FR2686043A1 - Method of producing a structural panel of the sandwich type, and panel thus obtained - Google Patents
Method of producing a structural panel of the sandwich type, and panel thus obtained Download PDFInfo
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- FR2686043A1 FR2686043A1 FR9200308A FR9200308A FR2686043A1 FR 2686043 A1 FR2686043 A1 FR 2686043A1 FR 9200308 A FR9200308 A FR 9200308A FR 9200308 A FR9200308 A FR 9200308A FR 2686043 A1 FR2686043 A1 FR 2686043A1
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- Prior art keywords
- panel
- skins
- heat
- sealable
- insert
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Classifications
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- 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 form; Layered products 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 form; Layered products 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 form; Layered products 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
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- 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
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- 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
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
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- 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
- E04C2/02—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials
- E04C2/10—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials of wood, fibres, chips, vegetable stems, or the like; of plastics; of foamed products
- E04C2/20—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials of wood, fibres, chips, vegetable stems, or the like; of plastics; of foamed products of plastics
-
- 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
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- 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
- B32B2250/00—Layers arrangement
- B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
-
- 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
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- 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
Abstract
Description
La présente invention est relative à un procédé de réalisation en une seule opération d'un panneau structurel du type sandwich dans lequel on incorpore un ou plusieurs inserts métalliques destinés au renforcement dudit panneau et/ou à des fixations ultérieures sur ce panneau. The present invention relates to a method for producing in a single operation a structural panel of the sandwich type in which one or more metallic inserts are incorporated intended for the reinforcement of said panel and / or for subsequent fastenings on this panel.
L'invention vise également un panneau structurel composite obtenu par la mise en oeuvre de ce procédé, ce panneau étant destiné notamment à l'industrie automobile et du transport pour réaliser des pièces de formes complexes.The invention also relates to a composite structural panel obtained by the implementation of this method, this panel being intended in particular for the automobile and transport industry for producing parts of complex shapes.
On connaît à l'heure actuelle dans l'industrie, et notamment dans l'industrie automobile, des éléments réalisés en matériaux thermoplastiques dans lesquels il est nécessaire d'incorporer des inserts métalliques, ces éléments de formes complexes pouvant être obtenus par estampage. Selon la technique actuelle, on met en oeuvre des processus de collage pour solidariser les différents constituants des panneaux composites à partir desquels sont réalisés de tels éléments. Cette technique ne donne pas totale satisfaction en raison notamment de la complexité du procédé de fabrication qui nécessite plusieurs opérations. Currently known in the industry, and in particular in the automotive industry, elements made of thermoplastic materials in which it is necessary to incorporate metal inserts, these elements of complex shapes can be obtained by stamping. According to the current technique, bonding processes are used to secure the various constituents of the composite panels from which such elements are made. This technique is not entirely satisfactory, in particular because of the complexity of the manufacturing process which requires several operations.
La présente invention s'est donc fixé pour objectif d'apporter un procédé de réalisation en une seule opération d'un panneau structurel du type sandwich dans lequel sont incorporés des inserts métalliques.The present invention has therefore set itself the objective of providing a process for producing, in a single operation, a structural panel of the sandwich type in which metal inserts are incorporated.
A cet effet, la présente invention vise en premier lieu à un procédé de fabrication en une seule opération d'un panneau structurel composite, du type sandwich constitué d'une âme alvéolaire en matière thermoplastique, de deux peaux en matière thermoplastique renforcée du type thermoplastique renforcé fibres, disposées perpendiculairement à l'axe des alvéoles de ladite âme, dans le cas d'une âme en nids d'abeille, et d'un ou plusieurs inserts métalliques destinés notamment au renforcement du panneau et/ou à des fixations ultérieures sur ce panneau, ce procédé étant caractérisé en ce que l'on préchauffe lesdites peaux à une température de l'ordre de 200 à 220"C afin de les rendre malléables et de favoriser leur accrochage par thermosoudage aux alvéoles de ladite âme et en ce que l'on préchauffe le ou lesdits inserts métalliques avant de réaliser un empilage des différents éléments dans un outillage de mise en forme du panneau. To this end, the present invention aims firstly at a method of manufacturing in a single operation a composite structural panel, of the sandwich type consisting of a cellular core of thermoplastic material, of two skins of reinforced thermoplastic material of the thermoplastic type. reinforced fibers, arranged perpendicular to the axis of the cells of said core, in the case of a honeycomb core, and one or more metal inserts intended in particular for the reinforcement of the panel and / or for subsequent fastenings on this panel, this process being characterized in that said skins are preheated to a temperature of the order of 200 to 220 "C in order to make them malleable and to promote their attachment by heat-sealing to the cells of said core and in that said metal insert (s) is preheated before stacking the various elements in a tool for shaping the panel.
Selon un mode de mise en oeuvre du procédé, objet de l'invention on dispose une pellicule thermoplastique, thermoscellable entre l'insert métallique et les peaux, lors de l'empilage des différents éléments constituant le panneau, afin de solidariser ledit insert auxdites peaux, après refroidissement du panneau, et en ce que la température de préchauffage dudit insert présente une valeur suffisamment élevée pour éviter une absorption trop rapide des calories apportées par lesdites peaux et nécessaires à la fusion de ladite pellicule thermoscellable. According to one embodiment of the method, object of the invention, there is a thermoplastic film, heat-sealable between the metal insert and the skins, during the stacking of the various elements constituting the panel, in order to secure said insert to said skins. , after cooling of the panel, and in that the preheating temperature of said insert has a sufficiently high value to avoid too rapid absorption of the calories provided by said skins and necessary for the melting of said heat-sealable film.
Selon un autre mode de mise en oeuvre du procédé, objet de cette invention, le ou les inserts métalliques sont pré-revêtus d'une pellicule thermoplastique, thermoscellable permettant de réaliser une solidarisation dudit insert auxdites peaux après refroidissement du panneau et en ce que la température de préchauffage du ou des inserts métalliques présente une valeur suffisamment élevée pour ne pas absorber trop rapidement les calories apportées par les peaux et servant à la fusion de la pellicule thermoscellable. According to another embodiment of the process which is the subject of this invention, the metal insert (s) are pre-coated with a thermoplastic film, heat-sealable making it possible to secure said insert to said skins after the panel has cooled and in that the the preheating temperature of the metal insert (s) has a value high enough not to absorb the calories brought on by the skins too quickly and used for melting the heat-sealable film.
Selon encore un autre mode de mise en oeuvre du procédé selon la présente invention, la solidarisation du ou des inserts métalliques avec lesdites peaux est réalisée mécaniquement après fluage et refroidissement d'une partie du matériau constituant lesdites peaux dans les reliefs en saillie ou en creux du ou des inserts, ces derniers étant préchauffés à une température suffisante pour favoriser ledit fluage dans une limite désirée. According to yet another embodiment of the method according to the present invention, the attachment of the metal insert (s) with said skins is carried out mechanically after creep and cooling of part of the material constituting said skins in the raised or recessed reliefs or inserts, the latter being preheated to a temperature sufficient to promote said creep within a desired limit.
La présente invention vise également un panneau structurel composite du type sandwich réalisé par la mise en oeuvre du procédé défini ci-dessus, ce panneau étant caractérisé essentiellement en ce qu'il comporte une âme alvéolaire en matière thermoplastique munie sur ses faces de peaux en matière thermoplastique renforcée du type thermoplastique renforcé fibres, disposées perpendiculairement à l'axe des alvéoles de ladite âme et au moins un insert métallique faisant partie intégrante du panneau. The present invention also relates to a composite structural panel of the sandwich type produced by the implementation of the method defined above, this panel being essentially characterized in that it comprises a cellular core of thermoplastic material provided on its faces with skins of material reinforced thermoplastic of the fiber reinforced thermoplastic type, arranged perpendicular to the axis of the cells of said core and at least one metal insert forming an integral part of the panel.
D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ciaprès en référence aux dessins annexés qui en illustrent des modes de mise en oeuvre et des exemples de réalisation dépourvus de tout caractère limitatif. Sur les dessins
la figure 1 est une vue schématique en perspective illustrant l'étape du procédé selon l'invention au cours de laquelle un insert métallique est pré-revêtu d'une pellicule thermoscellable
la figure 2 est également une vue en perspective illustrant la réalisation, selon le procédé de l'invention, d'un panneau sandwich composite avec un insert métallique
la figure 3 illustre, par une vue similaire à la figure 2, la réalisation selon l'invention d'un panneau comportant deux inserts métalliques et,
les figures 4 à 9 sont des vues en coupe verticale illustrant divers exemples de réalisation de pannneaux avec inserts métalliques de diverses configurations obtenus par la mise en oeuvre du procédé objet de l'invention.Other characteristics and advantages of the present invention will emerge from the description given below with reference to the appended drawings which illustrate modes of implementation and examples of embodiment devoid of any limiting character. On the drawings
Figure 1 is a schematic perspective view illustrating the step of the method according to the invention during which a metal insert is pre-coated with a heat-sealable film
Figure 2 is also a perspective view illustrating the embodiment, according to the method of the invention, of a composite sandwich panel with a metal insert
FIG. 3 illustrates, by a view similar to FIG. 2, the embodiment according to the invention of a panel comprising two metal inserts and,
Figures 4 to 9 are views in vertical section illustrating various embodiments of panels with metal inserts of various configurations obtained by the implementation of the method of the invention.
Ainsi qu'on l'a précisé ci-dessus, le procédé objet de l'invention vise à l'obtention en une seule opération d'un panneau structurel composite du type sandwich comportant une âme alvéolaire en nids d'abeille thermoplastique 10, polypropylène dans le présent exemple non limitatif dont les faces sont munies de peaux, 12, 12' en matière thermoplastique renforcée du type thermoplastique renforcé fibres, ces peaux étant disposées perpendiculairement à l'axe des alvéoles de ladite âme 10 ainsi qu'on le voit clairement sur la figure 2. Le panneau composite est également muni d'un ou de plusieurs inserts métalliques, par exemple en aluminium tels que 18 et 18'. As has been specified above, the process which is the subject of the invention aims to obtain in a single operation a composite structural panel of the sandwich type comprising a honeycomb core of thermoplastic honeycomb 10, polypropylene in the present nonlimiting example, the faces of which are provided with skins, 12, 12 ′ of reinforced thermoplastic material of the fiber reinforced thermoplastic type, these skins being arranged perpendicular to the axis of the cells of said core 10, as can be clearly seen in Figure 2. The composite panel is also provided with one or more metal inserts, for example aluminum such as 18 and 18 '.
Selon ce procédé, les peaux 12, 12' sont chauffées à des températures de l'ordre de 200 à 220"C, de façon à les rendre malléables et à obtenir une cohésion peaux 12, 12' - âme 10 par thermosoudure. Ce chauffage des peaux permet également une mise en forme du panneau sous pression. Avant l'empilage des différents éléments constitutifs du panneau dans un outillage de mise en forme, on préchauffe le ou les inserts métalliques tels que 18 ou 18'. Lors de l'empilage, on place les pellicules thermoscellables en polypropylène plus anhydride maléique entre les inserts 18, et 18' et les peaux 12, 12' (figure 3). Cet insert métallique est finalement emprisonné et parfaitement solidarisé après refroidissement dans le panneau ainsi obtenu. According to this process, the skins 12, 12 'are heated to temperatures of the order of 200 to 220 "C, so as to make them malleable and to obtain a cohesion skins 12, 12' - core 10 by heat sealing. This heating skins also allow the panel to be shaped under pressure. Before stacking the various constituent elements of the panel in a shaping tool, the metal insert (s) such as 18 or 18 ′ are preheated. , the heat-sealable polypropylene films plus maleic anhydride are placed between the inserts 18 and 18 'and the skins 12, 12' (FIG. 3). This metallic insert is finally trapped and perfectly secured after cooling in the panel thus obtained.
Selon une variante du procédé de l'invention et comme représenté sur la figure 2, on peut utiliser des inserts pré-revêtus d' une pellicule thermoscellable 14, 14', ce qui facilite la mise en oeuvre ultérieure de l'empilage dans le moule. Pour ce faire, et comme représenté sur la figure 1, la pellicule thermoscellable se présente sous la forme d'un film 14, 14' muni d'un matériau de protection non adhérent constitué par exemple d'un tissu enduit de polytétrafluoroéthylène 16, 16', puis l'ensemble est placé sur les plateaux d'une presse hydraulique dont la température est maintenue entre 200 et 220"C. A titre d'exemple non limitatif, la pression exercée par les plateaux de la presse, peut être de 5.105Pa à 106Pa et le temps d'application peut être de l'ordre d'une minute. According to a variant of the process of the invention and as shown in Figure 2, one can use inserts pre-coated with a heat-sealable film 14, 14 ', which facilitates the subsequent implementation of the stack in the mold . To do this, and as shown in Figure 1, the heat-sealable film is in the form of a film 14, 14 'provided with a non-adherent protective material consisting for example of a fabric coated with polytetrafluoroethylene 16, 16 ', then the assembly is placed on the plates of a hydraulic press whose temperature is maintained between 200 and 220 "C. By way of nonlimiting example, the pressure exerted by the plates of the press, can be 5.105 Pa at 106 Pa and the application time can be of the order of one minute.
On réalise ensuite un préchauffage de l'insert 18 ou 18' muni des pellicules 14, 14' à la température voulue, choisie de façon que l'insert soit suffisamment chaud pour ne pas absorber trop rapidement les calories apportées par les peaux 12, 12' et utile à la fusion des pellicules thermoscellables 14, 14'. Cette température peut être par exemple de l'ordre de 1500C. On réalise alors l'empilage des éléments devant constituer le panneau comme illustré par la figure 2. Cet empilage est mis en place dans un outillage approprié à une température de l'ordre de 60"C et soumis à une pression par exemple de 2.106Pa pendant une durée de 20 secondes. L'épaisseur du matériau composite sandwich finalement obtenu peut être déterminé en prévoyant des cales latérales de dimensions voulues.Dans cet exemple de mise en oeuvre la cohésion insert 18, 18' / sandwich est obtenue grâce à la pellicule thermofusible 14, 14', après refroidissement du panneau. The insert 18 or 18 ′ provided with the films 14, 14 ′ is then preheated to the desired temperature, chosen so that the insert is hot enough not to too quickly absorb the calories provided by the skins 12, 12 'and useful for melting heat-sealable films 14, 14'. This temperature can for example be of the order of 1500C. The elements which are to constitute the panel are then stacked as illustrated in FIG. 2. This stacking is put in place in an appropriate tool at a temperature of the order of 60 "C and subjected to a pressure, for example of 2.106 Pa for a period of 20 seconds. The thickness of the composite sandwich material finally obtained can be determined by providing lateral shims of desired dimensions. In this example of implementation, the cohesion of the insert 18, 18 ′ / sandwich is obtained by the film. hot-melt 14, 14 ', after cooling of the panel.
Selon la présente invention, la solidarisation entre le ou les inserts métalliques et les peaux telles que 12, 12' peut être réalisé mécaniquement après fluage (lors de l'opération de complexage) et refroidissement d'une partie de la matière constitutive des peaux 12, 12' dans les reliefs de l'insert, la température de ce dernier étant d'une valeur suffisante pour favoriser ce fluage dans la limite désirée. La figure 9 illustre un panneau ainsi obtenu, on y voit en 30, 30' les rivets obtenus par fluage du matériau constituant les peaux 12, 12' au travers d'ouvertures prévues dans l'insert métallique 28. According to the present invention, the connection between the metal insert (s) and the skins such as 12, 12 ′ can be carried out mechanically after creep (during the lamination operation) and cooling of part of the material constituting the skins 12 , 12 ′ in the reliefs of the insert, the temperature of the latter being of a sufficient value to promote this creep within the desired limit. FIG. 9 illustrates a panel thus obtained, we see at 30, 30 'the rivets obtained by creep of the material constituting the skins 12, 12' through openings provided in the metal insert 28.
Les inserts métalliques faisant partie intégrante des panneaux selon l'invention peuvent présenter toutes formes et configurations désirées. Sur les figures 1 à 4 et 9, ces inserts présentent la forme de tubes et sur les figures 5 à 6 ils présentent la forme de profilés de diverses configurations 20, 20', 22, 24, 26. Ils peuvent être totalement noyés dans le panneau comme représentés par les inserts 20, 20', 22 et 26 sur les figures 5, 6 et 8. Le métal utilisé pour la fabrication des inserts est de préférence de l'aluminium, car la structure de surface de ce métal, proche du verre, permet un bon accrochage en présence d'anhydride maléique. The metal inserts forming an integral part of the panels according to the invention can have any desired shape and configuration. In Figures 1 to 4 and 9, these inserts are in the form of tubes and in Figures 5 to 6 they are in the form of profiles of various configurations 20, 20 ', 22, 24, 26. They can be completely embedded in the panel as represented by the inserts 20, 20 ′, 22 and 26 in FIGS. 5, 6 and 8. The metal used for the manufacture of the inserts is preferably aluminum, since the surface structure of this metal, close to the glass, allows good adhesion in the presence of maleic anhydride.
Ainsi, et selon la présente invention, la solidarisation inserts-panneau composite sandwich peut être obtenu soit par la présence des pellicules thermoscellables, soit par accrochage mécanique ou par toutes solutions combinant ces deux modes de mise en oeuvre, avec ou sans emprisonnement multidirectionnel. Thus, and according to the present invention, the joining of inserts to sandwich composite panel can be obtained either by the presence of heat-sealable films, or by mechanical attachment or by any solutions combining these two modes of implementation, with or without multidirectional imprisonment.
L'invention permet donc d'obtenir des panneaux ou pièces structurelles composites avec inserts incorporés, se caractérisant notamment par les avantages suivants
- excellente résistance aux chocs
- très bonne rigidité de la structure réalisée permettant par exemple la réalisation de châssis monobloc de véhicules
- légèreté ;
- bonne isolation acoustique et thermique
- possibilité de prévoir des revêtements extérieurs permettant d'apporter au panneau des fonctions supplémentaires : complément d'isolation phonique, acoustique ou thermique, effets "barrière", décoration, etc... sous la forme de plaques minces ou de moquettes à matrice thermoplastique.The invention therefore makes it possible to obtain composite structural panels or parts with incorporated inserts, characterized in particular by the following advantages
- excellent impact resistance
- very good rigidity of the structure made, for example making one-piece chassis of vehicles
- lightness;
- good acoustic and thermal insulation
- possibility of providing external coverings to provide additional functions to the panel: additional sound, acoustic or thermal insulation, "barrier" effects, decoration, etc. in the form of thin sheets or carpets with thermoplastic matrix .
ll demeure bien entendu que la présente invention n'est pas limitée aux divers exemples de mise en oeuvre ou de réalisation décrits et/ou représentés ici, mais qu'elle en englobe toutes les variantes. C'est ainsi, notamment, que les pellicules thermoscellables telles que 14, 14' pourraient être appliquées sous la forme d'un film ou d'une poudre, par exemple par dépôt électrostatique ou en lit fluidisé. It remains to be understood that the present invention is not limited to the various examples of implementation or embodiment described and / or shown here, but that it encompasses all variants thereof. Thus, in particular, that the heat-sealable films such as 14, 14 ′ could be applied in the form of a film or a powder, for example by electrostatic deposition or in a fluidized bed.
Dans le cas d'un film, ce dernier peut être perforé ou non, les perforations permettant à l'air chaud emprisonné lors de l'application du film sur l'insert de s 'échapper plus facilement. In the case of a film, the latter may or may not be perforated, the perforations allowing the hot air trapped during the application of the film to the insert to escape more easily.
Dans les exemples représentés sur les figures 1 à 9, les panneaux ont été représentés plans et à faces parallèles, mais il est tout à fait possible d'obtenir des panneaux similaires à configurations autres (bombés, courbés, nervurés...) du fait de leur composition thermoplastique et des températures de mise en oeuvre entraînant un certain ramoXissement de la matière. In the examples represented in FIGS. 1 to 9, the panels have been shown planes and with parallel faces, but it is quite possible to obtain similar panels with other configurations (curved, curved, ribbed, etc.) because of their thermoplastic composition and processing temperatures causing a certain softening of the material.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9200308A FR2686043A1 (en) | 1992-01-14 | 1992-01-14 | Method of producing a structural panel of the sandwich type, and panel thus obtained |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9200308A FR2686043A1 (en) | 1992-01-14 | 1992-01-14 | Method of producing a structural panel of the sandwich type, and panel thus obtained |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR2686043A1 true FR2686043A1 (en) | 1993-07-16 |
| FR2686043B1 FR2686043B1 (en) | 1995-04-21 |
Family
ID=9425608
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR9200308A Granted FR2686043A1 (en) | 1992-01-14 | 1992-01-14 | Method of producing a structural panel of the sandwich type, and panel thus obtained |
Country Status (1)
| Country | Link |
|---|---|
| FR (1) | FR2686043A1 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0649736A1 (en) * | 1993-10-22 | 1995-04-26 | Etablissements Manducher | Motor vehicle back shelf and method for its manufacture |
| WO1998004398A1 (en) * | 1996-07-30 | 1998-02-05 | Peguform France | Forming an insert in a panel made of a sandwich-type composite material with a cellular core |
| FR2768076A1 (en) * | 1997-09-10 | 1999-03-12 | Peguform France | METHOD FOR PRODUCING A RIGIDIFIED ZONE INSERT FORMING IN A COMPOSITE SANDWICH PANEL, AND PANEL COMPRISING SUCH A ZONE |
| WO1999016660A1 (en) * | 1997-09-17 | 1999-04-08 | Ab Volvo | Load-carrying vehicle structure of composite material and method for its moulding |
| WO2005010293A1 (en) * | 2003-07-28 | 2005-02-03 | Xiamen New Technology Integrat | A paper honeycomb core composite panel |
| WO2006102090A1 (en) * | 2005-03-23 | 2006-09-28 | The Boeing Company | Integrated aircraft structural floor |
| AT503213B1 (en) * | 2006-01-27 | 2007-10-15 | Fischer Gmbh | SKIKERN WITH HOLLY CONSTRUCTION |
| EP2818415A1 (en) * | 2013-06-27 | 2014-12-31 | Airbus Operations GmbH | Panel member for an airframe |
| FR3032905A1 (en) * | 2015-02-24 | 2016-08-26 | Airbus Defence & Space Sas | COMPOSITE PANEL HAVING AN IMPROVED ASSEMBLY TERMINATION AND STRUCTURE COMPRISING SUCH A PANEL |
| FR3032908A1 (en) * | 2015-02-24 | 2016-08-26 | Airbus Defence & Space Sas | REINFORCED COMPOSITE PANEL |
| EP3144125A1 (en) * | 2015-09-17 | 2017-03-22 | The Boeing Company | Panel and associated closeout method |
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| DE3643688A1 (en) * | 1985-12-28 | 1987-07-02 | Sumitomo Light Metal Ind | PANEL ARRANGEMENT WITH HONEYCOMB STRUCTURE |
| DE3644676A1 (en) * | 1986-12-30 | 1988-07-14 | Schladitz Klaus | Process for producing lightweight structural parts |
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| FR1513551A (en) * | 1967-01-06 | 1968-02-16 | Process for producing composite walls and composite walls thus obtained | |
| GB1475945A (en) * | 1974-05-24 | 1977-06-10 | Ver Flugtechnische Werke | Cellular panel having reinforcing inserts |
| US4106962A (en) * | 1977-07-14 | 1978-08-15 | Ncr Corporation | Method of fastening metal part to plastic part |
| DE3643688A1 (en) * | 1985-12-28 | 1987-07-02 | Sumitomo Light Metal Ind | PANEL ARRANGEMENT WITH HONEYCOMB STRUCTURE |
| DE3644676A1 (en) * | 1986-12-30 | 1988-07-14 | Schladitz Klaus | Process for producing lightweight structural parts |
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|---|---|---|---|---|
| FR2711573A1 (en) * | 1993-10-22 | 1995-05-05 | Manducher Sa | Motor vehicle rear shelf and manufacturing method. |
| EP0649736A1 (en) * | 1993-10-22 | 1995-04-26 | Etablissements Manducher | Motor vehicle back shelf and method for its manufacture |
| WO1998004398A1 (en) * | 1996-07-30 | 1998-02-05 | Peguform France | Forming an insert in a panel made of a sandwich-type composite material with a cellular core |
| FR2751914A1 (en) * | 1996-07-30 | 1998-02-06 | Manducher Sa | FORMATION OF AN INSERT IN A PANEL IN COMPOSITE MATERIAL OF THE SANDWICH TYPE WITH A CORE CORE |
| EP0903216A3 (en) * | 1997-09-10 | 2000-02-09 | Peguform France | Method of manufacturing a sandwich panel which is locally stiffened, and panel produced thereby |
| FR2768076A1 (en) * | 1997-09-10 | 1999-03-12 | Peguform France | METHOD FOR PRODUCING A RIGIDIFIED ZONE INSERT FORMING IN A COMPOSITE SANDWICH PANEL, AND PANEL COMPRISING SUCH A ZONE |
| EP0903216A2 (en) * | 1997-09-10 | 1999-03-24 | Peguform France | Method of manufacturing a sandwich panel which is locally stiffened, and panel produced thereby |
| WO1999016660A1 (en) * | 1997-09-17 | 1999-04-08 | Ab Volvo | Load-carrying vehicle structure of composite material and method for its moulding |
| US6482508B1 (en) | 1997-09-17 | 2002-11-19 | Ab Volvo | Load-carrying vehicle structure of composite material and method for its moulding |
| WO2005010293A1 (en) * | 2003-07-28 | 2005-02-03 | Xiamen New Technology Integrat | A paper honeycomb core composite panel |
| WO2006102090A1 (en) * | 2005-03-23 | 2006-09-28 | The Boeing Company | Integrated aircraft structural floor |
| US7182291B2 (en) | 2005-03-23 | 2007-02-27 | The Boeing Company | Integrated aircraft structural floor |
| CN101146710B (en) * | 2005-03-23 | 2011-08-10 | 波音公司 | Integrated aircraft structural floor |
| JP2008534353A (en) * | 2005-03-23 | 2008-08-28 | ザ・ボーイング・カンパニー | Integrated aircraft structural flooring |
| AT503213B1 (en) * | 2006-01-27 | 2007-10-15 | Fischer Gmbh | SKIKERN WITH HOLLY CONSTRUCTION |
| EP2818415A1 (en) * | 2013-06-27 | 2014-12-31 | Airbus Operations GmbH | Panel member for an airframe |
| EP3470339A1 (en) * | 2013-06-27 | 2019-04-17 | Airbus Operations GmbH | Panel member for an airframe |
| US10814957B2 (en) | 2013-06-27 | 2020-10-27 | Airbus Operations Gmbh | Panel member for an airframe |
| FR3032905A1 (en) * | 2015-02-24 | 2016-08-26 | Airbus Defence & Space Sas | COMPOSITE PANEL HAVING AN IMPROVED ASSEMBLY TERMINATION AND STRUCTURE COMPRISING SUCH A PANEL |
| FR3032908A1 (en) * | 2015-02-24 | 2016-08-26 | Airbus Defence & Space Sas | REINFORCED COMPOSITE PANEL |
| WO2016135092A1 (en) * | 2015-02-24 | 2016-09-01 | Airbus Defence And Space Sas | Composite panel provided with an improved assembly end piece and structure comprising such a panel |
| WO2016135103A1 (en) * | 2015-02-24 | 2016-09-01 | Airbus Defence And Space Sas | Reinforced composite panel |
| EP3144125A1 (en) * | 2015-09-17 | 2017-03-22 | The Boeing Company | Panel and associated closeout method |
| US10155355B2 (en) | 2015-09-17 | 2018-12-18 | The Boeing Company | Panel and associated closeout method |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2686043B1 (en) | 1995-04-21 |
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