DE19726799A1 - Connecting arrangement for fibre compound sandwich structure - Google Patents

Connecting arrangement for fibre compound sandwich structure

Info

Publication number
DE19726799A1
DE19726799A1 DE19726799A DE19726799A DE19726799A1 DE 19726799 A1 DE19726799 A1 DE 19726799A1 DE 19726799 A DE19726799 A DE 19726799A DE 19726799 A DE19726799 A DE 19726799A DE 19726799 A1 DE19726799 A1 DE 19726799A1
Authority
DE
Germany
Prior art keywords
joining
connection arrangement
parts
arrangement according
connecting 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.)
Granted
Application number
DE19726799A
Other languages
German (de)
Other versions
DE19726799C2 (en
Inventor
Axel Dr Herrmann
Arno Pabsch
Wilm Felix Dr Unckenbold
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Priority to DE19726799A priority Critical patent/DE19726799C2/en
Priority to IT1998MI001445A priority patent/IT1301795B1/en
Priority to FR9808001A priority patent/FR2764840B1/en
Publication of DE19726799A1 publication Critical patent/DE19726799A1/en
Application granted granted Critical
Publication of DE19726799C2 publication Critical patent/DE19726799C2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/4835—Heat curing adhesives
    • 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
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5014—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being fibre-reinforced
    • 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
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5021—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being multi-layered
    • 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
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between the surfaces to be joined
    • 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
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5064—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5071—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped and being composed by one single element
    • 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
    • B29C66/40—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
    • B29C66/40—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
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4342—Joining substantially flat articles for forming corner connections, e.g. for making V-shaped pieces
    • B29C66/43421—Joining substantially flat articles for forming corner connections, e.g. for making V-shaped pieces with a right angle, e.g. for making L-shaped pieces
    • 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
    • B29C66/49—Internally supporting the, e.g. tubular, article during joining
    • B29C66/494—Internally supporting the, e.g. tubular, article during joining using an inflatable core
    • 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
    • B29C66/49—Internally supporting the, e.g. tubular, article during joining
    • B29C66/496—Internally supporting the, e.g. tubular, article during joining using a support which remains in the joined object
    • 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
    • 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
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • 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
    • B29C66/7252—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 hollow-walled
    • 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
    • B29C66/727—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 porous, e.g. foam
    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • 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
    • E04C2/3405—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 profiled spacer sheets
    • 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
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2007/00—Flat articles, e.g. films or sheets
    • B29L2007/002—Panels; Plates; Sheets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2024/00—Articles with hollow walls
    • 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
    • E04C2/3405—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 profiled spacer sheets
    • E04C2002/3444—Corrugated sheets
    • E04C2002/345—Corrugated sheets with triangular corrugations

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Architecture (AREA)
  • Chemical & Material Sciences (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Laminated Bodies (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Joining Of Building Structures In Genera (AREA)

Abstract

Connecting components are provided, which are so formed, that they can be fitted between the seam lips (11) of abutting seam parts (10) and a forced locking connection of the seam parts is formed. An upper seam lip (11) is located in the plane of the outer surface of the seam part and a lower seam lip (12) is so arranged at an angle to the inner surface or lower side (14) of the seam part that a self-centering of the seam surfaces (16) of abutting seam parts is achieved. The connecting components are separately produced and are introduced, particularly adhered, in the seam surfaces for production of a forced locking connection. The connecting components have a thin, fibre-reinforced outer skin and a foam core.

Description

Die Erfindung betrifft eine Verbindungsanordnung für Faserverbund-Sandwich­ strukturen in Modulbauweise, wobei Fügeteile der Strukturen vorgesehen sind.The invention relates to a connection arrangement for fiber composite sandwich Structures in modular construction, whereby parts of the structures to be joined are provided.

In der heutigen Zeit kommt der Anwendung von großflächigen Faserverbund­ strukturen im Bereich des Flugzeug-, Schiff- und des Schienenfahrzeugbaus eine immer größere Bedeutung zu. Aufgrund der hohen Tragfähigkeit in Verbin­ dung mit einem geringen Strukturgewicht bieten sich dabei oftmals Sandwich­ strukturen an, deren großflächige Herstellung jedoch häufig an fertigungstech­ nischen Problemen scheitert. Als ideale Lösung wird daher ein modulartiger Aufbau der Gesamtstruktur aus einzelnen vorgefertigten Halbzeugen angese­ hen. Die einzelnen vorgefertigten Halbzeuge müssen dann durch geeignete Verbindungstechnik zu den großflächigen Faserverbundstrukturen zusammen­ gefügt werden.Nowadays large fiber composites are used structures in the field of aircraft, ship and rail vehicle construction becoming more and more important. Due to the high load capacity in Verbin With a low structural weight, sandwiches are often offered structures, but their large-scale production often involves manufacturing technology African problems fail. The ideal solution is therefore a modular one Structure of the overall structure from individual prefabricated semi-finished products hen. The individual prefabricated semi-finished products must then be replaced by suitable ones Connection technology to the large-area fiber composite structures together be added.

Es ist bekannt, die einzelnen Fügeteile als vorgefertigte Halbzeuge mit einer Schäftung zu versehen. Bei einer solchen Schäftung werden beide Fügeteile unter einem Winkel von etwa 1 : 20, also L = 20 H, wobei L die Länge und H die Höhe der Schäftung ist, angefast. Vermittels dieser Schäftung an den einzelnen Fügeteilen wird dann eine kraftschlüssige Fügeverbindung aufgebaut. Diese Technologie hat sich für Reparaturmaßnahmen bewährt. Die im Verhältnis zur Bauteildicke um den Faktor 20 längere Fügefläche beinhaltet einen großen fer­ tigungstechnischen Aufwand, der neben hohen Anforderungen an die Kontur­ genauigkeit auch mit erheblichem Platzbedarf verbunden ist. Diese Technologie ist aufgrund des kostenintensiven Aufwandes weniger für die Serien- und Groß­ serienfertigung geeignet.It is known to use individual joining parts as prefabricated semi-finished products To provide shaft. With such a shaft, both joining parts are at an angle of about 1:20, so L = 20 H, where L is the length and H the The height of the shaft is chamfered. By means of this shaft to the individual Joined parts are then set up a non-positive joining connection. This Technology has proven itself for repair measures. The in relation to Component thickness 20 times longer joining area includes a large fer technical effort, in addition to high demands on the contour accuracy is also associated with considerable space requirements. This technology is less for the series and large because of the costly effort suitable for series production.

Der Erfindung liegt daher die Aufgabe zugrunde, eine kraftschlüssige Verbin­ dungsanordnung für Faserverbund-Sandwichstrukturen in Modulbauweise zu schaffen, welche einen hohen Automatisierungsgrad bei geringen Kosten reali­ siert. The invention is therefore based on the object of a non-positive connection arrangement for fiber composite sandwich structures in modular construction create a high degree of automation at low cost siert.  

Die Aufgabe wird durch die in Anspruch 1 definierte Erfindung gelöst. Weiterbil­ dungen der Erfindung sind in den Unteransprüchen definiert. Dadurch wird eine Verbindungsanordnung für Faserverbund-Sandwichstrukturen in Modulbau­ weise geschaffen, die definierte und reproduzierbare Verbindungen durch Kraft­ schluß realisiert. Die Außenfläche der zusammengefügten Sandwichstrukturen der einzelnen Faserverbundmodule oder Fügeteile ist einheitlich glatt und ver­ meidet dadurch nachteilige Einflüsse auf das Profil einer anliegenden Strömung. Die Fügeflächen der einzelnen Fügeteile ermöglichen vorteilhaft eine Selbstzen­ trierung und ermöglichen dadurch einen hohen Automatisierungsgrad mit ein­ fachen Handhabungswerkzeugen. Eine Serien- und Großserienfertigung ist da­ durch mit einer erfindungsgemäßen Verbindungsanordnung ermöglicht.The object is achieved by the invention defined in claim 1. Continuing Applications of the invention are defined in the subclaims. This will make one Connection arrangement for fiber composite sandwich structures in modular construction wisely created, the defined and reproducible connections by force finally realized. The outer surface of the assembled sandwich structures the individual fiber composite modules or joining parts is uniformly smooth and ver avoids adverse influences on the profile of an adjacent flow. The joining surfaces of the individual joining parts advantageously enable self-zening and thus enable a high degree of automation fold handling tools. A series and large series production is there made possible by a connection arrangement according to the invention.

Im Prinzip wird eine Verbindungsanordnung für Faserverbund-Sandwichstruk­ turen in Modulbauweise, wobei Fügeteile der Strukturen vorgesehen sind, ge­ schaffen, bei der die Fügeteile an ihren Stirnseiten mit Fügelippen versehen sind, und bei der Verbindungselemente vorgesehen sind, die so geformt sind, daß sie zwischen die Fügelippen aneinandergefügter Fügeteile einpassen oder einpaßbar sind und eine kraftschlüssige Verbindung der Fügeteile gebildet ist. Vorzugsweise sind eine obere und eine untere Fügelippe vorgesehen. Die obere Fügelippe ist vorzugsweise in der Ebene der Außenfläche der Fügeteile angeordnet, wohingegen die untere Fügelippe in einem Winkel zur Unterseite oder Innenfläche der Fügeteile so angeordnet ist, daß eine Selbstzentrierung der Fügeflächen der aneinandergefügten Fügeteile erzielt wird.In principle, a connection arrangement for fiber composite sandwich structure tures in modular design, with joining parts of the structures being provided, ge create, in which the parts to be joined are provided with joint lips on their end faces and in which connecting elements are provided which are shaped so that they fit between the joining lips of joined parts or are fitted and a non-positive connection of the joining parts is formed. An upper and a lower joint lip are preferably provided. The upper joint lip is preferably in the plane of the outer surface of the parts to be joined arranged, whereas the lower joint lip at an angle to the bottom or the inner surface of the joining parts is arranged so that self-centering the joining surfaces of the joined parts is achieved.

Besonders bevorzugt werden die Verbindungselemente separat gefertigt, und zwischen die Fügelippen im Bereich der Fügeflächen fest eingebracht, insbe­ sondere darin eingeklebt. Die Verbindungselemente selbst sind vorzugsweise in Varianten vorgesehen. Eine erste Variante der Verbindungselemente ist so aufgebaut, daß eine dünne faserverstärkte Außenhaut und ein Schaumkern, der von der faserverstärkten Außenhaut ummantelt wird, vorgesehen sind. Die Au­ ßenhaut hat vorzugsweise eine beanspruchungsgerechte Faserorientierung. Soll sie gegen Torsion geschützt sein, weist sie vorzugsweise ein ±45°-Gewebe aus Kohlefasern auf. Sind die einzelnen Fasern hingegen in einem 90°-Winkel als unidirektionale Lagen zueinander angeordnet, können Zug- oder Druckkräfte abgefangen werden.The connecting elements are particularly preferably manufactured separately, and firmly inserted between the joint lips in the area of the joining surfaces, in particular glued in particular. The connecting elements themselves are preferably in Variants provided. A first variant of the connecting elements is like this built that a thin fiber-reinforced outer skin and a foam core, the is covered by the fiber-reinforced outer skin, are provided. The Au Outer skin preferably has a fiber orientation that meets the requirements. If it is to be protected against torsion, it preferably has a ± 45 ° fabric made of carbon fibers. However, the individual fibers are at a 90 ° angle  Arranged as unidirectional layers to each other, tensile or compressive forces be intercepted.

Der Schaumkern weist vorzugsweise eine geringe Dichte auf. Dadurch ist er, den Anforderungen entsprechend, sehr leicht. Die Außenhaut der Verbindungs­ elemente kann entweder besonders bevorzugt durch Fasergeflechttechnologie gefertigt sein; dabei ist besonders vorteilhaft für das Verbindungselement als Halbzeug eine Fertigung in großen Stückzahlen möglich. Das Verbindungsele­ ment kann aber auch vorzugsweise vernähte Fasergelege oder -gestricke mit moderater Dehnfähigkeit aufweisen. Eine solche moderate Dehnfähigkeit liegt bei höheren Werten als die derzeitige Bemessungsgrundlage von εkrit = 0,4% für beispielsweise in der Luftfahrt eingesetzte Faserverbundstrukturen. Durch eine dreidimensionale Verstärkung infolge von Vernähen der Fasergelege oder Fasergewebe wird die Schadenstoleranz der Struktur deutlich verbessert, da auftretende Risse in ihrer Ausbreitung stark behindert werden. Infolgedessen kann die Dehnfähigkeit beispielsweise auf Werte von εkrit = 0,7 bis 0,8% erhöht werden.The foam core preferably has a low density. This makes it very light, according to the requirements. The outer skin of the connecting elements can either be particularly preferably made by braiding technology; it is particularly advantageous for the connecting element as a semifinished product to be produced in large quantities. The Verbindungsele element can also preferably have sewn fiber fabrics or knitted fabrics with moderate elasticity. Such a moderate elasticity lies at values higher than the current assessment basis of ε crit = 0.4% for fiber composite structures used for example in aviation. The damage tolerance of the structure is significantly improved by three-dimensional reinforcement as a result of sewing the fiber scrim or fiber fabric, since cracks that occur are severely hampered in their spread. As a result, the extensibility can be increased, for example, to values of ε crit = 0.7 to 0.8%.

In einer alternativen Variante ist ein entsprechendes Verbindungselement derart gefertigt, daß ein flexibler, mit flüssigem Harz vorgetränkter Gewebeschlauch mit einem Innenliner versehen wird. Ein solcher Gewebeschlauch mit Innenliner wird in die Fügefläche zwischen den Fügelippen zweier aneinanderstoßender Fügeteile eingefügt. Im Inneren des Innenliners wird ein Überdruck erzeugt. Vor­ zugsweise wird der Überdruck durch Aufblasen des Innenliners mit einem hei­ ßen oder warmen Medium, insbesondere mit Warmluft oder Heißdampf, erzeugt. Der den Innenliner umgebende Gewebeschlauch legt sich dadurch an die Kon­ tur der Fügeflächen der aneinanderstoßenden Fügeteile an. Besonders bevor­ zugt wird vermittels des Heizmediums zum Aufblasen des Innenliners zugleich die zum Aushärten des Harzes des Gewebeschlauches benötigte Temperatur­ bedingung definiert eingestellt. Dadurch verbindet das Harz der Gewebe­ schläuche die Fügeteile im Bereich der Fügeflächen zwischen den Fügelippen der aneinanderstoßenden Fügeteile vorteilhaft miteinander, verklebt diese ins­ besondere miteinander. In an alternative variant, a corresponding connecting element is of this type manufactured that a flexible fabric hose pre-soaked with liquid resin is provided with an inner liner. Such a fabric hose with an inner liner is in the joint surface between the joint lips of two abutting Joined parts inserted. Overpressure is generated inside the inner liner. Before the excess pressure is preferably increased by inflating the inner liner with a hot medium or warm medium, especially with warm air or superheated steam. The fabric hose surrounding the inner liner lies against the con the joining surfaces of the abutting joining parts. Especially before is added by means of the heating medium to inflate the inner liner at the same time the temperature required to harden the resin of the fabric hose condition defined. This connects the resin to the fabric hoses the parts to be joined in the area of the joining surfaces between the joining lips of the abutting joining parts advantageously with one another, glues them into the special with each other.  

Zur näheren Erläuterung der Erfindung werden im folgenden Ausführungsbei­ spiele einer Verbindungsanordnung für Faserverbund-Sandwichstrukturen in Modulbauweise anhand der Zeichnungen beschrieben. Diese zeigen in:In order to explain the invention in more detail, the following are examples play a connection arrangement for fiber composite sandwich structures in Modular construction described using the drawings. These show in:

Fig. 1 eine perspektivische Ansicht eines flachen Fügeteiles mit erfin­ dungsgemäßen Fügelippen, Fig. 1 is a perspective view of a flat joining part with OF INVENTION to the invention joining lips,

Fig. 2 eine perspektivische Schnittansicht von aneinandergefügten Füge­ teilen gemäß Fig. 1 mit erfindungsgemäßen Verbindungselementen, Fig. 2 is a perspective sectional view of the joined parts to be joined according to Fig. 1 according to the invention connecting elements,

Fig. 3 eine perspektivische Ansicht einer ersten Ausführungsform eines erfindungsgemäßen Verbindungselementes, Fig. 3 is a perspective view of a first embodiment of a connecting element according to the invention,

Fig. 4 eine zweite Ausführungsform eines erfindungsgemäßen Verbin­ dungselementes, und Fig. 4 shows a second embodiment of a connec tion element according to the invention, and

Fig. 5 eine perspektivische Schnittansicht einer gekrümmten Sandwich­ struktur in Modulbauweise mit erfindungsgemäßen Fügelippen und Verbindungselementen. Fig. 5 is a perspective sectional view of a curved sandwich structure in modular design with joint lips and connecting elements according to the invention.

Fig. 1 zeigt eine perspektivische Ansicht eines im wesentlichen flachen Füge­ teiles 10 mit Fügelippen 11, 12. Das Fügeteil 10 ist als Sandwichstruktur aufge­ baut. An seinem äußeren Rand ragen allseitig auf der Oberseite 13 und der Un­ terseite 14 des Fügeteils 10 die Fügelippen 11, 12 hervor. Die obere Füge­ lippe 11 ist in der Ebene der Oberseite 13 oder Außenfläche des Fügeteils 10 angeordnet. Die untere Fügelippe 12 ist in einem Winkel zur Unterseite 14 oder Innenfläche des Fügeteils 10 angeordnet. Die Unterseite der oberen Fügelippe 11, eine Außenwandung 15 des Fügeteils 10 und die Oberseite der unteren Fügelippe 12 bilden zusammen eine Fügefläche 16. Fig. 1 shows a perspective view of a substantially flat joining member 10 with joining lips 11, 12. The joining part 10 is built up as a sandwich structure. At its outer edge protrude on all sides on the top 13 and the underside 14 of the joining part 10, the joining lips 11 , 12 protrude. The upper joining lip 11 is arranged in the plane of the top 13 or outer surface of the joining part 10 . The lower joining lip 12 is arranged at an angle to the underside 14 or the inner surface of the joining part 10 . The underside of the upper joining lip 11 , an outer wall 15 of the joining part 10 and the top of the lower joining lip 12 together form a joining surface 16 .

Fig. 2 zeigt eine perspektivische Schnittansicht durch das in Fig. 1 dargestellte Fügeteil 10 mit beidseitig angefügten Fügeteilen 20, 30. Die Fügeteile 20, 30 weisen ebenfalls jeweils eine obere Fügelippe 21, 31 und eine untere Füge­ lippe 22, 32 auf. Die jeweiligen oberen Fügelippen 11, 21, 31 stoßen plan anein­ ander. Dadurch, daß die oberen Fügelippen in einer Ebene liegen, ergibt sich auf den Oberseiten 13, 23, 33 der Fügeteile eine plane Außenfläche der Ge­ samtstruktur. Eine Beeinflussung der äußeren Kontur der aneinandergefügten einzelnen Module in Form der Fügeteile in Sandwichbauweise geschieht da­ durch nicht. FIG. 2 shows a perspective sectional view through the joining part 10 shown in FIG. 1 with joining parts 20 , 30 attached on both sides. The joining parts 20 , 30 also each have an upper joining lip 21 , 31 and a lower joining lip 22 , 32 . The respective upper joint lips 11 , 21 , 31 abut each other plan. Characterized in that the upper joining lips lie in one plane, there is a flat outer surface of the entire structure on the upper sides 13 , 23 , 33 of the joining parts. The outer contour of the individual modules joined together in the form of the joining parts in sandwich construction is not affected by this.

Auch die beiden Fügeteile 20, 30 weisen mit einem Winkel zur jeweiligen Unter­ seite 24, 34 der Fügeteile angeordnete untere Fügelippen 22, 32 auf. In die sich durch die aneinandergrenzenden Fügeteile 10, 20 bzw. 10, 30 mit Außenwan­ dungen 25, 35 ergebenden Fügeflächen 16, 26 bzw. 16, 36 sind form- und kraftschlüssig Verbindungselemente 40 eingefügt.The two joining parts 20 , 30 also have lower joining lips 22 , 32 arranged at an angle to the respective underside 24 , 34 of the joining parts. In the by the adjacent joining parts 10 , 20 and 10 , 30 with Außenwan openings 25 , 35 resulting joining surfaces 16 , 26 and 16 , 36 , positive and non-positive connection elements 40 are inserted.

Die Verbindungselemente 40 sind so geformt und innerhalb der Fügeflächen befestigt, daß sie eine kraftschlüssige Verbindung der aneinandergefügten Fügeteile 10, 20 bzw. 10, 30 ermöglichen. Durch das Vorsehen der winklig zur Unterseite der jeweiligen Fügeteile angeordneten unteren Fügelippen wird eine Selbstzentrierung der Verbindungselemente 40 in den jeweiligen Füge­ flächen 16, 26 bzw. 16, 36 geschaffen.The connecting elements 40 are shaped and fastened within the joining surfaces in such a way that they enable a non-positive connection of the joining parts 10 , 20 or 10 , 30 which are joined together. By providing the lower joining lips arranged at an angle to the underside of the respective joining parts, self-centering of the connecting elements 40 in the respective joining surfaces 16 , 26 and 16 , 36 is created.

Vorzugsweise sind die Verbindungselemente 40 innerhalb der Füge­ flächen 16, 26 bzw. 16, 36 eingeklebt.The connecting elements 40 are preferably glued within the joining surfaces 16 , 26 and 16 , 36 , respectively.

Der Aufbau der separat hergestellten Verbindungselemente ist in den folgenden Figuren anhand zweier Beispiele beschrieben.The structure of the separately manufactured fasteners is as follows Figures described using two examples.

In Fig. 3 ist eine erste Ausführungsform eines erfindungsgemäßen Verbin­ dungselementes 40 in perspektivischer Ansicht dargestellt. Das Verbindungs­ element 40 weist eine dünne faserverstärkte Außenhaut 41 auf. Die Außen­ haut 41 umschließt vollständig einen inneren Schaumkern 42. Vorzugsweise weist der Schaumkern 42 eine geringe Dichte auf. Die Außenhaut 41 ist vor­ zugsweise mit einer beanspruchungsgerechten Faserorientierung ihres Gewe­ bes versehen. Beispielsweise kann eine ±45°-Orientierung eines Kohlefaser­ gewebes vorgesehen sein. Die faserverstärkte Außenhaut 41 kann beispiels­ weise durch Fasergeflechttechnologie hergestellt sein. Dadurch ist eine Ferti­ gung in großer Stückzahl möglich. Alternativ kann aber auch eine Fertigung mittels vernähter Fasergelege oder -gestricke mit moderater Dehnfähigkeit erfolgen. Jedenfalls sollte die faserverstärkte Außenhaut 41 sich der Form­ gebung des Schaumkerns 42 anpassen.In Fig. 3, a first embodiment of a connec tion element 40 according to the invention is shown in a perspective view. The connecting element 40 has a thin fiber-reinforced outer skin 41 . The outer skin 41 completely encloses an inner foam core 42 . The foam core 42 preferably has a low density. The outer skin 41 is preferably provided with a fiber orientation of its fabric that is suitable for the stress. For example, a ± 45 ° orientation of a carbon fiber fabric can be provided. The fiber-reinforced outer skin 41 can, for example, be produced by fiber braid technology. This makes it possible to produce in large numbers. Alternatively, however, production can also be carried out by means of sewn fiber fabrics or knitted fabrics with moderate stretchability. In any case, the fiber-reinforced outer skin 41 should adapt to the shape of the foam core 42 .

Der Schaumkern 42 ist so geformt, daß er optimal in die Fügeflächen zwischen den einzelnen zusammengefügten Fügeteilen einpaßt. Der Schaumkern ist da­ her stabförmig und im wesentlichen mit einem fünfeckigen Querschnitt verse­ hen. Drei Seiten des Fünfecks sind mit 90°-Winkeln zueinander angeordnet. Die beiden verbleibenden Seiten sind stumpfwinklig aneinandergefügt und weisen die halbe Länge der gegenüberliegenden Seite auf. Durch das stumpfwinklige Aneinanderfügen der beiden unteren Seiten bilden diese den Winkel der beiden unteren Fügelippen zueinander und zu den senkrecht angeordneten Außenwan­ dungen 15, 25 bzw. 15, 35 der jeweiligen Fügeteile 10, 20 bzw. 10, 30 gemäß Fig. 2 nach.The foam core 42 is shaped in such a way that it fits optimally into the joining surfaces between the individual joined joining parts. The foam core is rod-shaped and essentially hen with a pentagonal cross-section. Three sides of the pentagon are arranged at 90 ° to each other. The two remaining sides are joined at an obtuse angle and are half the length of the opposite side. Due to the obtuse-angled joining of the two lower sides, these form the angle of the two lower joining lips to one another and to the perpendicularly arranged outer wall 15 , 25 and 15 , 35 of the respective joining parts 10 , 20 and 10 , 30 according to FIG. 2.

In Fig. 4 ist eine zweite Ausführungsform eines erfindungsgemäßen Verbin­ dungselementes 50 dargestellt. Zugleich ist in Fig. 4 das Verbindungs­ element 50 in Einfügung innerhalb der Fügeteile 10, 20 bzw. 10, 30 gemäß Fig. 2 dargestellt.In Fig. 4, a second embodiment of a connec tion element 50 is shown. At the same time in Fig. 4, the connecting element 50 is shown in the insertion within the joining parts 10 , 20 and 10 , 30 of FIG. 2.

Das Verbindungselement 50 weist einen äußeren Gewebeschlauch 51 auf. Auf der Innenseite des Gewebeschlauches 51 ist ein Innenliner 52 vorgesehen. Der Gewebeschlauch 51 ist als flexibles, mit flüssigem Harz vorgetränktes Bauteil gefertigt. Der Gewebeschlauch mit Innenliner weist zunächst im nicht in die Fü­ geflächen eingefügten Zustand einen runden Querschnitt auf.The connecting element 50 has an outer fabric hose 51 . An inner liner 52 is provided on the inside of the fabric hose 51 . The fabric hose 51 is manufactured as a flexible component that is pre-saturated with liquid resin. The fabric hose with inner liner initially has a round cross section when it is not inserted into the joining surfaces.

Zum kraftschlüssigen Zusammenfügen der Fügeteile 10, 20 bzw. 10, 30 wird der Gewebeschlauch mit Innenliner in die Fügeflächen 16, 26 bzw. 16, 36 ein­ gefügt. Anschließend wird in dem Innenliner ein Überdruck erzeugt. Vorzugs­ weise wird der Überdruck mit einem warmen oder heißen Medium erzeugt. Beispielsweise wird Warmluft oder Heißdampf in den Innenliner eingeblasen und dieser dadurch aufgeblasen. Der den Innenliner umgebende Gewebe­ schlauch 51 legt sich dadurch an die Kontur der Fügeflächen 16, 26 bzw. 16, 36 der aneinanderstoßenden Fügeteile 10, 20 bzw. 10, 30 an. Durch das Einblasen eines warmen oder heißen Mediums wird die für das Aushärten des Harzes des Gewebeschlauches 51 notwendige Temperatur erzeugt. Durch entsprechende Wahl des Heizmediums zum Einblasen und Aufblasen kann eine entsprechende Temperaturbedingung definiert eingestellt werden. Das Harz des Gewebe­ schlauches wird dadurch erwärmt und verbindet, bzw. verklebt die Füge­ teile 10, 20 bzw. 10, 30 im Bereich ihrer Fügeflächen 16, 26 bzw. 16, 36 mitein­ ander. Dadurch trägt das Harz zur Stabilität des Verbindungselementes 50 bei.For the frictional joining of the joining parts 10 , 20 or 10 , 30 , the fabric hose with inner liner is inserted into the joining surfaces 16 , 26 or 16 , 36 . An overpressure is then generated in the inner liner. The overpressure is preferably generated with a warm or hot medium. For example, warm air or hot steam is blown into the inner liner, which inflates it. The fabric liner surrounding the inner liner 51 thereby lies against the contour of the joining surfaces 16 , 26 or 16 , 36 of the abutting joining parts 10 , 20 or 10 , 30 . By blowing in a warm or hot medium, the temperature required for curing the resin of the fabric tube 51 is generated. A corresponding temperature condition can be set in a defined manner by appropriately selecting the heating medium for blowing in and inflating. The resin of the fabric hose is thereby heated and connects, or glued the joint parts 10 , 20 and 10 , 30 in the area of their joining surfaces 16 , 26 and 16 , 36 mitein other. As a result, the resin contributes to the stability of the connecting element 50 .

Das Verbindungselement 50 weist nach dem Aufblasen und Aushärten des Harzes die dem Hohlraum zwischen den Fügeflächen 16, 26 bzw. 16, 36 ent­ sprechende Form auf. Diese Form entspricht auch der äußeren Form des Ver­ bindungselementes 40 gemäß der vorigen Figur.After the inflation and curing of the resin, the connecting element 50 has the shape corresponding to the cavity between the joining surfaces 16 , 26 and 16 , 36 , respectively. This shape also corresponds to the external shape of the connecting element 40 according to the previous figure.

In Fig. 5 ist eine alternative Ausführungsform des mittleren Fügeteils als ein gekrümmtes Fügeteil 60 dargestellt. Das gekrümmte Fügeteil 60 weist ebenfalls eine obere Fügelippe 61 und eine untere Fügelippe 62 auf. Die aneinandersto­ ßenden oberen Fügelippen 61 und 21 bzw. 61 und 31 bilden eine plane Außen­ fläche der Gesamtstruktur. Die jeweilige untere Fügelippe 62 kragt mit einem Winkel aus der Unterseite 64 des gekrümmten Fügeteils 60 aus. In die entste­ henden Fügeflächen 66, 26 bzw. 66, 36 sind Verbindungselemente 70 einge­ fügt. Diese entsprechen im wesentlichen den Verbindungselementen gemäß Fig. 3 bzw. Fig. 4. Aufgrund der mit einer leichten Schrägung zur Senkrechten vorgesehenen Außenwandungen 65 des gekrümmten Fügeteils 60 sind die Ver­ bindungselemente 70 ebenfalls mit einer entsprechenden Schrägung ihrer an diesen Außenwandungen 65 anliegenden Wandungen versehen. Der sonstige Aufbau der Verbindungselemente entspricht aber den Verbindungselementen gemäß Fig. 3 oder 4. Alternativ kann natürlich auch anstelle des Aufbaus ge­ mäß Fig. 3 ein Aufbau der Verbindungselemente gemäß Fig. 4, nämlich durch Vorsehen eines Gewebeschlauches mit Innenliner vorgesehen werden. Gerade wegen der schrägen Außenwandungen 65 und der dadurch anderen Fügeflä­ chenwinkel erweist sich ein Aufbau der Verbindungselemente gemäß Fig. 4 als besonders vorteilhaft.In Fig. 5, an alternative embodiment of the central joining part is shown as a curved joining portion 60. The curved joining part 60 also has an upper joining lip 61 and a lower joining lip 62 . The abutting upper joining lips 61 and 21 or 61 and 31 form a flat outer surface of the overall structure. The respective lower joint lip 62 protrudes from the underside 64 of the curved joining part 60 at an angle. In the existing joining surfaces 66 , 26 and 66 , 36 connecting elements 70 are inserted. These correspond essentially to the connecting elements according to FIG. 3 or FIG. 4. Because of the outer walls 65 of the curved joining part 60 provided with a slight inclination to the vertical, the connecting elements 70 are also provided with a corresponding inclination of their walls abutting these outer walls 65 . The other structure of the connecting elements corresponds to the connecting elements according to FIG. 3 or 4. Alternatively, of course, instead of the structure according to FIG. 3, a structure of the connecting elements according to FIG. 4, namely by providing a fabric hose with an inner liner, can be provided. Precisely because of the inclined outer walls 65 and the resulting different joint surface angle, a construction of the connecting elements according to FIG. 4 proves to be particularly advantageous.

Durch Vorsehen der entsprechenden Fügelippen an den Fügeteilen in Form von oberen und unteren Fügelippen lassen sich die einzelnen Fügeteilmodule in Sandwichstruktur zu vollständigen Strukturen zusammenkleben. Im Bereich des Leichtbaus aus Faserverbundwerkstoffen sind die erfindungsgemäßen Verbin­ dungselemente in Verbindung mit den oberen und unteren Fügelippen an den einzelnen Fügeteilen sehr nützliche Hilfsmittel für den Zusammenbau der leich­ ten Sandwichstrukturen.By providing the corresponding joining lips on the joining parts in the form of The individual joining module can be fitted in the upper and lower joining lips Glue the sandwich structure together to complete structures. In the area of Lightweight structures made of fiber composite materials are the connector according to the invention elements in connection with the upper and lower joint lips on the individual joining parts very useful tools for the assembly of the light sandwich structures.

Derartige, aus Modulen aufgebaute Gesamtstrukturen in Sandwichbauweise aus Faserverbundwerkstoffen werden besonders vorteilhaft in dem Flugbereich, im Schienenfahrzeugbau und im Schiffbau eingesetzt. Such overall structures made up of modules in sandwich construction fiber composite materials are particularly advantageous in the flight area, used in rail vehicle construction and shipbuilding.  

BezugszeichenlisteReference list

1010th

Fügeteile
Parts to be joined

1111

Fügelippe/obere Fügelippe
Joint lip / upper joint lip

1212th

Fügelippe/untere Fügelippe
Joint lip / lower joint lip

1313

Oberseite
Top

1414

Unterseite
bottom

1515

Außenwandung
Outer wall

1616

Fügefläche
Joining surface

2020th

Fügeteil
Joining part

2121

obere Fügelippe
upper joint lip

2222

untere Fügelippe
lower joint lip

2323

Oberseite
Top

2424th

Unterseite
bottom

2525th

Außenwandung
Outer wall

2626

Fügefläche
Joining surface

3030th

Fügeteil
Joining part

3131

obere Fügelippe
upper joint lip

3232

untere Fügelippe
lower joint lip

3333

Oberseite
Top

3434

Unterseite
bottom

3535

Außenwandung
Outer wall

3636

Fügefläche
Joining surface

4040

Verbindungselement
Fastener

4141

Außenhaut
Outer skin

4242

Schaumkern
Foam core

5050

Verbindungselement
Fastener

5151

Gewebeschlauch
Fabric hose

5252

Innenliner
Inner liner

6060

gekrümmtes Fügeteil
curved joint

6161

obere Fügelippe
upper joint lip

6262

untere Fügelippe
lower joint lip

6363

Oberseite
Top

6464

Unterseite
bottom

6565

Außenwandung
Outer wall

6666

Fügefläche
Joining surface

7070

Verbindungselement
Fastener

Claims (12)

1. Verbindungsanordnung für Faserverbund-Sandwichstrukturen in Modulbau­ weise, wobei Fügeteile der Strukturen vorgesehen sind, dadurch gekennzeichnet, daß die Fügeteile (10, 20, 30, 60) an ihren Stirnseiten mit Füge­ lippen (11, 12, 21, 22, 31, 32, 61, 62) versehen sind, und daß Verbindungselemente (40, 50, 70) vorgesehen sind, die so geformt sind, daß sie zwischen die Fügelippen aneinandergefügter Füge­ teile (10, 20, 30, 60) einpassen oder einpaßbar sind und eine kraftschlüssige Verbindung der Fügeteile gebildet ist.1. Connection arrangement for fiber composite sandwich structures in modular construction, whereby parts of the structures are provided, characterized in that the parts to be joined ( 10 , 20 , 30 , 60 ) on their end faces with joint lips ( 11 , 12 , 21 , 22 , 31 , 32 , 61 , 62 ) are provided, and that connecting elements ( 40 , 50 , 70 ) are provided, which are shaped so that they fit or fit between the joining lips of joined parts ( 10 , 20 , 30 , 60 ) and one non-positive connection of the joining parts is formed. 2. Verbindungsanordnung nach Anspruch 1, dadurch gekennzeichnet, daß eine obere Fügelippe (11, 21, 31, 61) in der Ebene der Außenfläche der Fügeteile liegt, und daß eine untere Fügelippe (12, 22, 32, 62) in einem Winkel zur Innenfläche oder Unterseite (14, 24, 34, 64) der Fügeteile so angeordnet ist, daß eine Selbstzentrierung der Fügeflächen (16, 26, 36, 66) von gegeneinander ge­ fügten Fügeteilen erzielt wird.2. Connection arrangement according to claim 1, characterized in that an upper joint lip ( 11 , 21 , 31 , 61 ) lies in the plane of the outer surface of the joining parts, and that a lower joint lip ( 12 , 22 , 32 , 62 ) at an angle to Inner surface or underside ( 14 , 24 , 34 , 64 ) of the joining parts is arranged so that self-centering of the joining surfaces ( 16 , 26 , 36 , 66 ) of mutually joined joining parts is achieved. 3. Verbindungsanordnung nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Verbindungselemente (40, 50, 70) separat gefertigt sind und in die Fügeflächen zum Erzeugen einer kraftschlüssigen Verbindung fest einge­ bracht, insbesondere eingeklebt, sind.3. Connection arrangement according to claim 1 or 2, characterized in that the connecting elements ( 40 , 50 , 70 ) are made separately and are firmly inserted, in particular glued, into the joining surfaces to produce a non-positive connection. 4. Verbindungsanordnung nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß die Verbindungselemente eine dünne faserverstärkte Außenhaut (41) und einen Schaumkern (42) aufweisen. 4. Connection arrangement according to one of the preceding claims, characterized in that the connecting elements have a thin fiber-reinforced outer skin ( 41 ) and a foam core ( 42 ). 5. Verbindungsanordnung nach Anspruch 4, dadurch gekennzeichnet, daß die Außenhaut (41) eine beanspruchungsgerechte Faserorientierung und der Schaumkern (42) eine geringe Dichte aufweist.5. Connection arrangement according to claim 4, characterized in that the outer skin ( 41 ) has a stress-oriented fiber orientation and the foam core ( 42 ) has a low density. 6. Verbindungsanordnung nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, daß die Außenhaut (41) der Verbindungselemente (40) durch Fasergeflecht- Technologie gefertigt ist.6. Connection arrangement according to one of the preceding claims, characterized in that the outer skin ( 41 ) of the connecting elements ( 40 ) is made by braiding technology. 7. Verbindungsanordnung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die Außenhaut (41) der Verbindungselemente (40) aus vernähten Faser­ gelegen oder -gestricken mit moderater Dehnfähigkeit, insbesondere mit ei­ ner Dehnfähigkeit von ε = 0,7 bis 0,8%, besteht.7. Connection arrangement according to one of claims 1 to 5, characterized in that the outer skin ( 41 ) of the connecting elements ( 40 ) made of sewn fiber or knitted with moderate elasticity, in particular with egg ner elasticity of ε = 0.7 to 0, 8%. 8. Verbindungsanordnung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Verbindungselemente (50) flexible, mit flüssigem Harz vorgetränkte Gewebeschläuche (51) mit Innenliner (52) aufweisen.8. Connection arrangement according to one of claims 1 to 3, characterized in that the connecting elements ( 50 ) have flexible, pre-impregnated with liquid resin fabric hoses ( 51 ) with inner liner ( 52 ). 9. Verbindungsanordnung nach Anspruch 8, dadurch gekennzeichnet, daß die Gewebeschläuche (51) mit Innenliner (52) in die Fügeflächen (16, 26, 36, 66) zwischen den Fügelippen eingefügt sind, und ein Überdruck in dem Innenliner (52) erzeugbar ist oder erzeugt ist.9. Connection arrangement according to claim 8, characterized in that the fabric hoses ( 51 ) with inner liner ( 52 ) in the joining surfaces ( 16 , 26 , 36 , 66 ) are inserted between the joining lips, and an overpressure in the inner liner ( 52 ) can be generated or is generated. 10. Verbindungsanordnung nach Anspruch 8 oder 9, dadurch gekennzeichnet, daß der Gewebeschlauch (51) sich an die Kontur der Fügeflächen (16, 26, 36, 66) durch Aufblasen des Innenliners mit einem warmen oder heißen Me­ dium, insbesondere mit Warmluft oder Heißdampf, an legt. 10. Connection arrangement according to claim 8 or 9, characterized in that the fabric hose ( 51 ) adheres to the contour of the joining surfaces ( 16 , 26 , 36 , 66 ) by inflating the inner liner with a warm or hot medium, in particular with hot air or hot steam , puts on. 11. Verbindungsanordnung nach einem der Ansprüche 8 bis 10, dadurch gekennzeichnet, daß vermittels des warmen oder heißen Mediums zum Aufblasen des Innen­ liners (52) Temperaturbedingungen für das Aushärten des Harzes der Gewe­ beschläuche (51) definiert einstellbar sind.11. Connection arrangement according to one of claims 8 to 10, characterized in that by means of the warm or hot medium for inflating the inner liner ( 52 ) temperature conditions for curing the resin of the Gewe hoses ( 51 ) are adjustable. 12. Verbindungsanordnung nach einem der Ansprüche 8 bis 11, dadurch gekennzeichnet, daß das Harz der Gewebeschläuche (51) die Fügeteile (10, 20, 30, 60) im Bereich ihrer Fügeflächen zwischen den Fügelippen miteinander verbindet, oder miteinander verklebt.12. Connection arrangement according to one of claims 8 to 11, characterized in that the resin of the fabric hoses ( 51 ) connects the joining parts ( 10 , 20 , 30 , 60 ) in the region of their joining surfaces between the joining lips, or glued together.
DE19726799A 1997-06-24 1997-06-24 Connection arrangement for fiber composite sandwich structures in modular construction and method for producing the connection arrangement Expired - Fee Related DE19726799C2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE19726799A DE19726799C2 (en) 1997-06-24 1997-06-24 Connection arrangement for fiber composite sandwich structures in modular construction and method for producing the connection arrangement
IT1998MI001445A IT1301795B1 (en) 1997-06-24 1998-06-24 CONNECTION SYSTEM FOR SANDWICH STRUCTURES IN FIBER COMPOSITE FOR MODULAR CONSTRUCTIONS.
FR9808001A FR2764840B1 (en) 1997-06-24 1998-06-24 JOINING SYSTEM FOR COMPOSITE SANDWICH STRUCTURES REINFORCED BY FIBERS IN MODULAR CONSTRUCTION

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19726799A DE19726799C2 (en) 1997-06-24 1997-06-24 Connection arrangement for fiber composite sandwich structures in modular construction and method for producing the connection arrangement

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DE19726799A1 true DE19726799A1 (en) 1999-01-07
DE19726799C2 DE19726799C2 (en) 2001-05-31

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FR (1) FR2764840B1 (en)
IT (1) IT1301795B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008022591B4 (en) * 2008-05-07 2012-12-13 Bruno Gruber Composite part and composite structure

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8834667B2 (en) * 2010-10-19 2014-09-16 The Boeing Company Method for joining sandwich truss core panels and composite structures produced therefrom
US20100186893A1 (en) * 2009-01-29 2010-07-29 Lockheed Martin Corporation System, method and apparatus for fabricating composite structures
CN104565785A (en) * 2014-12-30 2015-04-29 潘茜茜 Plate
CN104633433A (en) * 2014-12-30 2015-05-20 潘茜茜 Board

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1876723U (en) * 1963-05-22 1963-08-01 Metzeler Gummiwerke Ag SANDWICH PANEL JOINT.
DE2505232A1 (en) * 1974-02-07 1975-08-14 Sture Lennart Samuelsson METHOD OF MANUFACTURING TABLES WITH STRUCTURAL SKIN AND TABLES MANUFACTURED BY THIS PROCESS
DE9418409U1 (en) * 1994-11-17 1995-01-05 Schall Kg M Tent floor panel

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1479811A1 (en) * 1965-03-08 1969-04-30 Bil Vestfold & Karosseri A S Method for connecting sandwich elements, particularly in bodywork, and sandwich element for carrying out the method
DE58909514D1 (en) * 1988-09-19 1996-01-11 Alusuisse Lonza Services Ag Butt joint of panels and / or profiles.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1876723U (en) * 1963-05-22 1963-08-01 Metzeler Gummiwerke Ag SANDWICH PANEL JOINT.
DE2505232A1 (en) * 1974-02-07 1975-08-14 Sture Lennart Samuelsson METHOD OF MANUFACTURING TABLES WITH STRUCTURAL SKIN AND TABLES MANUFACTURED BY THIS PROCESS
DE9418409U1 (en) * 1994-11-17 1995-01-05 Schall Kg M Tent floor panel

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DD-Z.: Fertigungstechnik und Betrieb, 12.Jg., H.8,1962, S.533.537 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008022591B4 (en) * 2008-05-07 2012-12-13 Bruno Gruber Composite part and composite structure

Also Published As

Publication number Publication date
FR2764840B1 (en) 2001-03-09
DE19726799C2 (en) 2001-05-31
IT1301795B1 (en) 2000-07-07
FR2764840A1 (en) 1998-12-24
ITMI981445A1 (en) 1999-12-24

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