DE1779024A1 - Process for the production of composite panels with outer layers of fiber-reinforced synthetic resins - Google Patents
Process for the production of composite panels with outer layers of fiber-reinforced synthetic resinsInfo
- Publication number
- DE1779024A1 DE1779024A1 DE19681779024 DE1779024A DE1779024A1 DE 1779024 A1 DE1779024 A1 DE 1779024A1 DE 19681779024 DE19681779024 DE 19681779024 DE 1779024 A DE1779024 A DE 1779024A DE 1779024 A1 DE1779024 A1 DE 1779024A1
- Authority
- DE
- Germany
- Prior art keywords
- fiber
- layers
- core
- support core
- deodorant
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims description 20
- 229920003002 synthetic resin Polymers 0.000 title claims description 12
- 239000000057 synthetic resin Substances 0.000 title claims description 11
- 238000004519 manufacturing process Methods 0.000 title claims description 10
- 239000002131 composite material Substances 0.000 title description 12
- 229920005989 resin Polymers 0.000 claims description 12
- 239000011347 resin Substances 0.000 claims description 12
- 239000002781 deodorant agent Substances 0.000 claims description 9
- 239000000835 fiber Substances 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims description 3
- 230000009974 thixotropic effect Effects 0.000 claims description 3
- 239000004927 clay Substances 0.000 claims 1
- 238000001746 injection moulding Methods 0.000 claims 1
- 239000011162 core material Substances 0.000 description 18
- 241000264877 Hippospongia communis Species 0.000 description 9
- 239000011152 fibreglass Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 241001201614 Prays Species 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000002657 fibrous material Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 229920001225 polyester resin Polymers 0.000 description 1
- 239000004645 polyester resin Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000004753 textile Substances 0.000 description 1
- 239000013008 thixotropic agent Substances 0.000 description 1
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
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D24/00—Producing articles with hollow walls
- B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
- B29D24/005—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled the structure having joined ribs, e.g. honeycomb
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2305/00—Condition, form or state of the layers or laminate
- B32B2305/02—Cellular or porous
- B32B2305/024—Honeycomb
-
- 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
- B32B2305/08—Reinforcements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Laminated Bodies (AREA)
Description
Verfahren zur Herstellung von Verbundplatten mit D@@schichten aus faserverstärklen Kunstharzen @@ Wab@nkern D Erfindung betrifft ein Verfahren zur Herstellung yon Verbundplatten, die aus Deckschichten aus faservarstärkten Kunstahrzen und einem Wabenkern bestehen, insteschdere vor solchen, die zweidimensional gekrümmt sind.Process for the production of composite panels with D @@ layers fiber reinforced synthetic resins @@ Wab @ nkern D The invention relates to a method for Manufacture of composite panels made from outer layers of fiber-reinforced synthetic vehicles and a honeycomb core, instead of those that are two-dimensionally curved are.
Bs ist bekannt, Verbundplatten aus zwei Kunststof@@eok schichten und einem dazwischen liegendsn waben- oder rasterförmigen Kern herzustellen, indem man die Ze stege des Kernes in den nooh nicht ausgehärteten@ der Deckschichten eindrückt. Für die Deckschichten werden vorzugsweise glasfaserverstärke Kunst stoffe verwendet. Als Kernmaterial setzt man ebenfalls glasfaserverstärkte Kunststoffe in Form von Wellplattenstreifen oder kunstharzimprägnierte Papierwaben ein. Das vorgenannte Verf@hren betet gegenüber dem Verbinden des Kernes mit ausgehärteten festen Deckschichten den Vorteil, daß fUr die Bindung zwischen Deckschicht und Kern kein zusätzlicher Klebstoff aufgetragen werden muß und sich trotzdem eine haltbare Verbindung ergibt. Praktisch geschieht dies dadurch, daß man eine feste Unterlage mit Verstärkungsmaterial und mit einem haltbaren flüssigen Kunstharz, vorzugsweise Polyesterharz, bsschichtet und den Kern einseitig in dieses Zaser-Harz-Gemisch eindrückt. Nach der Härtung des Kunstharzes ist die eingedrückte Seite des Kernes mit der aus dem Baser-Harz-Gemisch entstandenen »eokschicht verbunden. Um die zweite Seite des Kernes mit der zweiten Deckschicht zu verbinden, wird der Vorgang in gleicher Weise wiederholt0 Die Herstellung erfolgt demnach in zwei Arbeitsgängen.Bs is known to layers and composite panels made of two Kunststof @@ eok to produce a honeycomb or grid-shaped core lying in between by the Ze webs of the core are pressed into the nooh uncured @ of the outer layers. For the outer layers, glass fiber reinforced plastics are preferably used. Glass fiber reinforced plastics in the form of are also used as the core material Corrugated sheet strips or synthetic resin-impregnated paper honeycombs. The foregoing Procedure prays against joining the core with hardened solid cover layers the advantage that for the bond between cover layer and core no additional Adhesive must be applied and a durable connection still results. In practice, this is done by placing a solid base with reinforcement material and coated with a durable liquid synthetic resin, preferably polyester resin and press the core into this Zaser resin mixture on one side. After hardening of the synthetic resin is the indented side of the core with that of the base resin mixture resulting »eokschicht connected. Around the second side of the core with the second To connect the top layer, the process is repeated in the same way therefore takes place in two operations.
Das Verfahrensprinzip auf einen Arbeitsgang zu beschränken, ist bisher au9 Schwierigkeiten gestoßen. Beim Eindrücken des Kernes wird das Faser-Harz-Gemisch im Bereich der Zellenstage verdiohtet und das flüssige Harz herauagepreßt. Daraus ergibt sich, daß beim gleiohzeitigen Verbinden beider Deokschichten mit dem Kern zwangsläufig das aus der oberen Deokschicht durch die Zellenstege herausgepreßt. Harz abläuft und 80 die Zellenstege m oberen Ende nicht mehr so in Harz einbettet, daß eine einwandfreie Verbindung zwischen oberer Deokschicht und Kern zustande kommt. Zur Umgehung des Ablaufens des Harzes bedient man sich@nach einem anderen Verfahren der Methode, statt des mit flüssigem Harz getränkten Verstärkungsmaterjais vorimprägnierte Glasfasermatten oder-gewebe zu verwenden. Bei diesen allgemein als Preprege bezeichneten Textilien befindet sich das Kunstharz in einem vorgehärteten bzw. vorvernetztem Zustand. Es tritt beim Aushärtevorgang nicht mehr. eine dünnflüssige Phase auf und läuft daher nioht ab. Der Nachteil dieses Verfahrens besteht aber darin, daß die endgültige Aushärtung der Prepregs aur unter Wärmeeinwirkung erzielt werden kann, so. da eine Kalthärtung im Sinne des erstgenannten Verfahrens nicht möglich ist. Weiterhin lasgen sich Prepregs nur unter zwangsweiser Verformung bei gleichseitiger Temperatursuführung, z. B. tn beheizten Dr@@werkseugen, sphärisch krümmen. Bei einem zwischen zwei Prepregs eingelegten balligen Wabenkern ergibt sich eine Druckwirkung auf die, nur linienförmig im Bereich weniger @ellenstege, so. da# bei Anwendung dieses Verfahrens die Prepregs au#erhalb des Druckbereiches ausknicken bs Falten bilden. Daher beschränkt sich dieses Verfahrensprinzip auf die Herstellung ebener oder höohstens eindimensional gekrümmt er Verbundplatten.So far, the process principle has been restricted to one operation au9 encountered difficulties. When pushing in of the core will be that Fiber-resin mixture in the area of the cell days and the liquid resin is pressed out. It follows that when both deodorant layers are connected simultaneously with the The core inevitably squeezed out of the upper layer of deodorant through the cell webs. Resin runs off and 80 no longer embeds the cell bars in the resin in the upper end, that there is a perfect connection between the upper layer of deodorant and the core. Another method is used to avoid the resin running off the method, instead of the reinforcement material soaked with liquid resin, pre-impregnated Use fiberglass mats or fabrics. These are generally referred to as prepregs In textiles, the synthetic resin is in a pre-hardened or pre-crosslinked one State. It no longer occurs during the curing process. a thin phase on and therefore does not expire. The disadvantage of this method is that the final curing of the prepregs can only be achieved under the action of heat, so. since cold hardening in the sense of the first-mentioned process is not possible. Furthermore, prepregs can only be read under forced deformation with equilateral Temperature supply, e.g. B. tn heated Dr @@ werkseugen, spherically bend. At a A crowned honeycomb core inserted between two prepregs results in a pressure effect on those, only linearly in the area of less @ point webs, see above. da # when applied With this method, the prepregs can be bent or folded outside the printing area form. This process principle is therefore limited to the production of flat surfaces or at most one-dimensionally curved composite panels.
Zweok der Srfiadung ist ee, auch sphärisch gekrümmte Verbundplatten in einem Arbeitsgang herzustellen.The second charge is ee, also spherically curved composite panels to be produced in one operation.
Der Brfindx legt dabei die Aufgabe zugrunde, den Verbundplatten eine feste Verbindung zwischen den Stegen des Stutzkerns und beiden glasfaserverstärkten Deokeohiohten zu geben.The Brfindx is based on the task of giving the composite panels a fixed connection between the webs of the support core and both glass fiber reinforced To give deokeohiohten.
Das wird erfindungsgemäß dadurch erreicht, daß die Deakschichten aus faserverstärktem Kunstharz unter Verwendung eines an sich bekannten thixotropierten Harzes gefertigt und ein Stötzkern, vorwiegend ein Wabenkern, noch vor Beginn der Härtungsreaktion des Kunstharzes zwischen sie eingebracht und das Ganze während des Härtungsvorganges unter Druck miteinander verbunden wird. Auf diese Weise ist es möglich, gewölbte oder auch sphärisch gekrümmte Verbundplatten in einem Arbeitsgang unter Verwendung eines konturengetreuen Formwerkzeuges bestehend aus Matrize und Patrize, unter gleichzeitiger Wahrung der Konturengenauigkeit herzustellen. Die Deckschichten können vorteilhaft auf dem Wege des an sich bekannten Faserspritzverfahrens auf die Formwerkzeuge aufgebracht werden.This is achieved according to the invention in that the Deakschichten from fiber-reinforced synthetic resin using a known thixotropic Resin and a support core, predominantly a honeycomb core, even before the start of the Hardening reaction of the resin introduced between them and the whole thing during the hardening process is connected to one another under pressure. That way is it is possible to produce curved or spherically curved composite panels in one operation using a true-to-contour molding tool consisting of a die and Manufacture the patrix while maintaining the contour accuracy. the Cover layers can advantageously be made using the fiber spraying process known per se are applied to the molds.
Das Verfaliren nach der Erfindung ermöglicht auch die Anfertigung der Verbundplatten in einem kontinuierlioben Herstellungsproze#.The method according to the invention also enables manufacture of the composite panels in a continuous manufacturing process #.
Die Zeichnung erläutert in einem Ausführungsbeispiel das Verfahren nach der Erfindung. 8ie zeigt in Fig. 1 die schematische Darstellung der Grundelemente, beispielswaise gewölbter Verbundplatten vor der Verbindung Fig. 2 einen Querschnitt der fertigen Verbundplatte Das Formwerkzeug besteht in an sich bekannter Weise aus einer Matrize 1 und einer Patrize 2. Die mit thixotropiertem Kunstharz getränkten Fasermaterialien 3 und 4 werden im noch ungehärteten Zustand sowohl auf die Matrize 1 als auch auf die Patrize 2 aufgelegt, wobei zunächst beide Auflageflächen nach oben liegen. Es empfiehlt sich, Matrize und patrize gllichzeitlg Zu belegen bzw. die Paserharsschicht auf sie gleichstitig aufzuspritzen.The drawing explains the method in one embodiment according to the invention. 8 it shows in Fig. 1 the schematic representation of the basic elements, for example arched composite panels before the connection Fig. 2 shows a cross section the finished composite panel The molding tool consists of in a manner known per se a die 1 and a male mold 2. The impregnated with thixotropic synthetic resin Fiber materials 3 and 4 are both in the still uncured state on the die 1 as well as placed on the male mold 2, both bearing surfaces initially after lying on top. It is recommended that the female and male molds are simultaneously covered or to spray the Paserharsschicht evenly on them.
Nach den Einbringen des Wabenkernes 5 wird die Matrize 1 auf die Patrize 2 unter gleiohzeitiger Einhaltung der Konturengenauigkeit gekippt und unter Kontaktdruck gegen die Patrize 2 bis zum Ende des Aushärtens gedruckt.After the honeycomb core 5 has been introduced, the female mold 1 is placed on the male mold 2 tilted while maintaining the contour accuracy and under contact pressure printed against the male mold 2 until the end of curing.
Das. in das Kunstharz eingemischte Thixotropiemittel erteilt dem noch nicht ausgehärteten Harz die Fähigkeit, auch nach Aufbringen des Druckes an den oberen Stegteilen der Wabenkerne zu verbleiben, um dort die gewünschte Klebeverbindung genauso wie an den unteren Stegteilen einzugehen.That. Thixotropic agents mixed into the synthetic resin still give this uncured resin the ability even after pressure is applied to the To remain upper web parts of the honeycomb cores to create the desired adhesive connection there in the same way as on the lower parts of the bridge.
Die. Figur 2 zeigt die fertige Verbundplatte. Sie zeigt auch, wie der Wabensteg durah. das aufbringen des Eontakt-@@@@@@@@ in beide Deokschichten eindringt und an beiden Deokschichten eine einwandfreie Verbindung zwischen Deckschicht und Wabensteg gewährleistet ist.The. Figure 2 shows the finished composite panel. It also shows how the honeycomb bridge through. applying the Eontakt - @@@@@@@@ in both layers of deodorant penetrates and a perfect connection between the top layer on both deodorant layers and honeycomb web is guaranteed.
Claims (4)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19681779024 DE1779024A1 (en) | 1968-06-28 | 1968-06-28 | Process for the production of composite panels with outer layers of fiber-reinforced synthetic resins |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19681779024 DE1779024A1 (en) | 1968-06-28 | 1968-06-28 | Process for the production of composite panels with outer layers of fiber-reinforced synthetic resins |
Publications (1)
Publication Number | Publication Date |
---|---|
DE1779024A1 true DE1779024A1 (en) | 1971-08-26 |
Family
ID=5703690
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19681779024 Pending DE1779024A1 (en) | 1968-06-28 | 1968-06-28 | Process for the production of composite panels with outer layers of fiber-reinforced synthetic resins |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE1779024A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2718002A1 (en) * | 1977-04-22 | 1978-10-26 | Roland Sommer | Laminated glass fibre reinforced plastics panels - with cover plates and internal corrugated support elements |
EP0008677A1 (en) * | 1978-08-09 | 1980-03-19 | Wolfgang Klingel | Method for producing a translucent profilated cellular plastics panel with textured light-scattering surface |
US4563321A (en) * | 1977-10-13 | 1986-01-07 | Gessford James D | Method of producing a plastic unitary curved structure with two surfaces and a honeycomb shaped core |
DE3644676A1 (en) * | 1986-12-30 | 1988-07-14 | Schladitz Klaus | Process for producing lightweight structural parts |
DE4130620A1 (en) * | 1991-09-14 | 1993-03-25 | Eurocopter Deutschland | Bending process for shaping flat honeycomb layer - includes vacuum holding film-covered layer on flat bendable plate and second film covering over first, aids vacuum drawing into curved cavity |
-
1968
- 1968-06-28 DE DE19681779024 patent/DE1779024A1/en active Pending
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2718002A1 (en) * | 1977-04-22 | 1978-10-26 | Roland Sommer | Laminated glass fibre reinforced plastics panels - with cover plates and internal corrugated support elements |
US4563321A (en) * | 1977-10-13 | 1986-01-07 | Gessford James D | Method of producing a plastic unitary curved structure with two surfaces and a honeycomb shaped core |
EP0008677A1 (en) * | 1978-08-09 | 1980-03-19 | Wolfgang Klingel | Method for producing a translucent profilated cellular plastics panel with textured light-scattering surface |
DE3644676A1 (en) * | 1986-12-30 | 1988-07-14 | Schladitz Klaus | Process for producing lightweight structural parts |
DE4130620A1 (en) * | 1991-09-14 | 1993-03-25 | Eurocopter Deutschland | Bending process for shaping flat honeycomb layer - includes vacuum holding film-covered layer on flat bendable plate and second film covering over first, aids vacuum drawing into curved cavity |
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