EP0072333A1 - Process for producing full and rigid panels - Google Patents

Process for producing full and rigid panels Download PDF

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Publication number
EP0072333A1
EP0072333A1 EP82401513A EP82401513A EP0072333A1 EP 0072333 A1 EP0072333 A1 EP 0072333A1 EP 82401513 A EP82401513 A EP 82401513A EP 82401513 A EP82401513 A EP 82401513A EP 0072333 A1 EP0072333 A1 EP 0072333A1
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EP
European Patent Office
Prior art keywords
wings
elements
filling
wing
section
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Granted
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EP82401513A
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German (de)
French (fr)
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EP0072333B1 (en
Inventor
Benoît Labbé
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Fernand Labbe SA
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Fernand Labbe SA
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Priority to AT82401513T priority Critical patent/ATE23595T1/en
Publication of EP0072333A1 publication Critical patent/EP0072333A1/en
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Publication of EP0072333B1 publication Critical patent/EP0072333B1/en
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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
    • E04C2/30—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
    • E04C2/40—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 a number of smaller components rigidly or movably connected together, e.g. interlocking, hingedly connected of particular shape, e.g. not rectangular of variable shape or size, e.g. flexible or telescopic panels

Definitions

  • the invention relates to a panel, in particular a drop side and its production method.
  • Solid panels which can be used in particular as drop sides, constituted by a plurality of juxtaposed coplanar filling elements, self-supporting and directly fixed to the frame which supports them. Such panels do not require a frame or intermediate uprights.
  • Each filling element has, in horizontal cross section, a flattened U shape having a solid and smooth core on the outside and two wings facing the internal face of the drop side. Two adjacent fillers. are rigidly joined together, at the location of their wings, by means of perforations made in the wings with which the rivets cooperate.
  • This seal is in the form of a strip having substantially the shape and dimensions of the wings and in particular of elastomer.
  • This seal may include perforations corresponding to the perforations of the wings and allowing the introduction of the fastening members of the filling elements.
  • the wings may include wing returns.
  • the filling elements have a flattened U shape.
  • the connecting rivets of the elements are not visible and do not protrude
  • the filling elements have a flat core, which means that the surface of the mounted drop side, directed towards the outside, is flat and allows the possible external decoration of the drop side and cleaning is facilitated.
  • the filling elements are made from flat metal plates, and the edges of the wings or wing returns are sharp.
  • the workers must protect their hands.
  • the outer surface of the drop side is planar, the inner surface includes sharp edges formed by the edges of the wings or wing returns. Consequently, it is not possible to envisage using the sideboards thus manufactured for trucks transporting fragile objects, for example furniture, which are then inevitably scratched by the sharp edges of the wings.
  • the aesthetic appearance of the interior of the drop side is not satisfactory.
  • the seal arranged between the wings of two filling elements is visible from the outside. Again the general appearance of the drop leaves to be desired because the color of the joint inevitably contrasts with the color of the panel.
  • the object of the invention is therefore to remedy these drawbacks.
  • it proposes a method of producing a solid rigid panel, by juxtaposition and fixing of a plurality of coplanar filling elements, having in cross-section a general shape of a flattened U, each comprising a flat core and two wings turned towards the internal face, possibly two returns of wings turned towards the lower surface of the core of the filling element, the webs of two adjacent filling elements being coplanar and their wings turned on the same side, method according to which has between two adjoining wings a sealing material that Ion compresses between the two wings so that it comes to fill at least partially one or more housings made in at least one of the wings, and located on either side of the longitudinal axis of the wings, or preferably of the longitudinal center line.
  • the sealing material expands in a direction perpendicular to this line. However, it does not diffuse to the outside of the panel thus produced. The formed joint is therefore invisible from the outside.
  • the invention also relates to the means for implementing such a method.
  • These are flattened U-shaped filling elements, the wings of which comprise a series of perforations arranged longitudinally and each comprising at least one half-cylinder housing, with an axis parallel to the longitudinal axis of the wings.
  • Reinforcement elements crimp the adjoining wings of two adjacent filling elements. Their function is multiple, in addition to the reinforcement, they make it possible to hide the wings and serve as support for connecting elements, of appreciably T-shape, in straight cross section, which come to fit in grooves of the elements enhancement.
  • a flat internal panel surface is obtained, the different faces facing inwards of the filling, reinforcing and connecting elements being coplanar.
  • a filling element 1, according to the invention, is rigid and self-supporting. It can be made of metal and coated with a colored lacquer. It enables a solid curtain panel to be produced by juxtaposition and joining together with similar filling elements.
  • each filling element comprises a flat core, of substantially rectangular shape (see FIG. 5), the external face of which is smooth and, two wings 3 facing the two-faced face of the core 2, more particularly perpendicular to the core 2.
  • the filling element is provided with wing returns 4 facing towards the underside of the filling element, parallel to the core 2.
  • the filling element has a general shape of a flattened U, in cross section.
  • Perforations 5 are arranged on a longitudinal axis of each of the wings, namely an axis perpendicular to the cutting plane of the filling element 1, preferably on the center line of each wing 3.
  • the perforations of the same wing are equidistant from each other and the perforations of one wing are located opposite the perforations of the other wing.
  • At least one wing 3 has a longitudinal housing 6. This is continuous, that is to say that it extends over the entire length of the wing 3.
  • At least one wing 3 comprises at least two longitudinal housings 6, 6 ′ situated on either side of the line of perforations, therefore of a longitudinal axis of the wing.
  • longitudinal axis is meant an axis parallel to the longitudinal sides of the wing. This being from preferably rectangular, the longitudinal median is the median of the rectangle delimiting the wing.
  • These housings 6, 6 ' have a substantially semicircular shape, in cross section.
  • These two housings can be provided on only one of the wings or also two housings on each of the wings. They can be produced by profiling the metal sheet used to manufacture the filling element 1.
  • the wing returns 4 are each provided at their free ends with a boss 7. This is produced for example by folding the free end of the wing return towards the wing, and in a direction directed towards the internal face 8 of the core 2.
  • the rigid panel is produced as follows (see Figures 3 and 4); several filling elements 1a, 1b, and 1c are placed side by side, the cores 2a, 2b, 2c being coplanar and the wings 3a, 3b and 3c being all situated on the same side relative to the plane defined by the cores.
  • the perforations are placed facing each other, as well as the housings. These form either semi-cylindrical grooves when only one wing has housings and that it is placed next to a wing without any housing, or cylindrical grooves with axes parallel to each other and parallel to the longitudinal axis of the wings, of circular cross section when each wing has housings 6 and 6 '.
  • the sealing material 9 is preferably a deformable material, for example an elastomer or a pasty material, namely a silicone. It may possibly be pierced with holes corresponding to the perforations 5. It is placed along the longitudinal axis of the wings, more particularly of the midline. When compressing this material in the direction of the arrows F1, F2, it deforms and diffuses towards the ends of the wings, in a direction substantially perpendicular to the longitudinal axis of the wings. It then fills the housings 6.
  • a deformable material for example an elastomer or a pasty material, namely a silicone. It may possibly be pierced with holes corresponding to the perforations 5. It is placed along the longitudinal axis of the wings, more particularly of the midline. When compressing this material in the direction of the arrows F1, F2, it deforms and diffuses towards the ends of the wings, in a direction substantially perpendicular to the longitudinal axis of the wings. It then fills the housing
  • the material 9 is placed in a large quantity, it completely fills the housings 6 and if it is placed in small quantity, it partially fills these housings. In any case, it does not reach the internal faces (8a, 8b, 8c) of the filling elements. When we look at the panel thus produced, from the outside, that is to say in the direction of arrow F3, we do not see the joint formed by the sealing material 9.
  • the width of the wings of the flattened U forming the cross section of the filling element 1 is very small compared to the width L of the core 2.
  • the width L is increased when it is desired to increase the length of the drop side or panel made. This avoids making many attachments. Therefore, it is necessary to strengthen the fasteners between two adjacent elements 1.
  • a reinforcing element 11 is placed which crimps the contiguous wing returns 4a, 4b of two adjacent filling elements 1a, 1b.
  • Each reinforcing element 11 is placed by sliding in a direction parallel to the longitudinal axis of the wings.
  • the connecting element 19 has a T-shaped cross section.
  • the tabs 20 and 20 ′ of the T come to cooperate with the grooves 15a and 15b of the two reinforcing elements 11a, llb arranged on the two pairs of contiguous wings 4a , 4b and 4'b 4 c of the filling elements 1a, 1b, 1c placed side by side.
  • all the reinforcing elements are parallel, their branches 14 are all turned towards the cores 2a, 2b, 2c and their bottoms 12a, 12b are all in the same plane parallel to the plane of the cores 2a, 2b, 2c.
  • the filling elements 19 sliding in the grooves 15a, 15b of two successive reinforcing elements are arranged so that the surface of the bar of the T comes flush with the surfaces of the bottoms 12a, 12b.
  • the surfaces of the bottoms 12a, 12b, of the reinforcing elements and the surfaces 21 of the filling elements are coplanar.
  • the panel made full and rigid therefore has a continuous external face and an internal face which is also continuous.

Abstract

1. A method of constructing a rigid solid panel by juxtaposing and securing a number of coplanar filling elements (1a, 1b, 1c) having a cross-section in the form of a flattened U and each having a flat web (2), two flanges turned towards the inner face of the web, and two flange bends (4) facing the inner surface of the filling element, a recess (6) being formed on at least one of the outer surfaces of the flanges of the element, the method being characterised in that a deformable sealing material (9) is disposed between two adjacent flanges (3a, 3b) of two adjacent filling elements (1a, 1b) which material is compressed between the two flanges (3a, 3b) of the adjacent filling elements by bringing the flanges together so that the material at least partly fills the recess (6) without spreading to the outer surface of the panel.

Description

L'invention concerne un panneau, notamment une ridelle et son procédé de réalisation.The invention relates to a panel, in particular a drop side and its production method.

On connaît des panneaux pleins utilisables notamment comme ridelles, constitués par une pluralité d'éléments de remplissage coplanaires juxtaposés, auto-portants et directement fixés au châssis qui les supporte. De tels panneaux ne nécessitent pas de charpente ou de montants intermédiaires. Chaque élément de remplissage a, en section droite transversale horizontale, une forme de U aplati ayant une âme pleine et lisse extérieurement et deux ailes tournées vers la face interne de la ridelle. Deux éléments de remplissage adjacents. sont rigidement solidarisés entre eux, à l'endroit de leurs ailes, au moyen de perforations réalisées dans les ailes avec lesquelles coopèrent des rivets.Solid panels are known which can be used in particular as drop sides, constituted by a plurality of juxtaposed coplanar filling elements, self-supporting and directly fixed to the frame which supports them. Such panels do not require a frame or intermediate uprights. Each filling element has, in horizontal cross section, a flattened U shape having a solid and smooth core on the outside and two wings facing the internal face of the drop side. Two adjacent fillers. are rigidly joined together, at the location of their wings, by means of perforations made in the wings with which the rivets cooperate.

Entre les ailes contiguës, on place un joint d'étanchéité. Ce joint se présente sous la forme d'une bande ayant sensiblement la forme et les dimensions des ailes et notamment en élastomère. Ce joint peut comporter des perforations correspondant aux perforations des ailes et permettant l'introduction des organes de solidarisation des éléments de remplissage. Par ailleurs, les ailes peuvent comporter des retours d'ailes. Ainsi les éléments de remplissage ont une forme d'U aplati.Between the adjoining wings, a seal is placed. This seal is in the form of a strip having substantially the shape and dimensions of the wings and in particular of elastomer. This seal may include perforations corresponding to the perforations of the wings and allowing the introduction of the fastening members of the filling elements. Furthermore, the wings may include wing returns. Thus the filling elements have a flattened U shape.

De tels panneaux présentent des avantages certains ; les rivets de liaison des éléments ne sont pas apparents et ne saillent pas, les éléments de remplissage ont une âme plane ce qui fait que la surface de la ridelle montée, dirigée vers l'extérieur, est plane et permet l'éventuelle décoration extérieure de la ridelle et le nettoyage en est facilité.Such panels have certain advantages; the connecting rivets of the elements are not visible and do not protrude, the filling elements have a flat core, which means that the surface of the mounted drop side, directed towards the outside, is flat and allows the possible external decoration of the drop side and cleaning is facilitated.

Cependant, ces panneaux comportent des inconvénients. En effet, les éléments de remplissage sont fabriqués à partir de plaques métalliques planes, et les bords des ailes ou des retours d'ailes sont coupants. Ainsi, lors du montage de la ridelle, les ouvriers doivent se protéger les mains. Par ailleurs, si la surface extérieure de la ridelle est plane, la surface intérieure comprend des arêtes vives formées par les bords des ailes ou des retours d'ailes. Par conséquent, on ne peut envisager d'utiliser les ridelles ainsi fabriquées pour des camions transportant des objets fragiles, par exemple des meubles, qui sont alors inévitablement rayés par les bords vifs des ailes. De plus, l'as- pectesthétique de l'intérieur de la ridelle n'est pas satisfaisant. En outre, le joint disposé entre les ailes de deux éléments de remplissage est visible de l'extérieur. Là encore l'aspect général de la ridelle laisse à désirer car la couleur du joint tranche inévitablement avec la couleur du panneau.However, these panels have drawbacks. Indeed, the filling elements are made from flat metal plates, and the edges of the wings or wing returns are sharp. Thus, when mounting the drop side, the workers must protect their hands. Furthermore, if the outer surface of the drop side is planar, the inner surface includes sharp edges formed by the edges of the wings or wing returns. Consequently, it is not possible to envisage using the sideboards thus manufactured for trucks transporting fragile objects, for example furniture, which are then inevitably scratched by the sharp edges of the wings. In addition, the aesthetic appearance of the interior of the drop side is not satisfactory. In addition, the seal arranged between the wings of two filling elements is visible from the outside. Again the general appearance of the drop leaves to be desired because the color of the joint inevitably contrasts with the color of the panel.

L'invention a donc pour objet de remédier à ces inconvénients. A cet effet, elle propose un procédé de réalisation d'un panneau rigide plein, par juxtaposition et fixation d'une pluralité d'éléments de remplissage coplanaires, ayant en section droite transversale une forme générale de U aplati, comportant chacun une âme plane et deux ailes tournées vers la face interne, éventuellement deux retours d'ailes tournés vers l'intrados de l'âme de lelêment de remplissage, les âmes de deux éléments de remplissage adjacents étant coplanaires et leurs ailes tournées d'un même côté, procédé selon lequel on dispose entre deux ailes contiguës un matériau d'étanchéité que Ion comprime entre les deux ailes pour qu'il vienne remplir au moins partiellement un ou plusieurs logements réalisés dansau moins une des ailes, et situés de part et d'autre de l'axe longitudinal des ailes, ou de préférence de la ligne médiane longitudinale.The object of the invention is therefore to remedy these drawbacks. To this end, it proposes a method of producing a solid rigid panel, by juxtaposition and fixing of a plurality of coplanar filling elements, having in cross-section a general shape of a flattened U, each comprising a flat core and two wings turned towards the internal face, possibly two returns of wings turned towards the lower surface of the core of the filling element, the webs of two adjacent filling elements being coplanar and their wings turned on the same side, method according to which has between two adjoining wings a sealing material that Ion compresses between the two wings so that it comes to fill at least partially one or more housings made in at least one of the wings, and located on either side of the longitudinal axis of the wings, or preferably of the longitudinal center line.

Le matériau d'étanchéité se dilate selon une direction perpendiculaire à cette ligne. Cependant, il ne diffuse pas jusqu'à l'extérieur du panneau ainsi réalisé. Le joint formé est donc invisible de l'extérieur.The sealing material expands in a direction perpendicular to this line. However, it does not diffuse to the outside of the panel thus produced. The formed joint is therefore invisible from the outside.

L'invention concerne aussi les moyens pour la mise en oeuvre d'un tel procédé. Ce sont des éléments de remplissage en forme d'U aplati, dont les ailes comportent une série de perforations disposées longitudinalement et comportant chacune au moins un logement demi-cylindre, d'axe parallèle à l'axe longitudinal des ailes. Des éléments de renforcement viennent sertir les ailes contiguës de deux éléments de remplissage adjacents. Leur fonction est multiple, outre le renforcement, ils permettent de masquer les ailes et servent de support à des éléments de liaison, de forme sensible-, ment en T, en section transversale droite, qui viennent s'emboîter dans des rainures des éléments de renforcement. On obtient une surface de panneau interne plane, les différentes faces dirigées vers l'intérieur des éléments de remplissage, de renforcement et de liaison étant coplanaires.The invention also relates to the means for implementing such a method. These are flattened U-shaped filling elements, the wings of which comprise a series of perforations arranged longitudinally and each comprising at least one half-cylinder housing, with an axis parallel to the longitudinal axis of the wings. Reinforcement elements crimp the adjoining wings of two adjacent filling elements. Their function is multiple, in addition to the reinforcement, they make it possible to hide the wings and serve as support for connecting elements, of appreciably T-shape, in straight cross section, which come to fit in grooves of the elements enhancement. A flat internal panel surface is obtained, the different faces facing inwards of the filling, reinforcing and connecting elements being coplanar.

Les autres caractéristiques de l'invention seront bien comprises grâce à la description qui suit, en référence aux dessins annexés dans lesquels :

  • La figure 1 est une vue schématique, en coupe, par un plan horizontal transversal d'un élément de remplissage selon l'invention ; la figure 2 est une vue schématique, en coupe par un plan horizontal, transversal d'un élément de renforcement ; la figure 3 est une vue schématique, en coupe par un plan horizontal, transversal d'un panneau réalisé au moyen des éléments de remplissage et de renforcement ; la figure 4 est une vue schématique analogue à la figure 3, des éléments de liaison étant emboités ; la figure 5 et la figure 6 -sont des vues de face respectivement externe et interne du panneau de la figure 4.
The other characteristics of the invention will be understood from the following description, with reference to the accompanying drawings in which:
  • Figure 1 is a schematic view, in section, through a horizontal transverse plane of a filling element according to the invention; Figure 2 is a schematic view, in section through a horizontal, transverse plane of a reinforcing element; FIG. 3 is a schematic view, in section through a horizontal, transverse plane of a panel produced by means of filling and reinforcing elements; Figure 4 is a schematic view similar to Figure 3, the connecting elements being fitted; FIG. 5 and FIG. 6 are respectively external and internal front views of the panel in FIG. 4.

Un élément de remplissage 1, selon l'invention, est rigide et auto-portant. Il peut être réalisé en métal et revêtu d'une laque de couleur. Il permet de réaliser un panneau ridige plein par juxtaposition et solidarisation avec des éléments de remplissage semblables. D'une façon connue en soi, chaque élément de remplissage comporte une âme plane, de forme sensiblement rectangulaire (voir figure 5), dont la face externe est lisse et, deux ailes 3 tournées vers la face bterne de l'âme 2, plus particulièrement perpendiculaires à l'àme 2. De préférence, l'élément de remplissage est muni de retours d'ailes 4 tournées vers l'intrados de l'élément de remplissage, parallèles à l'âme 2. Ainsi l'élément de remplissage a une forme générale d'U aplati, en section droite transversale. Des perforations 5 sont disposées sur un axe longitudinal de chacune des ailes, à savoir un axe perpendiculaire au plan de coupe de l'élément de remplissage 1, de préférence sur la ligne médiane de chaque aile 3. Les perforations d'une même aile sont équidistantes les unes des autres et les perforations d'une ailes sont situées en regard des perforations de l'autre aile.A filling element 1, according to the invention, is rigid and self-supporting. It can be made of metal and coated with a colored lacquer. It enables a solid curtain panel to be produced by juxtaposition and joining together with similar filling elements. In a manner known per se, each filling element comprises a flat core, of substantially rectangular shape (see FIG. 5), the external face of which is smooth and, two wings 3 facing the two-faced face of the core 2, more particularly perpendicular to the core 2. Preferably, the filling element is provided with wing returns 4 facing towards the underside of the filling element, parallel to the core 2. Thus the filling element has a general shape of a flattened U, in cross section. Perforations 5 are arranged on a longitudinal axis of each of the wings, namely an axis perpendicular to the cutting plane of the filling element 1, preferably on the center line of each wing 3. The perforations of the same wing are equidistant from each other and the perforations of one wing are located opposite the perforations of the other wing.

Selon l'invention au moins une aile 3 comporte un logement 6 longitudinal. Celui-ci est continu, c'est-à-dire qu'il s'étend sur toute la longueur de l'aile 3.According to the invention at least one wing 3 has a longitudinal housing 6. This is continuous, that is to say that it extends over the entire length of the wing 3.

De préférence, au moins une aile 3 comporte au moins deux logements 6, 6', longitudinaux situés de part et d'autre de la ligne de perforations donc d'un axe longitudinal de l'aile. Par axe longitudinal, on entend un axe parallèle aux côtés longitudinaux de l'aile. Celle-ci étant de préférence rectangualire, la médiane longitudinale est la médiane du rectangle délimitant l'aile. Ces logements 6, 6' ont une forme sensiblement demi-circulaire, en section droite transversale. On peut prévoir ces deux logements sur une seule des ailes ou aussi deux logements sur chacune des ailes. Ils peuvent être réalisés par profilage de la feuille métallique utilisée pour fabriquer l'élément de remplissage 1. Préférentiellement, les retours d'ailes 4 sont munis chacun à leurs extrémités libres d'un bosselage 7. Celui-ci est réalisé par exemple en repliant l'extrémité libre du retour d'aile vers l'aile, et dans une direction dirigée vers la face interne 8 de l'âme 2.Preferably, at least one wing 3 comprises at least two longitudinal housings 6, 6 ′ situated on either side of the line of perforations, therefore of a longitudinal axis of the wing. By longitudinal axis is meant an axis parallel to the longitudinal sides of the wing. This being from preferably rectangular, the longitudinal median is the median of the rectangle delimiting the wing. These housings 6, 6 'have a substantially semicircular shape, in cross section. These two housings can be provided on only one of the wings or also two housings on each of the wings. They can be produced by profiling the metal sheet used to manufacture the filling element 1. Preferably, the wing returns 4 are each provided at their free ends with a boss 7. This is produced for example by folding the free end of the wing return towards the wing, and in a direction directed towards the internal face 8 of the core 2.

Le panneau rigide est réalisé de la façon suivante (voir figures 3 et 4) ; on dispose côte à côte plusieurs éléments de remplissage la, 1b, et 1c, les âmes 2a, 2b, 2c étant coplanaires et les ailes 3a, 3b et 3c étant toutes situées du même côté par rapport au plan défini par les âmes. Les perforations sont placées en regard les unes des autres, ainsi que les logements. Ceux-ci forment soit des sillons demi-cylindriques quand seule une aile comporte des logements et qu'on la place à côté d'une aile ne possédant pas de logement, soit des sillons cylindriques d'axes parallèles entre eux et parallèles à l'axe longitudinal des ailes, de section droite transversale circulaire quand chaque aile possède des logements 6 et 6'.The rigid panel is produced as follows (see Figures 3 and 4); several filling elements 1a, 1b, and 1c are placed side by side, the cores 2a, 2b, 2c being coplanar and the wings 3a, 3b and 3c being all situated on the same side relative to the plane defined by the cores. The perforations are placed facing each other, as well as the housings. These form either semi-cylindrical grooves when only one wing has housings and that it is placed next to a wing without any housing, or cylindrical grooves with axes parallel to each other and parallel to the longitudinal axis of the wings, of circular cross section when each wing has housings 6 and 6 '.

On dispose entre deux ailes contiguës un matériau d'étanchéité 9 que l'on comprime entre les deux ailes, notamment en rapprochant celles-ci grâce aux organes de solidarisation 10, par exemple des rivets. Le matériau d'étanchéité 9 est de préférence une matière déformable, par exemple un élastomère ou une matière pâteuse, à savoir un silicone. Il peut être éventuellement percé de trous correspondant aux perforations 5. On le place le long de Taxe longitudinal des ailes, plus particulièrement de la ligne médiane. Lorsqu'on comprime ce matériau selon la direction des flèches F1, F2, il se déforme et diffuse vers les extrémités des ailes, selon une direction sensiblement perpendiculaire à l'axe longitudinal des ailes. Il vient alors remplir les logements 6. Si le matériau 9 est placé en quantité importante, il remplit totalement les logements 6 et si il est placé en faible quantité, il remplit partiellement ces logements. En tout cas, il ne parvient pas jusqu'aux faces internes (8a, 8b, 8c) des éléments de remplissage. Lorsqu'on regarde le panneau ainsi réalisé, depuis l'extérieur, c'est-à-dire en direction de la flèche F3, on n'aperçoit pas le joint formé par le matériau d'étanchéité 9.There is between two contiguous wings a sealing material 9 which is compressed between the two wings, in particular by bringing them together by means of the fastening members 10, for example rivets. The sealing material 9 is preferably a deformable material, for example an elastomer or a pasty material, namely a silicone. It may possibly be pierced with holes corresponding to the perforations 5. It is placed along the longitudinal axis of the wings, more particularly of the midline. When compressing this material in the direction of the arrows F1, F2, it deforms and diffuses towards the ends of the wings, in a direction substantially perpendicular to the longitudinal axis of the wings. It then fills the housings 6. If the material 9 is placed in a large quantity, it completely fills the housings 6 and if it is placed in small quantity, it partially fills these housings. In any case, it does not reach the internal faces (8a, 8b, 8c) of the filling elements. When we look at the panel thus produced, from the outside, that is to say in the direction of arrow F3, we do not see the joint formed by the sealing material 9.

On conçoit que la largeur des ailes du U aplati formant la section transversale droite de l'élément de remplissage 1 est très faible par rapport à la largeur L de l'àme 2. La largeur L est augmentée quand on désire augmenter la longueur de la ridelle ou du panneau réalisé. On évite ainsi d'effectuer de nombreuses fixations. Par conséquent, il est nécessaire de renforcer les fixations entre deux éléments 1 adjacents. A cet effet, on place un élément de renforcement 11 qui vient sertir les retours d'ailes contigus 4a, 4b de deux éléments de remplissage la, lb adjacents. Chaque élément de renforcement 11 est placé par coulissement selon une direction parallèle à l'axe longitudinal des ailes. Il a en section droite transversale une forme générale d'U aplati ayant un fond plat 12, des côtés 13 formant un angle avec le fond plat 12, de préférence perpendiculaires, et deux bords 14 parallèles au fond 12, tourné vers l'intrados de l'élément de renforcement. La largeur des côtés 13 est sensiblement égale à la largeur 1 des ailes de 1 élément 3 de remplissage, la largeur D du fond 12 étant sensiblement supérieure au double de la largeur d des ailes de l'élément de remplissage 1, de façon à pouvoir sertir ces ailes. Dans ce cas, il n'est pas obligatoire de prévoir des bosselages 7, car les éléments de renforcement jouent un rôle protecteur puisqu'ils masquent les bords tranchants des retours d'ailes. Par ailleurs, l'élément de renforcement 11 comporte sur chaque côté 13 des rainures 15. Celles-ci sont longitudinales, s'étendent selon une direction parallèle à l'axe longitudinal des côtés 13 et leur section droite transversale a la forme d'un U dont les branches 16 et 17 sont parallèles aux bords 14. Le fond 18 de rainure est parallèle aux côtés 13. Cette structure permet d'emboîter à force un élément de liaison 19 selon une direction parallèle à l'axe longitudinal des ailes 3. L'élément de liaison 19 a une section droite transversale en forme de T. Les pattes 20 et 20' du T viennent coopérer avec les rainures 15a et 15b des deux éléments de renforcement 11a, llb disposés sur les deux paires d'ailes contiguës 4a, 4b et 4'b 4 c des éléments de remplissage la, 1b, 1c placés côte à côte. Ainsi, tous les éléments de renforcement sont parallèles, leurs branches 14 sont toutes tournées vers les âmes 2a, 2b, 2c et leurs fonds 12a, 12b sont tous dans un même plan parallèle au plan des âmes 2a, 2b, 2c.It is understood that the width of the wings of the flattened U forming the cross section of the filling element 1 is very small compared to the width L of the core 2. The width L is increased when it is desired to increase the length of the drop side or panel made. This avoids making many attachments. Therefore, it is necessary to strengthen the fasteners between two adjacent elements 1. To this end, a reinforcing element 11 is placed which crimps the contiguous wing returns 4a, 4b of two adjacent filling elements 1a, 1b. Each reinforcing element 11 is placed by sliding in a direction parallel to the longitudinal axis of the wings. It has in cross section a general shape of a flattened U having a flat bottom 12, sides 13 forming an angle with the flat bottom 12, preferably perpendicular, and two edges 14 parallel to the bottom 12, facing towards the lower surface of the reinforcing element. The width of the sides 13 is substantially equal to the width 1 of the wings of 1 filling element 3, the width D of the bottom 12 being substantially greater than twice the width d of the wings of the filling element 1, so as to be able crimp these wings. In this case, it is not compulsory to provide bosses 7, because the reinforcing elements play a protective role since they mask the sharp edges of the wing returns. Furthermore, the reinforcing element 11 has on each side 13 grooves 15. These are longitudinal, extend in a direction parallel to the longitudinal axis of the sides 13 and their cross section is in the form of a U whose branches 16 and 17 are parallel to the edges 14. The bottom 18 of groove is parallel to the sides 13. This structure makes it possible to force-fit a connecting element 19 in a direction parallel to the longitudinal axis of the wings 3. The connecting element 19 has a T-shaped cross section. The tabs 20 and 20 ′ of the T come to cooperate with the grooves 15a and 15b of the two reinforcing elements 11a, llb arranged on the two pairs of contiguous wings 4a , 4b and 4'b 4 c of the filling elements 1a, 1b, 1c placed side by side. Thus, all the reinforcing elements are parallel, their branches 14 are all turned towards the cores 2a, 2b, 2c and their bottoms 12a, 12b are all in the same plane parallel to the plane of the cores 2a, 2b, 2c.

Les éléments de remplissage 19 venant coulisser dans les rainures 15a, 15b de deux éléments de renforcement successifs sont disposés de façon que la surface de la barre du T vienne affleurer les surfaces des fonds 12a, 12b. Ainsi, les surfaces des fonds 12a, 12b, des éléments de renforcement et les surfaces 21 des éléments de remplissage sont coplanaires. Lorsqu'on regarde le panneau ainsi réalisé, depuis l'intérieur, c'est-à-dire en direction de la flèche F4, on ne voit que les surfaces desfonds 12a, 12b, 12c, et les autres surfaces 21, 21', 21" des éléments de remplissage, les surfaces de fond 12a, 12b alternant avec les surfaces 21 21', 21" des éléments de remplissage (cf. figure 6) et étant coplanaires.The filling elements 19 sliding in the grooves 15a, 15b of two successive reinforcing elements are arranged so that the surface of the bar of the T comes flush with the surfaces of the bottoms 12a, 12b. Thus, the surfaces of the bottoms 12a, 12b, of the reinforcing elements and the surfaces 21 of the filling elements are coplanar. When we look at the panel thus produced, from the inside, that is to say in the direction of arrow F4, we only see the bottom surfaces 12a, 12b, 12c, and the other surfaces 21, 21 ', 21 "of the filling elements, the bottom surfaces 12a, 12b alternating with the surfaces 21 21 ', 21" of the filling elements (cf. FIG. 6) and being coplanar.

Le panneau réalisé plein et rigide a donc une face externe continue et une face interne elle aussi continue.The panel made full and rigid therefore has a continuous external face and an internal face which is also continuous.

Naturellement, il va de soi que l'invention peut faire l'objet de nombreuses autres variantes, formes et applications.Naturally, it goes without saying that the invention can be the subject of numerous other variants, forms and applications.

Claims (20)

1. Procédé de réalisation-d'un panneau rigide plein, par juxtaposition et fixation d'une pluralité d'éléments de remplissage coplanaires, ayant en section droite transversale une forme d'U aplati comportant chacun une âme plane, deux ailes tournées vers la face interne de l'âme et éventuellement deux retours d'ailes tournés vers l'intrados de l'élément de remplissage, ledit procédé étant caractérisé en ce que l'on dispose, entre deux ailes contiguës (3a, 3b) de deux éléments de remplissage adjacents (la, lb) un matériau d'étanchéité (9) que l'on comprime entre les deux ailes (3a, 3b) pour qu'il vienne remplir au moins partiellement un logement (6) réalisé dans au moins une des ailes.1. A method of making a solid rigid panel, by juxtaposition and fixing of a plurality of coplanar filling elements, having in cross-section a flattened U shape each comprising a flat core, two wings facing the inner face of the core and possibly two wing returns facing towards the lower surface of the filling element, said method being characterized in that there are, between two contiguous wings (3a, 3b), two elements of adjacent filling (la, lb) a sealing material (9) which is compressed between the two wings (3a, 3b) so that it comes to fill at least partially a housing (6) made in at least one of the wings . 2. Procédé selon la revendication 1, caractérisé en ce que l'on dispose le matériau (9) sur un axe longitudinal des ailes et qu'on le comprime pour qu'il diffuse vers l'extérieur des ailes selon une direction perpendiculaire à l'axe longitudinal des ailes.2. Method according to claim 1, characterized in that the material (9) is placed on a longitudinal axis of the wings and that it is compressed so that it diffuses towards the outside of the wings in a direction perpendicular to the longitudinal axis of the wings. 3. Procédé selon la revendication 2, caractérisé en ce que l'on dispose le matériau (9) sur la médiane longitudinale des ailes et qu'il diffuse selon une direction perpendiculaire à cette médiane.3. Method according to claim 2, characterized in that the material (9) is placed on the longitudinal median of the wings and that it diffuses in a direction perpendicular to this median. 4. Procédé selon l'une quelconque des revendications 1 à 3 caractérisé en ce que les logements (6) sont de forme sensiblement demi-circulaire, en section droite transversale.4. Method according to any one of claims 1 to 3 characterized in that the housings (6) are of substantially semi-circular shape, in cross section. 5. Procédé selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le matériau (9) comporte des perforations situées en regard des perforations correspondantes prévues dans les ailes pour la fixation des éléments de remplissage.5. Method according to any one of claims 1 to 4, characterized in that the material (9) comprises perforations located opposite the corresponding perforations provided in the wings for fixing the filling elements. 6. Procédé selon l'une quelconque des revendications 1 à 5 caractérisé en ce que le matériau d'étanchéité (9) est une bande d'élastomère.6. Method according to any one of claims 1 to 5 characterized in that the sealing material (9) is an elastomer strip. 7. Procédé selon l'une quelconque des revendications 1 à 4 caractérisé en ce que le matériau d'étanchéité (9) est sous forme pâteuse, de préférence une composition de silicone.7. Method according to any one of claims 1 to 4 characterized in that the sealing material (9) is in pasty form, preferably a silicone composition. 8.Procédé selon l'une quelconque des revendications 1 à 7 caractérisé en ce que l'on place un élément de renforcement (11) venant sertir les retours d'ailes (4a, 4b) contigus de deux éléments de remplissage (la, 1b) adjacents.8. Process according to any one of Claims 1 to 7, characterized in that a reinforcing element (11) is placed which crimps the wing returns (4a, 4b) contiguous with two filling elements (la, 1b ) adjacent. 9. Procédé selon la revendication 8, cararactérisé en ce que l'élément de renforcement (11) est placé par coulissement selon une direction parallèle à l'axe longitudinal des ailes.9. Method according to claim 8, characterized in that the reinforcing element (11) is placed by sliding in a direction parallel to the longitudinal axis of the wings. 10. Procédé selon l'une quelconque des revendications 8 et 9, caractérisé en ce que l'on place des éléments de liaison (19) entre les deux éléments de renforcement (lla, llb) successifs.10. Method according to any one of claims 8 and 9, characterized in that one places connecting elements (19) between the two reinforcing elements (lla, llb) successive. 11. Procédé selon la revendication 10, caractérisé en ce que l'élément de liaison (19) est emboité à force par coulissement selon une direction parallèle à l'axe longitudinal des ailes.11. Method according to claim 10, characterized in that the connecting element (19) is force fitted by sliding in a direction parallel to the longitudinal axis of the wings. 12. Procédé selon l'une quelconque des revendications 10 et 11, caractérisé en ce que l'élément de lhison est emboîté dans des rainures (15) réalisées dans les éléments de renforcement.12. Method according to any one of claims 10 and 11, characterized in that the lhison element is fitted into grooves (15) made in the reinforcing elements. 13. Elément de remplissage pour la mise en oeuvre du procédé selon l'une quelconque des revendications 1 à 12, caractérisé en ce qu'en section droite transversale il a sensiblement la forme d'un U aplati dont au moins une des ailes comporte au moins un logement (6)continu .13. Filling element for implementing the method according to any one of claims 1 to 12, characterized in that in cross section it has sen the shape of a flattened U, at least one of the wings of which comprises at least one continuous housing (6). 14. Elément de remplissage selon la revendication 13, caractérisé en ce qu'au moins une des ailes comporte deux logements (6, 6') demi-circulaires continus situés de part et d'autre de l'axe longitudinal de l'aile, de préférence la médiane longitudinale.14. Filling element according to claim 13, characterized in that at least one of the wings comprises two continuous semicircular housings (6, 6 ') situated on either side of the longitudinal axis of the wing, preferably the longitudinal median. 15. Elément de remplissage selon l'une quelconque des revendications 13 et 14 caractérisé en ce que les ailes comportent chacune un retour d'aile tourné vers l'intrados de l'élément de remplissage.15. Filling element according to any one of claims 13 and 14 characterized in that the wings each comprise a wing return facing the underside of the filling element. 16. Elément de remplissage selon la revendication 15, caractérisé en ce que les retours d'ailes (4) sont munis à leur extrémité libre d'un bosselage (7).16. Filling element according to claim 15, characterized in that the wing returns (4) are provided at their free end with a boss (7). 17. Elément de renforcement pour la mise en oeuvre du procédé selon l'une quelconque des revendications 8 à 12, caractérisé en ce qu'il a en section droite transversale une forme générale de U aplati ayant un fond plat (12) et deux côtés (13), chaque côté étant muni d'un bord sensiblement parallèle au fond de l'élément de renforcement et tourné vers son intrados.17. Reinforcement element for implementing the method according to any one of claims 8 to 12, characterized in that it has in cross-section a general shape of a flattened U having a flat bottom (12) and two sides (13), each side being provided with an edge substantially parallel to the bottom of the reinforcing element and turned towards its lower surface. 18. Elément de renforcement selon la revendication 17, caractérisé en ce que chaque côté (13) comporte une rainure (15) s'étendant selon une direction parallèle à l'axe des côtés (13) .18. Reinforcement element according to claim 17, characterized in that each side (13) has a groove (15) extending in a direction parallel to the axis of the sides (13). 19{ Elément de liaison pour la mise en oeuvre du procédé selon l'une quelconque des revendications 10 à 12, caractérisé en ce qu'il a en section droite transversale la forme sensiblement d'un T.19 {connecting element for implementing the method according to any one of claims 10 to 12, characterized in that it has, in cross-section, the shape substantially of a T. 20. Panneau rigide plein réalisé par le procédé selon l'une quelconque des revendications 1 à 12, caractérisé en ce qu'il est constituée d'éléments de remplissage (1) dont les retours d'ailes (4) sont sertis par des éléments de renforcement (11) coopérant avec des éléments de liaison (19), les surfaces (21) des éléments de liaison (19) alternant avec les surfaces des fonds (12) des éléments de renforcement et étant coplanaires.20. Solid rigid panel produced by the method according to any one of claims 1 to 12, characterized in that it consists of filling elements (1) whose wing returns (4) are crimped by elements reinforcement (11) cooperating with connection elements (19), the surfaces (21) of the connection elements (19) alternating with the surfaces of the bases (12) of the reinforcement elements and being coplanar.
EP82401513A 1981-08-11 1982-08-10 Process for producing full and rigid panels Expired EP0072333B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82401513T ATE23595T1 (en) 1981-08-11 1982-08-10 PROCESS FOR MANUFACTURING FULL AND RIGID WALL ELEMENTS.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8115509A FR2511464A1 (en) 1981-08-11 1981-08-11 METHOD FOR MAKING A RIGID FULL PANEL
FR8115509 1981-08-11

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EP0072333A1 true EP0072333A1 (en) 1983-02-16
EP0072333B1 EP0072333B1 (en) 1986-11-12

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EP82401513A Expired EP0072333B1 (en) 1981-08-11 1982-08-10 Process for producing full and rigid panels

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EP (1) EP0072333B1 (en)
AT (1) ATE23595T1 (en)
DE (1) DE3274274D1 (en)
ES (1) ES273660Y (en)
FR (1) FR2511464A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0414654A1 (en) * 1989-08-23 1991-02-27 Jacques Wybauw Interior panel for a vertilated light façade
GB2283032A (en) * 1993-10-19 1995-04-26 Armfibre Ltd Decking system
GB2451193A (en) * 2007-07-20 2009-01-21 Wernick Buildings Ltd Modular Custodial Accommodation

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US3055460A (en) * 1958-09-11 1962-09-25 Southwestern Porcelain Steel C Building construction
DE2246804A1 (en) * 1972-09-22 1974-03-28 Rakennusvalmiste Oy PROCESS FOR PRODUCING A LIGHTWEIGHT ROOM ELEMENT
FR2343914A1 (en) * 1976-03-08 1977-10-07 Chereau Jean ASSEMBLY OF PREFABRICATED PANELS INTENDED IN PARTICULAR FOR REFRIGERATED VEHICLES
GB1540727A (en) * 1975-12-23 1979-02-14 Europ Profiles Ltd Sheet metal panel elements for double-skin walls for buildings
FR2417717A1 (en) * 1978-02-21 1979-09-14 Labbe Fernand Sa Side panel for lorry - has U=shaped cross section plates attached directly to chassis and including fastener apertures in each flange
FR2437568A1 (en) * 1978-09-29 1980-04-25 Francon & Cie Sa THIN MATERIAL PANEL OR PARTITION
DE2848774A1 (en) * 1978-11-10 1980-05-22 Ackermann Fruehauf Vehicle body wall section - has mating halves of clip type coupling along opposite edges
FR2444226A1 (en) * 1978-12-14 1980-07-11 Ackermann Fruehauf PARTITION PANEL FOR MOTOR VEHICLE SUPERSTRUCTURE
US4216635A (en) * 1976-03-29 1980-08-12 Pepsico, Inc. Hollow panel structure and method for the construction thereof
FR2454399A2 (en) * 1978-09-14 1980-11-14 Sovam BODY FOR VEHICLE, AS WELL AS VEHICLES PROVIDED WITH THIS BODY

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3055460A (en) * 1958-09-11 1962-09-25 Southwestern Porcelain Steel C Building construction
DE2246804A1 (en) * 1972-09-22 1974-03-28 Rakennusvalmiste Oy PROCESS FOR PRODUCING A LIGHTWEIGHT ROOM ELEMENT
GB1540727A (en) * 1975-12-23 1979-02-14 Europ Profiles Ltd Sheet metal panel elements for double-skin walls for buildings
FR2343914A1 (en) * 1976-03-08 1977-10-07 Chereau Jean ASSEMBLY OF PREFABRICATED PANELS INTENDED IN PARTICULAR FOR REFRIGERATED VEHICLES
US4216635A (en) * 1976-03-29 1980-08-12 Pepsico, Inc. Hollow panel structure and method for the construction thereof
FR2417717A1 (en) * 1978-02-21 1979-09-14 Labbe Fernand Sa Side panel for lorry - has U=shaped cross section plates attached directly to chassis and including fastener apertures in each flange
FR2454399A2 (en) * 1978-09-14 1980-11-14 Sovam BODY FOR VEHICLE, AS WELL AS VEHICLES PROVIDED WITH THIS BODY
FR2437568A1 (en) * 1978-09-29 1980-04-25 Francon & Cie Sa THIN MATERIAL PANEL OR PARTITION
DE2848774A1 (en) * 1978-11-10 1980-05-22 Ackermann Fruehauf Vehicle body wall section - has mating halves of clip type coupling along opposite edges
FR2444226A1 (en) * 1978-12-14 1980-07-11 Ackermann Fruehauf PARTITION PANEL FOR MOTOR VEHICLE SUPERSTRUCTURE

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0414654A1 (en) * 1989-08-23 1991-02-27 Jacques Wybauw Interior panel for a vertilated light façade
GB2283032A (en) * 1993-10-19 1995-04-26 Armfibre Ltd Decking system
GB2283032B (en) * 1993-10-19 1997-04-23 Armfibre Ltd Decking system
GB2451193A (en) * 2007-07-20 2009-01-21 Wernick Buildings Ltd Modular Custodial Accommodation
GB2451193B (en) * 2007-07-20 2009-07-22 Wernick Buildings Ltd Modular custodial accommodation

Also Published As

Publication number Publication date
ATE23595T1 (en) 1986-11-15
ES273660Y (en) 1984-11-16
ES273660U (en) 1984-04-01
EP0072333B1 (en) 1986-11-12
DE3274274D1 (en) 1987-01-02
FR2511464A1 (en) 1983-02-18
FR2511464B1 (en) 1984-01-06

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