DE4118286A1 - Honeycomb core laminate prodn. - by prefabricating e.g. thermoplastic FRP edges and incorporating them when hot pressing core and e.g. thermoplastic FRP skins - Google Patents
Honeycomb core laminate prodn. - by prefabricating e.g. thermoplastic FRP edges and incorporating them when hot pressing core and e.g. thermoplastic FRP skinsInfo
- Publication number
- DE4118286A1 DE4118286A1 DE19914118286 DE4118286A DE4118286A1 DE 4118286 A1 DE4118286 A1 DE 4118286A1 DE 19914118286 DE19914118286 DE 19914118286 DE 4118286 A DE4118286 A DE 4118286A DE 4118286 A1 DE4118286 A1 DE 4118286A1
- Authority
- DE
- Germany
- Prior art keywords
- edges
- covers
- mould
- edge profiles
- thermoplastic frp
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- 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
- B29C67/00—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00
- B29C67/0044—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00 for shaping edges or extremities
-
- 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
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/60—Multitubular or multicompartmented articles, e.g. honeycomb
- B29L2031/608—Honeycomb structures
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
Description
Die Erfindung bezieht sich auf ein Verfahren zur Herstellung von Sandwichbauteilen gemäß dem Gattungsbegriff des Anspruchs 1.The invention relates to a method for producing Sandwich components according to the preamble of claim 1.
Verfahren zur Herstellung von Sandwichbauteilen sind an sich in vielfältigen Ausführungsformen bekannt, wobei jedes dieser Verfahren gemäß dem zu fertigenden Bauteil spezialisiert ist. Auch das vorliegende Verfahren ist auf die Herstellung von Sandwichbauteilen aus faserverstärkten Duroplasten unter Verwen dung von vorimprägnierten Halbzeugen, wie die vorstehend schon angesprochenen Hexagonalwaben mit Deckschichten.Methods for manufacturing sandwich components are inherently in known various embodiments, each of these Specialized process according to the component to be manufactured. The present process is also based on the production of Sandwich components made of fiber-reinforced thermosets using of pre-impregnated semi-finished products, such as those already mentioned addressed hexagonal honeycombs with cover layers.
Bei allen diesen Verfahren besteht bis heute noch das erhebliche Problem, daß keine exakten Randabschlüsse erhalten werden und dies insbesondere bei solchen Bauteilen, bei denen Hexagonalwa ben verwendet werden. Durch den jeweiligen Stützwerkstoff wird kein Druck in seitlicher Richtung aufgebaut, was bisher zusätz liche Maßnahmen erfordert, um die sonst entstehenden schlecht ausgeprägten Randprofile zu vermeiden, die in aufwendiger Weise nachgearbeitet werden müssen. In all of these processes, the significant remains to this day Problem that no exact border seals are obtained and this is particularly the case with components in which Hexagonalwa ben can be used. Through the respective support material no pressure built up in the lateral direction, which was previously additional measures required to avoid the otherwise arising bad to avoid pronounced edge profiles in a complex manner have to be reworked.
Beim Stand der Technik wird bei Duroplasten als Matrix für die Deckschichten versucht, den vorbeschriebenen Nachteil schlechter Randprofile dadurch zu beheben, daß durch aufschäumende Systeme - wie beispielsweise Spleißkleber - eine Volumenvergrößerung herbeigeführt wird, um dadurch dann einen gewissen Druck auch in seitlicher Richtung aufzubauen. Für thermoplastische Deckschich ten sind jedoch aufgrund der höheren Verarbeitungstemperaturen bisher keine vorteilhaften Maßnahmen zur Erzielung guter Randab schlüsse bekanntgeworden. Darum ist das Problem der Herstellung von Sandwichbauteilen mit thermoplastischen Deckschichten, bei denen die Randprofile voll und exakt ausgebildet sind, ohne Nachbearbeitungen etc. bisher nicht zu lösen.In the prior art, thermosets are used as a matrix for the Top layers tried to make the above disadvantage worse Fix edge profiles by using foaming systems - such as splice glue - an increase in volume is brought about, in order to then also a certain pressure in build sideways. For thermoplastic top layers However, due to the higher processing temperatures So far, no advantageous measures to achieve good Randab conclusions became known. That is why the problem is manufacturing of sandwich components with thermoplastic cover layers, at which the edge profiles are fully and precisely designed without Postprocessing etc. has not yet been resolved.
Der vorliegenden Erfindung liegt die Aufgabe zugrunde, ein Verfahren aufzuzeigen mit dem die Nachteile des Standes der Technik beseitigt werden können und nachbearbeitungsfreie Rand profile bei den eingangs genannten Sandwichbauelementen erzielt werden.The present invention is based on the object Show methods with the disadvantages of the prior art Technology can be eliminated and post-processing edge profiles achieved in the sandwich components mentioned above will.
Diese Aufgabe wird durch die im Anspruch 1 aufgezeigten Maßnah men gelöst. In den Unteransprüchen sind Weiterbildungen und Ausgestaltungen angegeben und in der nachfolgenden Beschreibung sind Ausführungsbeispiele erläutert.This object is achieved by the measure indicated in claim 1 men solved. Further training and are in the subclaims Refinements specified and in the description below Exemplary embodiments are explained.
Die Figuren der Zeichnung ergänzen diese Erläuterungen. Es zeigenThe figures in the drawing complete these explanations. It demonstrate
Fig. 1a ein Schemabild eines Bauteils in Form einer sogenannten Hatrack-Klappe mit eingesetzten vorgefertigten Profil randelementen in Draufsicht, FIG. 1a is a schematic diagram of a component in the form of a so-called hat rack flap with inserted prefabricated profile elements edge in plan view,
Fig. 1b eine Seitenansicht des Bauteils gemäß Fig. 1a, FIG. 1b is a side view of the device according to Fig. 1a,
Fig. 2a einen Schnitt entlang der Linie A-A gemäß Fig. 1a mit gestrichelt gezeichneter Werkzeugform in schematischer Darstellung, Fig. 2a shows a section along the line AA shown in Fig. 1a with dashed lined mold in a schematic representation;
Fig. 2b einen Schnitt eines weiteren Ausführungsbeispiels bezüglich des Ansatzes der vorgeformten Profilrandele mente an das Sandwichbauteil. Fig. 2b shows a section of a further embodiment with respect to the approach of the preformed Profilrandele elements to the sandwich component.
Das vorgeschlagene Verfahren wird am Beispiel einer sogenannten Hatrack-Klappe, wie sie in den Fig. 1a und 1b schematisch skizziert ist, erläutert. Das eingangs geschilderte Problem bei der Herstellung von Sandwichbauteilen 10 mit thermoplastischen Einzelelementen - wie beispielsweise die Deckschichten 12 aus Prepregteilen - bei denen die Ränder voll ausgeformt sind, wird nun dadurch gelöst, daß diese Randprofile 11 in einem ersten Arbeitsgang vorgefertigt werden, beispielsweise als Spritzguß teile. Daran schließt sich der eigentliche Preßvorgang an, bei dem die matrixartigen Deckschichten 12 mit dem Hexagonalwaben- Formkern 13 verbunden werden. Hierzu werden in einer Werkzeug form 14 die Deckschichten 12 mit dem Formkern 13 und den ange setzten Randprofilen 11 so eingelegt, daß die Randprofile 11 aus der Werkzeugform 14 herausragen, wie dies in Fig. 2a skizziert ist. Anschließend wird die Werkzeugform 14 auf die Schweißtempe ratur, die im allgemeinen bei Thermoplastmaterial 180°C oder etwas mehr beträgt, aufgeheizt. The proposed method is explained using the example of a so-called hatrack flap, as is schematically outlined in FIGS . 1a and 1b. The problem described above in the production of sandwich components 10 with thermoplastic individual elements - such as the cover layers 12 made of prepreg parts - in which the edges are fully formed, is now solved in that these edge profiles 11 are prefabricated in a first operation, for example parts as injection molding . This is followed by the actual pressing process, in which the matrix-like cover layers 12 are connected to the hexagonal honeycomb mold core 13 . For this purpose, the cover layers 12 with the mandrel 13 and the attached edge profiles 11 are inserted in a mold 14 so that the edge profiles 11 protrude from the mold 14 , as is sketched in Fig. 2a. The mold 14 is then heated to the welding temperature, which is generally 180.degree. C. or slightly more for thermoplastic material.
Dadurch daß die Randprofile außerhalb der Werkzeugform 14 zu liegen kommen, werden diese nicht oder nur sehr unwesentlich mit aufgeheizt, wodurch deren im ersten Arbeitsgang geschaffene Form voll beibehalten wird. In den Fig. 2a und 2b sind Ausfüh rungsbeispiele für die formgerechte Verbindung von Sandwichbau teil 12, 13 und vorgeformten Randprofilen 11 dargestellt. Gemäß Fig. 2a werden die Randprofile 11 über das Sandwichbauteil 12, 13 gestülpt. Hierzu weisen deren Randkanten eine Verjüngung auf, die in die Paßformnute 11a des Randprofils 11 eingeführt werden, d. h. das Randprofil 11 wird mit seiner Nute 11a über den Bau teilrand gedrückt.Because the edge profiles come to lie outside the mold 14 , they are not heated or are heated only to a very minor extent, as a result of which the shape created in the first operation is fully retained. In FIGS. 2a and 2b are examples of exporting approximately part 12 for the form fair compound of sandwich construction, 13 and preformed edge profiles 11 is shown. Referring to FIG. 2a, the edge profiles 11 are placed over the sandwich component 12, 13. For this purpose, the marginal edges have a taper, which are inserted into the fit groove 11 a of the edge profile 11 , ie the edge profile 11 is pressed with its groove 11 a over the partial edge of the construction.
Bei dem Ausführungsbeispiel gemäß Fig. 2b ist das Randprofil 11 mit einer Paßleiste 11b versehen, während die Deckschichten 12 über den Formkern 13 des Sandwichbauteils 10 vorstehen und sich an diese Paßleiste anpressen. In beiden Fällen werden die Deckschichten 12 mit dem Formkern 13 in üblicher Weise mit Druck beaufschlagt und somit die Randprofile mit den Deckschich ten 12 und dem Formkern 13 verbunden. Anschließend wird der komplette Aufbau unter Druck abgekühlt und ausgehärtet und dann das fertige Bauteil 10 - hier die Hatrack-Klappe - aus der Werkzeugform 14 entfernt. Als Ergebnis ergibt sich nun ein Bauteil 10, bei dem die Randprofile 11 voll und exakt ausgeformt sind und daher keinerlei Nacharbeitsaufwand mehr erforderlich ist.In the embodiment according to Fig. 2b, the edge profile is provided with a register strip 11 b 11 while the surface layers 12 protrude beyond the mold core 13 of the sandwich component 10 and is pressed against this register strip. In both cases, the cover layers 12 are pressurized with the mandrel 13 in the usual manner and thus the edge profiles with the cover layers th 12 and the mandrel 13 are connected. The entire assembly is then cooled and cured under pressure and then the finished component 10 - here the hatrack flap - is removed from the mold 14 . The result is a component 10 in which the edge profiles 11 are fully and precisely shaped and therefore no rework is required.
Die Eckverbindungen der vorgeformten Profile können auf ver schiedene Weise erfolgen, beispielsweise durch Verschraubung, durch Nut und Federn oder Paßflächen und Paßbolzen etc. Auch ist eine Anbindung durch Klebung oder "one-shot-bonding" beim Härten der Klappe denkbar. Außerdem können die Profile zusätzlich noch mit Halterungen für Scharniere usw. versehen sein.The corner connections of the preformed profiles can be ver different ways, for example by screwing, by tongue and groove or mating surfaces and fitting bolts etc. Also a connection by gluing or "one-shot-bonding" during hardening the flap conceivable. In addition, the profiles can also be provided with brackets for hinges, etc.
Claims (4)
- a) die Randprofile (11) des Bauteils (10) in einem vorge schalteten Arbeitsgang fertig ausgeformt werden,
- b) die matrixartigen Deckschichten (12), der Formkern (13) und die Randprofile (11) in eine Werkzeugform (14) paßge recht eingelegt werden,
- c) die Werkzeugform (14) mit Ausnahme der Randprofile (11) anschließend auf die Schweißtemperatur des Deckschichten materials aufgeheizt und mit entsprechendem Druck belastet wird und
- d) unter Druckbelastung stehend abgekühlt wird.
- a) the edge profiles ( 11 ) of the component ( 10 ) are completely formed in an upstream operation,
- b) the matrix-like cover layers ( 12 ), the mandrel ( 13 ) and the edge profiles ( 11 ) are inserted in a tool mold ( 14 ) in a suitable manner,
- c) the mold ( 14 ), with the exception of the edge profiles ( 11 ), is then heated to the welding temperature of the cover layer material and is subjected to the appropriate pressure, and
- d) is cooled while under pressure.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19914118286 DE4118286C2 (en) | 1991-06-04 | 1991-06-04 | Process for the production of sandwich components from fiber-reinforced thermoplastics |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19914118286 DE4118286C2 (en) | 1991-06-04 | 1991-06-04 | Process for the production of sandwich components from fiber-reinforced thermoplastics |
Publications (2)
Publication Number | Publication Date |
---|---|
DE4118286A1 true DE4118286A1 (en) | 1992-12-10 |
DE4118286C2 DE4118286C2 (en) | 1998-06-04 |
Family
ID=6433149
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19914118286 Expired - Lifetime DE4118286C2 (en) | 1991-06-04 | 1991-06-04 | Process for the production of sandwich components from fiber-reinforced thermoplastics |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE4118286C2 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2745523A1 (en) * | 1996-03-04 | 1997-09-05 | Manducher Sa | FORMING MOLD FOR A COMPOSITE STACK |
FR2876307A1 (en) * | 2004-10-11 | 2006-04-14 | Peguform France Sa | VEHICLE PIECE HAVING NON-FLUABLE MATERIAL |
EP2946918A1 (en) * | 2014-05-23 | 2015-11-25 | Airbus Defence and Space GmbH | Sandwich component and method for producing a sandwich component |
FR3032908A1 (en) * | 2015-02-24 | 2016-08-26 | Airbus Defence & Space Sas | REINFORCED COMPOSITE PANEL |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3906127A (en) * | 1973-09-10 | 1975-09-16 | Teledyne Inc | Drawing board |
DE3401959A1 (en) * | 1983-01-20 | 1984-07-26 | Norden Packaging Machinery AB, Kalmar | DEVICE FOR SEALING HOLLOW BODIES |
DE3704906A1 (en) * | 1986-02-19 | 1987-10-15 | Otto Dietzsch | Insulating panel |
EP0389978A2 (en) * | 1989-03-28 | 1990-10-03 | Cytec Technology Corp. | Composite panel |
-
1991
- 1991-06-04 DE DE19914118286 patent/DE4118286C2/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3906127A (en) * | 1973-09-10 | 1975-09-16 | Teledyne Inc | Drawing board |
DE3401959A1 (en) * | 1983-01-20 | 1984-07-26 | Norden Packaging Machinery AB, Kalmar | DEVICE FOR SEALING HOLLOW BODIES |
DE3704906A1 (en) * | 1986-02-19 | 1987-10-15 | Otto Dietzsch | Insulating panel |
EP0389978A2 (en) * | 1989-03-28 | 1990-10-03 | Cytec Technology Corp. | Composite panel |
Non-Patent Citations (1)
Title |
---|
DE-Z: Fertigungstechnik u. Betrieb, August 1962, Heft 8, S. 533-537 * |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2745523A1 (en) * | 1996-03-04 | 1997-09-05 | Manducher Sa | FORMING MOLD FOR A COMPOSITE STACK |
EP0794051A1 (en) * | 1996-03-04 | 1997-09-10 | Peguform France | Forming mould for a stacked multilayered structure |
US6050630A (en) * | 1996-03-04 | 2000-04-18 | Peguform France | Molded composite stack |
FR2876307A1 (en) * | 2004-10-11 | 2006-04-14 | Peguform France Sa | VEHICLE PIECE HAVING NON-FLUABLE MATERIAL |
WO2006040323A1 (en) * | 2004-10-11 | 2006-04-20 | Cadence Innovation | Vehicle part made of a non-yieldable material, method and mould for the production of said part |
EP2946918A1 (en) * | 2014-05-23 | 2015-11-25 | Airbus Defence and Space GmbH | Sandwich component and method for producing a sandwich component |
US10399299B2 (en) | 2014-05-23 | 2019-09-03 | Airbus Defence and Space GmbH | Sandwich component and method for producing a sandwich component |
FR3032908A1 (en) * | 2015-02-24 | 2016-08-26 | Airbus Defence & Space Sas | REINFORCED COMPOSITE PANEL |
WO2016135103A1 (en) * | 2015-02-24 | 2016-09-01 | Airbus Defence And Space Sas | Reinforced composite panel |
Also Published As
Publication number | Publication date |
---|---|
DE4118286C2 (en) | 1998-06-04 |
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Legal Events
Date | Code | Title | Description |
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OP8 | Request for examination as to paragraph 44 patent law | ||
8127 | New person/name/address of the applicant |
Owner name: DEUTSCHE AEROSPACE AIRBUS GMBH, 2000 HAMBURG, DE |
|
8127 | New person/name/address of the applicant |
Owner name: DAIMLER-BENZ AEROSPACE AIRBUS GMBH, 21129 HAMBURG, |
|
8125 | Change of the main classification |
Ipc: B29C 65/02 |
|
D2 | Grant after examination | ||
8364 | No opposition during term of opposition | ||
8327 | Change in the person/name/address of the patent owner |
Owner name: DAIMLERCHRYSLER AEROSPACE AIRBUS GMBH, 21129 HAMBU |
|
8327 | Change in the person/name/address of the patent owner |
Owner name: EADS AIRBUS GMBH, 21129 HAMBURG, DE |
|
8327 | Change in the person/name/address of the patent owner |
Owner name: AIRBUS DEUTSCHLAND GMBH, 21129 HAMBURG, DE |
|
8327 | Change in the person/name/address of the patent owner |
Owner name: AIRBUS OPERATIONS GMBH, 21129 HAMBURG, DE |
|
R071 | Expiry of right | ||
R071 | Expiry of right |