DE102012000508A1 - Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge - Google Patents

Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge Download PDF

Info

Publication number
DE102012000508A1
DE102012000508A1 DE201210000508 DE102012000508A DE102012000508A1 DE 102012000508 A1 DE102012000508 A1 DE 102012000508A1 DE 201210000508 DE201210000508 DE 201210000508 DE 102012000508 A DE102012000508 A DE 102012000508A DE 102012000508 A1 DE102012000508 A1 DE 102012000508A1
Authority
DE
Germany
Prior art keywords
aluminum
webs
prepreg
electrostatic charge
producing
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.)
Withdrawn
Application number
DE201210000508
Other languages
German (de)
Inventor
Nicole Frerichs
Carsten Härig
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.)
FRERICHS, NICOLE, DIPL.-ING., DE
HAERIG, CARSTEN, DIPL.-ING., DE
Original Assignee
Bob Engineering Automation und Produktentwicklung GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Bob Engineering Automation und Produktentwicklung GmbH filed Critical Bob Engineering Automation und Produktentwicklung GmbH
Priority to DE201210000508 priority Critical patent/DE102012000508A1/en
Publication of DE102012000508A1 publication Critical patent/DE102012000508A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B29C70/06—Fibrous reinforcements only
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
    • 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
    • B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
    • B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
    • B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/18—Handling of layers or the laminate
    • 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
    • B29K2705/00—Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
    • B29K2705/02—Aluminium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/18—Handling of layers or the laminate
    • B32B2038/1891—Using a robot for handling the layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/42—Alternating layers, e.g. ABAB(C), AABBAABB(C)
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two or more layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/07—Parts immersed or impregnated in a matrix
    • B32B2305/076—Prepregs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2310/00—Treatment by energy or chemical effects
    • B32B2310/021—Treatment by energy or chemical effects using electrical effects
    • B32B2310/025—Electrostatic charges
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2311/00—Metals, their alloys or their compounds
    • B32B2311/24—Aluminium

Abstract

Producing multilayered component, preferably a glass laminate aluminum reinforced epoxy component, comprises arranging alternating layers of aluminum- and prepreg webs on a surface of a laminating- and adhesive device, where outer layers of finished component are respectively formed from aluminum webs, and the prepreg webs are fixed on the aluminum webs by electrostatic charge.

Description

Die Erfindung betrifft ein Verfahren zum Herstellen eines GLARE-Bauteiles gemäß dem Oberbegriff des Anspruches 1.The invention relates to a method for producing a GLARE component according to the preamble of claim 1.

Aus der Praxis sind GLARE-Bauteile bekannt. Sie werden beispielsweise im Flugzeugbau verwendet. Die Bezeichnung GLARE steht als Abkürzung für „glassfibre reinforced epoxy”, also glasfaserverstärktem Epoxidharz (teilweise liest man auch glass-fibre reinforced aluminium). Bei diesen GLARE-Bauteilen werden abwechselnd Lagen von Aluminium- und Prepreg-Bahnen aufeinander gelegt, wobei außen jeweils eine Lage von Aluminium-Bahnen angeordnet ist. Die Abkürzung Prepreg steht für „preimpregnated fibres”, also vorimprägnierten Fasern. Diese Prepreg-Bahnen bestehen aus einem Gewebe aus Endlosfasern und einer ungehärteten duroplastischen Kunststoffmatrix. Mit anderen Worten: das Gewebe wird mit einem Harz stabilisiert, wobei die Kunststoffmatrix bereits den Härter enthält. Um die vorzeitige chemische Reaktion des Härters mit dem Bindemittel zu unterbinden, werden Prepreg-Bahnen von der Herstellung bis zur Verlegung ständig gekühlt. Dabei sind Temperaturen von bis zu minus 20° Celsius erforderlich.From practice GLARE components are known. They are used for example in aircraft. The term GLARE stands for "glassfibre reinforced epoxy", ie glass-fiber-reinforced epoxy resin (in some cases glass-fiber reinforced aluminum is also used). In these GLARE components layers of aluminum and prepreg sheets are alternately laid on top of each other, with a layer of aluminum sheets being arranged on the outside. The abbreviation prepreg stands for "preimpregnated fibers", ie preimpregnated fibers. These prepreg sheets consist of a fabric of continuous fibers and an uncured thermosetting plastic matrix. In other words, the fabric is stabilized with a resin, the plastic matrix already containing the hardener. To prevent the premature chemical reaction of the hardener with the binder, prepreg sheets are constantly cooled from manufacture to laying. It requires temperatures of up to minus 20 ° Celsius.

Bei der Herstellung von GLARE-Bauteilen – beispielsweise von schalenförmigen Flugzeugteilen – werden zunächst Aluminium-Bahnen in eine Schalenform eingelegt. Die ersten Bahnen bilden die spätere Außenseite des Bauteiles. Indem man ein GLARE-Bauteil von unten nach oben schichtweise aufbaut, wird das schalenförmige Bauteil also von außen nach innen hergestellt. An Überlappungsstellen der Aluminium-Bahnen können die Bahnen auch gekröpft sein. In diesen gekröpften Bereichen und auch an Stoßstellen wird ein Schmelzkleber eingebracht, der auch die Aufgabe hat, jegliches Eindringen von Luft und/oder Feuchtigkeit zu verhindern.In the manufacture of GLARE components - for example, shell-shaped aircraft parts - aluminum tracks are first inserted into a shell shape. The first tracks form the later outside of the component. By constructing a GLARE component layer by layer from bottom to top, the shell-shaped component is produced from outside to inside. At overlaps of the aluminum tracks, the tracks can also be cranked. In these cranked areas and at joints a hot melt adhesive is introduced, which also has the task of preventing any ingress of air and / or moisture.

Bei einer doppelt gekrümmten Schalenform werden die Aluminium-Bahnen in einer Streckmaschine auf die Schalenform vorbereitet. Das Zuschneiden der Prepreg-Bahnen erfolgt in einer weiteren Maschine, der so genannten Vorstation.In a double-curved shell mold, the aluminum sheets are prepared in a stretching machine to the shell shape. The cutting of the prepreg sheets takes place in another machine, the so-called pre-station.

Ein Nachteil nach dem Stand der Technik ist, dass zum Einlegen der Aluminium-Bahnen und der Prepreg-Bahnen und auch beim blasenfreien Glattstreichen der Prepreg-Bahnen mehrere Arbeiter benötigt werden. Zwar ist aus der Fertigung von CFK-Bauteilen (also Kohlefaser verstärkten Kunststoffen) das Ausbringen von CFK-Bahnen oder –Fäden mittels eines an einem Roboter montierten Endeffektors und einer Andrückrolle bekannt, jedoch werden dort die Bauteilen von innen nach außen herstellt und werden zudem häufig in einfacher Form gewickelt. Bei der vorliegenden Erfindung hingegen erfolgt der Aufbau der Schichten in einer Hohlform, was die Zugänglichkeit für einen Roboter erschwert.A disadvantage of the prior art is that several workers are needed to load the aluminum webs and the prepreg webs, as well as the blister-free smoothing of the prepreg webs. Although it is known from the production of CFRP components (ie carbon fiber reinforced plastics) the application of CFRP webs or threads by means of a mounted on a robot end effector and a pressure roller, but there are the components produced from the inside out and are also common wrapped in a simple form. In the present invention, however, the structure of the layers is in a mold, which makes accessibility difficult for a robot.

Da die Prepreg-Bahnen bei Ausbringen nicht mehr gekühlt sind, startet der Aushärteprozess des Epoxidharzklebers. Hier kommen nun zwei Nachteile aus dem Stand der Technik zum Tragen: Zum Einen kann die Andrückrolle ein Verschieben der Bahnen – bedingt durch Querkräfte – hervorrufen, und zum Anderen kann die Andruckrolle wegen der gekrümmten Form des Bauteiles nicht für alle Positionen der Schalenform den geeigneten Krümmungsradius aufweisen. Es kommt also zu Verquetschungen der klebenden Prepreg-Bahnen und/oder zu verbleibenden Lufteinschlüssen.Since the prepreg webs are no longer cooled when deployed, the curing process of the epoxy resin adhesive starts. Here are two disadvantages of the prior art come to fruition: On the one hand, the pressure roller cause a displacement of the tracks - due to lateral forces - and on the other hand, the pressure roller because of the curved shape of the component not for all positions of the shell shape the appropriate radius of curvature exhibit. So it comes to pinching of the adhesive prepreg sheets and / or remaining trapped air.

Ist der gesamte Schichtaufbau eines Bauteiles nun fertig, so wird nach dem Stand der Technik zunächst der Stapel an Bahnen mittels eines sogenannten Vakuum-Sackes abgedeckt, wobei der Vakuum-Sack auch noch einen Teil der Montage-Schalenform abdeckt. Durch eine Besaugungsöffnung in der Montage-Schalenform wird dann der Raum zwischen dem Vakuum-Sack und der Montage-Schalenform entlüftet. Zur Beschleunigung der Entlüftung kann zwischen der oberen Aluminium-Lage und dem Vakuum-Sack noch eine Airweave-Lage angeordnet werden. Diese Airweave-Lage ist eine watteähnliche Matte, die sich bei der Entlüftung – bzw. Besaugung zwar zusammenpresst, aber dann dennoch über genügend Kanäle verfügt, um Luft zu leiten. Danach wird die Montage-Schalenform zusammen mit dem Lagen-Stapel in einen Autoklav gebracht. In diesen Autoklav wird mit etwa 10 bar Druck weiter entlüftet und mit Hilfe der in dem Autoklav herrschenden Temperatur (mehrere 100 Grad Celsius) das Bauteil ausgehärtet.If the entire layer structure of a component is now finished, according to the prior art the stack of webs is first covered by means of a so-called vacuum bag, wherein the vacuum bag also covers part of the assembly shell mold. The space between the vacuum bag and the mounting shell mold is then vented through a suction opening in the mounting shell mold. To accelerate the vent, an airweave layer can be arranged between the upper aluminum layer and the vacuum bag. This Airweave layer is a cotton-like mat that compresses during air extraction or aspiration, but still has enough channels to conduct air. Thereafter, the mounting shell mold is placed in an autoclave together with the layer stack. In this autoclave is further vented at about 10 bar pressure and cured with the help of prevailing in the autoclave temperature (several 100 degrees Celsius), the component.

Es ist deshalb Aufgabe der Erfindung ein Verfahren für die Herstellung eines mehrlagigen bzw. mehrschichtigen Bauteils zu finden, bei welchem die Probleme nach dem Stand der Technik nicht auftreten, jedoch wenigstens wesentlich geringer sind.It is therefore an object of the invention to find a method for the production of a multilayer or multilayer component, in which the problems of the prior art do not occur, but at least substantially lower.

Die Aufgabe wird durch ein Verfahren mit den Merkmalen des Anspruches 1 gelöst. Vorteilhafte Ausgestaltungen sind mit den abhängigen Ansprüchen formuliert.The object is achieved by a method having the features of claim 1. Advantageous embodiments are formulated with the dependent claims.

Erfindungsgemäß werden die Prepreg-Bahnen nicht manuell glatt gestrichen, sondern sie werden nunmehr durch eine elektrostatische Aufladung selbsttätig zum Anlegen an die Oberfläche der Aluminium-Bahnen gebracht. Um ein elektrisches Feld zum Aufbau der Elektrostatik aufzubauen, ist mindestens ein elektrischer Pol in Form einer Emissionsspitze an einer, bevorzugt balkenförmigen Elektrode zur Oberfläche der oberen Prepreg-Bahn beabstandet. Mindestens ein weiterer Pol ist mit der unter der Prepreg-Bahn angeordneten Aluminium-Bahn in elektrischer Wirkverbindung.According to the invention, the prepreg sheets are not smoothed manually, but they are now brought by an electrostatic charge automatically applying to the surface of the aluminum sheets. In order to build up an electric field for establishing the electrostatics, at least one electrical pole in the form of an emission peak is spaced on a preferably bar-shaped electrode to the surface of the upper prepreg web. At least one further pole is in electrical connection with the aluminum track arranged below the prepreg track.

Da die Aluminium-Bahnen immer einen Randbereich besitzen, findet man auch immer einen Kontaktpunkt für den Pol. Für die Oberfläche der Prepreg-Bahn ist es vorteilhaft, wenn die Elektrode mehrere Pole aufweist, weil so ein homogeneres elektrisches Feld erzeugt werden kann. Der Abstand der Elektrode zur Prepreg-Bahn beträgt bevorzugt ungefähr 100 mm; er ist auf diesen Betrag jedoch nicht beschränkt.Since the aluminum tracks always have a border area, you will always find a contact point for the pole. It is advantageous for the surface of the prepreg sheet if the electrode has several poles, because this allows a more homogeneous electric field to be generated. The distance of the electrode from the prepreg sheet is preferably about 100 mm; he is not limited to this amount.

Da gemäß der Erfindung die Prepreg-Bahnen nicht mehr manuell ausgebracht und glatt gestrichen werden, kann man diesen Arbeitsgang auch mittels eines 7-Achsen Roboters bewerkstelligen (sechs Achsen des Roboters plus eine Achse für ein translatorisches Verfahren des Roboters längs der Bauteil-Langsachse).Since according to the invention, the prepreg webs are no longer applied manually and smoothed, this operation can also be accomplished by means of a 7-axis robot (six axes of the robot plus an axis for a translatory process of the robot along the component longitudinal axis).

Vorteilhaft ist vorgesehen, dass in einer Vorstation das Material per Kamera geprüft wird und Fehlstellen ermittelt werden. Anschließend wird der Zuschnitt einer definierten Lage in der Schale durchgeführt.It is advantageously provided that the material is checked by camera in a previous station and defects are determined. Subsequently, the blank is cut to a defined position in the shell.

Mittels eines anderen Werkzeuges des Roboters – beispielsweise einer Saugheber-Vorrichtung – können auch die Aluminium-Bahnen positioniert werden. In Verbindung mit einer Heißklebe-Vorrichtung können die Aluminium-Bahnen auch zugleich vom Roboter verklebt werden. In einer weiterem Ausgestaltung können mit einem anderen Endeffektor weitere Klebebahnen ausgelegt werden, die dann im Autoklav-Prozess aufschmelzen und die Stoßstellen schließen.By means of another tool of the robot - for example a siphon device - also the aluminum tracks can be positioned. In conjunction with a hot glue device, the aluminum webs can also be glued by the robot at the same time. In a further embodiment, further adhesive webs can be designed with another end effector, which then melt in the autoclave process and close the joints.

In einer weiteren Ausgestaltung werden anstatt von Glasfasern in den Prepreg-Bahnen Kohlefasern verwendet.In a further embodiment, carbon fibers are used instead of glass fibers in the prepreg webs.

In einer noch anderen Ausgestaltung der Erfindung wird anstelle der Prepreg-Bahnen eine Schmelzkleber-Schicht auf die Aluminium-Bahnen ausgebracht. Diese Schmelzkleber-Schicht kann eine Bahnenform haben oder auch durch Sprühen erzeugt sein.In yet another embodiment of the invention, instead of the prepreg sheets, a hot melt adhesive layer is applied to the aluminum sheets. This hot melt adhesive layer may have a sheet form or be produced by spraying.

Durch die beschriebenen Maßnahmen können nicht nur Lohnkosten, sondern auch Bauteilkosten (wie beim Stand der Technik beschrieben; Verlust des Bauteiles) gespart werden.The measures described not only save labor costs but also component costs (as described in the prior art, loss of the component).

Die Erfindung ist nicht auf das dargestellte und beschriebene Ausführungsbeispiel beschränkt, sondern umfasst insbesondere auch Varianten, die durch Kombination von in Verbindung mit der vorliegenden Erfindung beschriebenen Merkmale bzw. Elementen gebildet werden können. So kann beispielsweise das erfindungsgemäße Verfahren auch beim Etikettieren von Objekten, beim Bedrucken oder Beschichten angewandt werden. Die Anmelderin behält sich also vor, noch weitere bisher nur in der Beschreibung offenbarte Merkmale von erfindungswesentlicher Bedeutung zu beanspruchen. Die mit der Anmeldung eingereichten Patentansprüche sind somit lediglich Formulierungsvorschläge ohne Präjudiz für die Erzielung weitergehenden Patentschutzes.The invention is not limited to the illustrated and described embodiment, but in particular also includes variants that can be formed by combining features or elements described in connection with the present invention. Thus, for example, the method according to the invention can also be used in the labeling of objects, in printing or coating. The Applicant therefore reserves the right to claim further features of significance essential to the invention which have hitherto been disclosed only in the description. The claims filed with the application are thus merely formulation suggestions without prejudice to achieve further patent protection.

Claims (6)

Verfahren zur Herstellung eines mehrschichtigen bzw. mehrlagigen Bauteiles, insbesondere eines GLARE-Bauteiles, wobei auf eine Oberfläche einer Laminier- und Klebevorrichtung abwechselnd Lagen von Aluminium- und Prepreg-Bahnen ausgelegt werden, wobei bei dem fertigen Bauteil die äußeren Lagen jeweils von Aluminium-Bahnen gebildet werden, dadurch gekennzeichnet, dass die Prepreg-Bahnen mittels elektrostatischer Aufladung auf den Aluminium-Bahnen fixiert werden.A method for producing a multilayer or multi-layer component, in particular a GLARE component, wherein layers of aluminum and prepreg sheets are alternately laid on a surface of a laminating and gluing device, wherein in the finished component, the outer layers of each aluminum sheets be formed, characterized in that the prepreg sheets are fixed by means of electrostatic charge on the aluminum sheets. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass die Oberfläche der Laminier- und Klebevorrichtung mindestens einfach-gekrümmt konkav geformt ist.A method according to claim 1, characterized in that the surface of the laminating and gluing device is concave-shaped at least single-curved. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass zum Aufbau einer elektrostatischen Aufladung mindestens ein Pol zu der zu glättenden Prepreg-Bahn beabstandet ist und mindestens ein weiterer Pol mit der darunter befindlichen Aluminium-Bahn verbunden ist.A method according to claim 1 or 2, characterized in that to build up an electrostatic charge at least one pole is spaced from the to be smoothed prepreg sheet and at least one further pole is connected to the underlying aluminum sheet. Verfahren nach mindestens einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das Ablegen der Lagen von Aluminium- und Prepreg-Bahnen vollständig automatisiert ist.Method according to at least one of claims 1 to 3, characterized in that the deposition of the layers of aluminum and prepreg sheets is completely automated. Verfahren nach mindestens einem der in der Anmeldung offenbarten Merkmale.Method according to at least one of the features disclosed in the application. Verwendung eines Verfahrens nach wenigstens einem der Ansprüche 1 bis 5 für die Etikettierung, das Bedrucken und/oder das Beschichten eines Objektes.Use of a method according to at least one of claims 1 to 5 for the labeling, printing and / or coating of an object.
DE201210000508 2012-01-13 2012-01-13 Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge Withdrawn DE102012000508A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE201210000508 DE102012000508A1 (en) 2012-01-13 2012-01-13 Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201210000508 DE102012000508A1 (en) 2012-01-13 2012-01-13 Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge

Publications (1)

Publication Number Publication Date
DE102012000508A1 true DE102012000508A1 (en) 2013-07-18

Family

ID=48692990

Family Applications (1)

Application Number Title Priority Date Filing Date
DE201210000508 Withdrawn DE102012000508A1 (en) 2012-01-13 2012-01-13 Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge

Country Status (1)

Country Link
DE (1) DE102012000508A1 (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013167106A1 (en) 2012-05-08 2013-11-14 Premium Aerotec Gmbh Method and device for applying and fixing a film on a tool or component surface
DE102014118702A1 (en) 2014-12-16 2016-06-16 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Crankshaft and crankshaft assembly
DE102015009177A1 (en) 2015-07-09 2017-01-12 Broetje-Automation Gmbh Method for producing a fiber-metal laminate component of an aircraft
WO2017080841A1 (en) 2015-11-13 2017-05-18 Aleris Rolled Products Germany Gmbh Method of manufacturing a fibre metal laminate material
DE102017116033A1 (en) 2017-07-17 2019-01-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Process for producing a semifinished fiber product and a fiber composite component and its products
DE102018000272A1 (en) 2018-01-16 2019-07-18 Elfolion Gmbh Foil-like functional material and method for its production
DE102023004229A1 (en) 2022-10-21 2024-05-02 Ernst-Georg Ortwein Mounting system and unwinder

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2410479A1 (en) * 1973-03-08 1975-03-27 Simco Co Inc DEVICE AND METHOD FOR ELECTROSTATIC LAMINATION
CH621142A5 (en) * 1976-12-08 1981-01-15 Hermann Felchlin
DE29517139U1 (en) * 1995-10-27 1995-12-21 Dettke Hubertus Device for the electrostatic fixing of a multi-layer flat material
DE19513830A1 (en) * 1995-04-12 1996-10-17 Kolbe Druck Gmbh & Co Kg Labelling ticket for fresh food in transparent packaging container
DE69314175T2 (en) * 1992-07-09 1998-03-12 Structural Laminates Co SPLIT LAMINATES FOR AIRCRAFT FUSELAGE
WO2004071761A1 (en) * 2003-02-17 2004-08-26 Stichting Fmlc Laminate of metal plates and intersecting fibre layers
DE102005044823B3 (en) * 2005-09-20 2007-05-16 Airbus Gmbh Placing method of thin material layer onto relief mold for producing composite material involves arranging elastically-reversible deformable portion with attached material layer so that surface relief of material layer matches relief mold

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2410479A1 (en) * 1973-03-08 1975-03-27 Simco Co Inc DEVICE AND METHOD FOR ELECTROSTATIC LAMINATION
CH621142A5 (en) * 1976-12-08 1981-01-15 Hermann Felchlin
DE69314175T2 (en) * 1992-07-09 1998-03-12 Structural Laminates Co SPLIT LAMINATES FOR AIRCRAFT FUSELAGE
DE19513830A1 (en) * 1995-04-12 1996-10-17 Kolbe Druck Gmbh & Co Kg Labelling ticket for fresh food in transparent packaging container
DE29517139U1 (en) * 1995-10-27 1995-12-21 Dettke Hubertus Device for the electrostatic fixing of a multi-layer flat material
WO2004071761A1 (en) * 2003-02-17 2004-08-26 Stichting Fmlc Laminate of metal plates and intersecting fibre layers
DE102005044823B3 (en) * 2005-09-20 2007-05-16 Airbus Gmbh Placing method of thin material layer onto relief mold for producing composite material involves arranging elastically-reversible deformable portion with attached material layer so that surface relief of material layer matches relief mold

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013167106A1 (en) 2012-05-08 2013-11-14 Premium Aerotec Gmbh Method and device for applying and fixing a film on a tool or component surface
DE102014118702A1 (en) 2014-12-16 2016-06-16 Dr. Ing. H.C. F. Porsche Aktiengesellschaft Crankshaft and crankshaft assembly
DE102015009177A1 (en) 2015-07-09 2017-01-12 Broetje-Automation Gmbh Method for producing a fiber-metal laminate component of an aircraft
RU2752348C2 (en) * 2015-07-09 2021-07-26 Бретье-Аутомацион Гмбх Method for producing aircraft component from fiber-metal layered material
US11453179B2 (en) 2015-07-09 2022-09-27 Broetje-Automation Gmbh Method for producing a fiber metal laminate component of an airplane
WO2017080841A1 (en) 2015-11-13 2017-05-18 Aleris Rolled Products Germany Gmbh Method of manufacturing a fibre metal laminate material
DE112016005215T5 (en) 2015-11-13 2018-08-02 Aleris Rolled Products Germany Gmbh Process for producing a fiber-metal laminate material
DE102017116033A1 (en) 2017-07-17 2019-01-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Process for producing a semifinished fiber product and a fiber composite component and its products
DE102017116033B4 (en) 2017-07-17 2021-08-26 Deutsches Zentrum für Luft- und Raumfahrt e.V. Process for the production of a semi-finished fiber product and a fiber composite component as well as a fiber composite component
DE102018000272A1 (en) 2018-01-16 2019-07-18 Elfolion Gmbh Foil-like functional material and method for its production
WO2019141303A1 (en) 2018-01-16 2019-07-25 Elfolion Gmbh Foil-like functional material and method for the production thereof
DE102023004229A1 (en) 2022-10-21 2024-05-02 Ernst-Georg Ortwein Mounting system and unwinder

Similar Documents

Publication Publication Date Title
DE102012000508A1 (en) Producing e.g. glass laminate aluminum reinforced epoxy component useful in aircraft construction, comprises arranging aluminum and prepreg webs alternating layers, where prepreg webs are fixed on the aluminum webs by electrostatic charge
DE102005026010B4 (en) Method for producing a reinforced shell for forming subcomponents for aircraft
DE102008042574B4 (en) Apparatus for depositing and draping sections of a reinforcing fiber structure to produce a profile preform and method
EP3033218B1 (en) Method for producing a component from organo sheets
DE102006021110B4 (en) Apparatus and method for producing a large-scale fiber composite structural component
DE102015009177A1 (en) Method for producing a fiber-metal laminate component of an aircraft
WO2009156061A2 (en) Rotor blade for a wind turbine, method and manufacturing mold for the production thereof
WO2016023735A1 (en) Method for producing an smc component provided with a unidirectional fibre scrim
WO2007010049A1 (en) Method for producing in a tfp method one-or multi-layer layer fibre preforms and a support layer
EP2477800B1 (en) Method for reinforcing a fiber composite component and arrangement for producing a reinforced fiber composite component
EP3444107A1 (en) Method for manufacturing a sandwich component, core for a sandwich component and sandwich component
DE102012108168B4 (en) Forming tool and method for the production of fiber composite components
EP1197315A2 (en) Method for manufacturing preforms from fibre reinforced composite materials and preform obtained thereby
EP2878431B1 (en) Method for producing a fibre arrangement comprising several layers, and gripping device for performing the method
WO2016102454A2 (en) Method and apparatus for manufacturing a sandwich component
EP2519399B1 (en) Method and layment tool for producing a fiber scrim
DE102010029094A1 (en) Stringerpositionierung
EP1695889A2 (en) Elastic sidewall for covering the bellows of an intercommunicating gangway between two articulated vehicles or vehicle parts
DE102011010384A1 (en) Method for manufacturing fiber composite component, particularly structural component for vehicle, involves providing primary structure by partial curing of fiber material infiltered with matrix material
DE102015218401A1 (en) Flat car element for an elevator installation
DE102007004314B4 (en) Method for producing a fiber composite component with at least one interspersed region for an aircraft or spacecraft
DE102012111950B4 (en) draping
DE102016210090A1 (en) Method and manufacturing arrangement for producing a workpiece by press molding, and method and welding arrangement for welding
DE102010031579B4 (en) Production of fiber composite components from prepreg blanks
DE102010023669B4 (en) Continuous fiber composite components, as well as methods for manufacturing continuous fiber composite components

Legal Events

Date Code Title Description
R163 Identified publications notified
R082 Change of representative

Representative=s name: KANZLEI "REGION GOEPPINGEN" (GBR) PATENTANWALT, DE

R081 Change of applicant/patentee

Owner name: HAERIG, CARSTEN, DIPL.-ING., DE

Free format text: FORMER OWNER: BOB ENGINEERING GMBH AUTOMATION UND PRODUKTENTWICKLUNG, 73054 EISLINGEN, DE

Effective date: 20140626

Owner name: FRERICHS, NICOLE, DIPL.-ING., DE

Free format text: FORMER OWNER: BOB ENGINEERING GMBH AUTOMATION UND PRODUKTENTWICKLUNG, 73054 EISLINGEN, DE

Effective date: 20140626

R082 Change of representative
R005 Application deemed withdrawn due to failure to request examination