb-core part 14.
  • R + x the radius of the projections 18 in the region of their head
  • R - x the radius of the recesses 20'
  • the oversize or undersize x is chosen in dependence upon the size of the projections 18, 18' and recesses 20, 20' and in dependence upon the properties of the material of which the honeycomb-core parts 12, 14 consist, and in particular, in dependence upon the cell width of the honeycomb. Also, the oversize does not have to be equal to the undersize, but the two sizes can be chosen independently of one another and may even be zero.
  • R + x has a value of 32 mm and R - x, a value of 28 mm, i.e.
  • x 2 mm.
  • the distance between the centre points of two consecutive projections 18', which corresponds to the distance between the centre points of two consecutive recesses 20', is 2y.
  • the distance (in the longitudinal direction of the honeycomb- core interlocking system 24) between the centre point of a recess 20' and the centre point of a succeeding projection 18 is y, the latter being 50 mm in the example shown.
  • the projection 18 not only has an oversize with respect to the corresponding recess 20, but also a certain deviation in shape. Whereas the recess 20 has a circular contour, the head of the projection 18 is of slightly oval design, in order to bring about, in this way, a higher contact pressure in the butt joint in the region of the point of the tongue.
  • Figure 3 represents a photograph of two honeycomb-core parts 12, 14 which are joined to one another in a manner corresponding to figure 2. It can be clearly seen from figure 3 that the measures described with reference to figure 2 lead to the honeycombs disposed in the region of the butt joint interlocking together in the correct manner and to said butt joint being filled up completely with honeycomb material.
  • the projections have a tongue-shaped contour
  • other shapes of many kinds by means of which the objective of a honeycomb-core interlocking system, and in particular of an undercut form-locking connection between two honeycomb-core parts 12, 14, can likewise be achieved, are possible for the projections and associated recesses.
  • the honeycomb-core interlocking system 24 has undercut portions in such a way that the two honeycomb-core parts 12, 14 cannot be separated from one another by a tensile load occurring in the plane of the honeycomb-core 10, and that no notches are produced.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

La présente invention concerne un noyau en nid d'abeille (10) particulier à un composant de type sandwich qui est constitué d'au moins deux parties de noyau en nid d'abeille (12, 14) reliées l'une à l'autre. Pour un gain de poids au moins deux noyaux (12, 14) sont reliés en même temps au niveau des bords (16, 22) se faisant face au moyen d'un système d'emboîtement des noyaux en nid d'abeille (24).
PCT/EP2008/004444 2007-06-06 2008-06-04 Noyau en nid d'abeille particulier à un composant de type sandwich constitué d'au moins deux parties de noyau en nid d'abeille reliées l'une à l'autre et procédé de fabrication dudit noyau en nid d'abeille Ceased WO2008148537A1 (fr)

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US94224307P 2007-06-06 2007-06-06
US60/942,243 2007-06-06
DE102007026296A DE102007026296A1 (de) 2007-06-06 2007-06-06 Wabenkern, insbesondere für ein Sandwichbauteil, aus wenigstens zwei miteinander verbundenen Wabenkernteilen und Verfahren zu seiner Herstellung
DE102007026296.7 2007-06-06

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CN104786558A (zh) * 2014-01-21 2015-07-22 波音公司 夹层结构复合材料及其制造方法和飞机
FR3019774A1 (fr) * 2014-04-14 2015-10-16 Astrium Sas Piece polygonale a alveoles pour une ame de panneau, en particulier de reflecteur d'antenne de satellite
DE102014215661A1 (de) 2014-08-07 2016-02-11 Airbus Operations Gmbh Flugzeuginnenverkleidungsbauteil, Verfahren zur Herstellung eines Flugzeuginnenverkleidungsbauteils und Flugzeugbaugruppe
JP2018122444A (ja) * 2017-01-30 2018-08-09 昭和飛行機工業株式会社 ハニカムコアの連結方法、および連結ハニカムコア
CN108870058A (zh) * 2018-08-29 2018-11-23 徐卫国 一种采用开槽法消除压缩峰值的蜂窝芯及其加工方法
US20190112066A1 (en) * 2017-10-16 2019-04-18 Rohr, Inc. Structural panel with splice joint between adjacent core structures

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DE102010034084A1 (de) 2010-08-12 2012-02-16 Airbus Operations Gmbh Flugzeuginnenverkleidungsbauteil und Verfahren zur Herstellung eines Flugzeuginnenverkleidungsbauteils
DE102016222435B4 (de) 2016-11-15 2018-09-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Sandwichelement, tragende Struktur und Fahrzeug
DE202018101146U1 (de) * 2018-03-01 2019-06-04 Reinz-Dichtungs-Gmbh Temperierplatte

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CN104786558A (zh) * 2014-01-21 2015-07-22 波音公司 夹层结构复合材料及其制造方法和飞机
EP2896498A1 (fr) * 2014-01-21 2015-07-22 The Boeing Company Appareil composite à structure sandwich avec procédé d'assemblage d'âme et d'épissure pour le maintien des capacités acoustiques et structurelles
CN104786558B (zh) * 2014-01-21 2020-10-16 波音公司 夹层结构复合材料及其制造方法和飞机
FR3019774A1 (fr) * 2014-04-14 2015-10-16 Astrium Sas Piece polygonale a alveoles pour une ame de panneau, en particulier de reflecteur d'antenne de satellite
WO2015158966A1 (fr) * 2014-04-14 2015-10-22 Airbus Defense And Space Sas Pièce polygonale à alvéoles pour une âme de panneau, en particulier de réflecteur d'antenne de satellite
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DE102014215661A1 (de) 2014-08-07 2016-02-11 Airbus Operations Gmbh Flugzeuginnenverkleidungsbauteil, Verfahren zur Herstellung eines Flugzeuginnenverkleidungsbauteils und Flugzeugbaugruppe
US10710697B2 (en) 2014-08-07 2020-07-14 Airbus Operations Gmbh Aircraft interior lining component, method for producing an aircraft interior lining component, and aircraft assembly
JP2018122444A (ja) * 2017-01-30 2018-08-09 昭和飛行機工業株式会社 ハニカムコアの連結方法、および連結ハニカムコア
US20190112066A1 (en) * 2017-10-16 2019-04-18 Rohr, Inc. Structural panel with splice joint between adjacent core structures
US10994856B2 (en) * 2017-10-16 2021-05-04 Rohr, Inc. Structural panel with splice joint between adjacent core structures
CN108870058A (zh) * 2018-08-29 2018-11-23 徐卫国 一种采用开槽法消除压缩峰值的蜂窝芯及其加工方法

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