WO2007012353A1 - Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde sowie von kernverbund-strukturen - Google Patents
Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde sowie von kernverbund-strukturen Download PDFInfo
- Publication number
- WO2007012353A1 WO2007012353A1 PCT/EP2006/003110 EP2006003110W WO2007012353A1 WO 2007012353 A1 WO2007012353 A1 WO 2007012353A1 EP 2006003110 W EP2006003110 W EP 2006003110W WO 2007012353 A1 WO2007012353 A1 WO 2007012353A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- core material
- core
- reinforcing
- sandwich structure
- sewing
- Prior art date
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
- B29C70/086—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 pure plastics material, e.g. foam layers
-
- 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
-
- 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
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
- Y10T156/1062—Prior to assembly
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49801—Shaping fiber or fibered material
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49833—Punching, piercing or reaming part by surface of second part
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49833—Punching, piercing or reaming part by surface of second part
- Y10T29/49835—Punching, piercing or reaming part by surface of second part with shaping
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49838—Assembling or joining by stringing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
- Y10T428/24612—Composite web or sheet
Definitions
- the invention relates to the design and production of reinforcing elements penetrating in the thickness direction of the core composite according to the preamble of claim 1 for reinforcing core composite structures.
- the invention is suitable for reinforcing core composite structures.
- the core composite structure may preferably be made of fiber-plastic composite with outer layers of textile semifinished products (FIGS. 1, 3 and 5, eg fabrics, scrims, mats, etc.), a core material (FIG. 1, 4, eg polymeric foam ) and a polyme . matrix material (thermoplastic or duromer).
- Kem-composites are structures constructed in layers, which consist of relatively thin upper (FIG. 1, 3) and lower outer layers (FIG. 1, 5) and of a relatively thick core layer (FIG.
- the transversal eg compression and tensile strength and strength in the z-direction, shear stiffness and strength in the xz and yz plane, peel resistance between the cover layer and the core, fail-safe behavior
- the in-plane mechanical properties of core composite structures eg stiffness and strength in the direction of the plate plane
- This additional expansion corresponds approximately to the cross-sectional area of the sewing thread ( Figure 2). Again, the larger the cross-sectional area of the sewing thread used, the greater the additional expansion.
- Figures 4 and 5 show the possible increase in suture volume content as the number of suture threads in the core hole increase.
- the black curve in Figure 4 describes the proportional increase of the Nähfadenvolumengehalts with constant core hole diameter, the black dot-dashed curve according to the above theory of exact positioning accuracy and the additional expansion of the core hole diameter due to the introduced sutures and the dotted curve describes the true course of Nähfadenvolumengehalts increasing number of sewing threads or punctures.
- the resulting diameter in the polymeric core material when using more conventional production methods depends mainly on the sewing needle diameter used, the cross-sectional area of the sewing thread and on the pore diameter of the polymeric rigid foam used. Since in all previously known Arm michsvon sewing needle and sewing thread at the same time pierce the core composite structure, there is always an unfavorable ratio of introduced cross-sectional area of the reinforcing elements to the size of the core hole diameter. High fiber volume contents in Kemloch bemesser, similar to the fiber volume content of the outer layers (> 50%), can thus not be achieved with conventional Arm michsvon.
- the aim must be to achieve the highest possible fiber volume content of the reinforcement in the core hole diameter.
- the high resin content in Kemloch micr ensures an increase in weight, which is not tolerated in particular in aerospace.
- the invention is based on the object to improve the mechanical properties of core composite structures by introducing reinforcing elements in the thickness direction of the core composite structure (z-direction), with the possibility to achieve a high Faservolumgehalt the armor in Kemloch bemesser. Furthermore, the weight should not be influenced too negatively by the introduction of the reinforcing elements into the core composite structure.
- This novel sewing technique can also be used for preforming as well as for attaching additional component components (eg stringers, frames, etc.) to the core composite structure. solution
- FIG. 1 illustrates the underlying invention and design of such artig armored core composite structure.
- a gripper system (2) pierces one side of one side of the core composite structure (step 1 and 2) into the core material (4) and optionally through the top (3) and bottom textile cover layer (5) (step 2) and takes with help a gripper (1) on the opposite side of a reinforcing structure (6), z.
- Sewing thread Sewing thread, pultruded fiber reinforced rods fed via means (7) (step 2), and introduces the reinforcing structure during the backward movement into the core composite structure (step 3).
- the gripper system (2) moves upwards and pulls the reinforcing structure into the core or into the core composite structure (step 3).
- the core material (4) can be a polymeric rigid foam (eg PMI, PVC, PEI, PU etc.).
- the core material (4) can have a thickness of up to 150 mm, a width of about 1250 mm and a length of 2500 mm.
- the upper (3) and lower (5) textile cover layers may be the same or different and made of glass, carbon, aramid or other reinforcing materials.
- the thickness of a single textile cover layer layer may be the same or different and be between 0.1 mm and 1, 0 mm.
- Thermoplastic or thermosets can be used as the polymer matrix material.
- the reinforcing structure (6) can consist both of textile reinforcing structures (eg sewing threads, rovings) or of rod-shaped elements (eg pins of unidirectional fiber-plastic composite, unreinforced plastic or metal, etc.).
- Typical diameters of the reinforcing structure (6) may be 0.1 mm to 2.0 mm.
- the material to be sewn or the reinforcing unit is transported on to the next puncturing position and the reinforcing process is then repeated there.
- the supplied reinforcing structure can be cut to length, so that there is no connection from one puncture to another.
- the cut can be done by any common technical means, such as by cutting or flaming.
- the core composite structure can be impregnated with a thermosetting or thermoplastic matrix material in a liquid composite molding process.
Abstract
Description
Claims
Priority Applications (15)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR1020087002100A KR101319703B1 (ko) | 2005-07-27 | 2006-04-05 | 샌드위치 구조물 내 코어 재료의 강화 방법 및 강화된 샌드위치 구조물 |
CN2006800185389A CN101198459B (zh) | 2005-07-27 | 2006-04-05 | 用于加固夹层结构的芯部材料的制造方法 |
DK06724058.0T DK1907193T3 (da) | 2005-07-27 | 2006-04-05 | Fremstillingsfremgangsmåde til armering af kernematerialer til kernesamlinger |
AU2006274270A AU2006274270B2 (en) | 2005-07-27 | 2006-04-05 | Method for producing a core material reinforcement for sandwich structures and said sandwich structures |
EP06724058A EP1907193B8 (de) | 2005-07-27 | 2006-04-05 | Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde |
JP2008523137A JP4751448B2 (ja) | 2005-07-27 | 2006-04-05 | サンドイッチ構造のための芯材を補強するための製造方法ならびにサンドイッチ構造物 |
US11/914,064 US20080226876A1 (en) | 2005-07-27 | 2006-04-05 | Method for Producing a Core Material Reinforcement for Sandwich Structures and Said Sanwich Structures |
NZ563572A NZ563572A (en) | 2005-07-27 | 2006-04-05 | Method for producing a core material reinforcement for sandwich structures and said sandwich structures |
AT06724058T ATE500049T1 (de) | 2005-07-27 | 2006-04-05 | Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde |
DE502006009011T DE502006009011D1 (de) | 2005-07-27 | 2006-04-05 | Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde |
PL06724058T PL1907193T3 (pl) | 2005-07-27 | 2006-04-05 | Sposób wytwarzania wzmocnienia materiałów rdzeniowych |
BRPI0613882-9A BRPI0613882A2 (pt) | 2005-07-27 | 2006-04-05 | processo de produção para o reforço de materiais de núcleo para compósitos de núcleo e estruturas de compósito de núcleo |
CA2616655A CA2616655C (en) | 2005-07-27 | 2006-04-05 | Production method for reinforcing core materials for core composites and core composite structures |
IL186761A IL186761A (en) | 2005-07-27 | 2007-10-18 | Method for producing a core material reinforcement for sandwich structures and said sandwich structures |
HK08112447.6A HK1120768A1 (en) | 2005-07-27 | 2008-11-13 | Method for producing a core material reinforcement for sandwich structures |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102005035681A DE102005035681A1 (de) | 2005-07-27 | 2005-07-27 | Fertigungsverfahren zur Armierung von Kernmaterialien für Kernverbunde sowie von Kernverbund-Strukturen |
DE102005035681.8 | 2005-07-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2007012353A1 true WO2007012353A1 (de) | 2007-02-01 |
Family
ID=36609036
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2006/003110 WO2007012353A1 (de) | 2005-07-27 | 2006-04-05 | Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde sowie von kernverbund-strukturen |
Country Status (20)
Country | Link |
---|---|
US (1) | US20080226876A1 (de) |
EP (1) | EP1907193B8 (de) |
JP (1) | JP4751448B2 (de) |
KR (1) | KR101319703B1 (de) |
CN (1) | CN101198459B (de) |
AT (1) | ATE500049T1 (de) |
AU (1) | AU2006274270B2 (de) |
BR (1) | BRPI0613882A2 (de) |
CA (1) | CA2616655C (de) |
DE (2) | DE102005035681A1 (de) |
DK (1) | DK1907193T3 (de) |
ES (1) | ES2361617T3 (de) |
HK (1) | HK1120768A1 (de) |
IL (1) | IL186761A (de) |
NZ (1) | NZ563572A (de) |
PL (1) | PL1907193T3 (de) |
RU (1) | RU2419543C2 (de) |
TW (1) | TWI388429B (de) |
WO (1) | WO2007012353A1 (de) |
ZA (1) | ZA200800782B (de) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102007033120A1 (de) * | 2007-07-13 | 2009-01-15 | Evonik Röhm Gmbh | Verbesserte Stumpfstoßverbindungen für Kernwerkstoffe |
CN101417518A (zh) * | 2007-10-25 | 2009-04-29 | 赢创罗姆有限责任公司 | 双面-单针-底线-缝纫技术 |
WO2010026054A1 (de) | 2008-09-03 | 2010-03-11 | Airbus Operations Gmbh | Sandwichplatte mit integrierter verstärkungsstruktur sowie verfahren zu deren herstellung |
DE102013018158A1 (de) | 2013-12-05 | 2015-06-11 | Airbus Defence and Space GmbH | Verfahren zur Herstellung von verstärkten Materialien und Material erhältlich aus diesem Verfahren |
DE102015202035A1 (de) * | 2015-02-05 | 2016-08-11 | Bayerische Motoren Werke Aktiengesellschaft | Verfahren zur Herstellung eines Faser-Kunststoff-Verbund-Bauteils |
EP3263321A1 (de) * | 2016-06-29 | 2018-01-03 | Airbus Defence and Space GmbH | Verfahren zur herstellung eines sandwich-paneels mit einem verstärkten schaumstoffkern |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7861969B2 (en) * | 2007-05-24 | 2011-01-04 | The Boeing Company | Shaped composite stringers and methods of making |
US7879276B2 (en) | 2007-11-08 | 2011-02-01 | The Boeing Company | Foam stiffened hollow composite stringer |
DE102007055684A1 (de) * | 2007-11-21 | 2009-06-10 | Airbus Deutschland Gmbh | Vorrichtung zur Herstellung eines verstärkten Schaumwerkstoffes |
DE102008006981B3 (de) * | 2008-01-31 | 2009-06-10 | Airbus Deutschland Gmbh | Verfahren zum Herstellen eines Kernverbundes, insbesondere eines Kernverbundes im Luft- und Raumfahrtbereich |
US8127450B2 (en) * | 2008-01-31 | 2012-03-06 | Airbus Operations Gmbh | Method for producing a sandwich construction, in particular a sandwich construction for the aeronautical and aerospace fields |
DE102008001826B3 (de) * | 2008-05-16 | 2009-09-17 | Airbus Deutschland Gmbh | Ausschnittverstärkung für Kernverbunde sowie ein Verfahren zum Herstellen einer Ausschnittverstärkung für Kernverbunde |
US8540921B2 (en) | 2008-11-25 | 2013-09-24 | The Boeing Company | Method of forming a reinforced foam-filled composite stringer |
US8500066B2 (en) | 2009-06-12 | 2013-08-06 | The Boeing Company | Method and apparatus for wireless aircraft communications and power system using fuselage stringers |
US8570152B2 (en) | 2009-07-23 | 2013-10-29 | The Boeing Company | Method and apparatus for wireless sensing with power harvesting of a wireless signal |
US8617687B2 (en) | 2009-08-03 | 2013-12-31 | The Boeing Company | Multi-functional aircraft structures |
DE102010054935B4 (de) * | 2010-12-17 | 2013-11-28 | Daimler Ag | Karosseriemodulbauteil |
WO2014016068A1 (de) | 2012-07-24 | 2014-01-30 | Evonik Industries Ag | Neuer formgebungsprozess für pmi-schaumwerkstoffe bzw. daraus hergestellte compositebauteile |
GB2510133B (en) * | 2013-01-24 | 2017-08-30 | Bae Systems Plc | Conductive bonded composites |
DE102013223347A1 (de) | 2013-11-15 | 2015-05-21 | Evonik Industries Ag | Mit Poly(meth)acrylimid-Schaum gefüllte Wabenstrukturen |
DE102014014961A1 (de) * | 2014-10-14 | 2016-04-14 | Airbus Defence and Space GmbH | Vorrichtung sowie Verfahren |
WO2016102244A1 (de) * | 2014-12-22 | 2016-06-30 | Basf Se | Faserverstärkung von schaumstoffen aus miteinander verbundenen segmente |
DE102015110855B4 (de) | 2015-07-06 | 2019-12-05 | Technische Universität Chemnitz | Verfahren zur Fertigung von komplexen 3D-Preformen |
RU2678021C1 (ru) * | 2017-09-11 | 2019-01-22 | Государственное бюджетное образовательное учреждение высшего образования Московской области "Технологический университет" | Способ изготовления объемно армированного композиционного материала |
GB201903190D0 (en) * | 2019-03-09 | 2019-04-24 | Rolls Royce Plc | An apparatus for gripping a plurality of reinforcement rods |
DE102019114433A1 (de) * | 2019-05-29 | 2020-12-03 | Airbus Operations Gmbh | Verfahren und ein System zum Herstellen eines Bauteils oder Halbzeugs mit einem faserverstärkten Schaumkern |
FR3098444B1 (fr) | 2019-07-08 | 2021-10-01 | Soc Internationale Pour Le Commerce Et Lindustrie | Procédé de renforcement d’un panneau et un procédé de fabrication de panneau composite mettant en œuvre un tel procédé |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2245862A (en) * | 1990-07-03 | 1992-01-15 | Short Brothers Plc | Manufacture of a composite material |
US5741574A (en) * | 1993-05-04 | 1998-04-21 | Foster-Miller, Inc. | Truss reinforced foam core sandwich |
US5935680A (en) * | 1995-11-01 | 1999-08-10 | The Boeing Company | Interlaced Z-pin sandwich structure |
US20060006023A1 (en) * | 2004-07-08 | 2006-01-12 | The United States Of America As Represented By Secretary Of The Army | Combination rear impact guard, ladder, and ramp for military cargo vehicles |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2996330A (en) * | 1959-11-12 | 1961-08-15 | Edwin L Hutto | Remotely operated manipulator |
DE3246803A1 (de) * | 1982-12-17 | 1984-06-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Verfahren zum herstellen von bauteilen aus lagen von faserverstaerktem kunststoff |
DE4030989A1 (de) * | 1990-10-01 | 1992-04-09 | Airbus Gmbh | Verfahren und vorrichtung zum verstaerken von bauteilen aus lagen von faserverstaerktem thermoplastischem kunststoff |
DE4200855A1 (de) * | 1992-01-15 | 1993-07-22 | Mst Draenbedarf | Schutzabdeckung fuer erdboeden |
ES2208694T3 (es) * | 1995-08-21 | 2004-06-16 | Foster-Miller, Inc. | Sistema para insertar elementos en estructura de material compuesto. |
US5876652A (en) * | 1996-04-05 | 1999-03-02 | The Boeing Company | Method for improving pulloff strength in pin-reinforced sandwich structure |
US6722842B1 (en) * | 1998-01-13 | 2004-04-20 | Btm Corporation | End arm manipulator |
US6367856B1 (en) * | 1999-04-15 | 2002-04-09 | Thomas J. Jasperse | Transfer apparatus for automated parts movement |
US7056576B2 (en) * | 2001-04-06 | 2006-06-06 | Ebert Composites, Inc. | 3D fiber elements with high moment of inertia characteristics in composite sandwich laminates |
US7105071B2 (en) * | 2001-04-06 | 2006-09-12 | Ebert Composites Corporation | Method of inserting z-axis reinforcing fibers into a composite laminate |
US6676785B2 (en) * | 2001-04-06 | 2004-01-13 | Ebert Composites Corporation | Method of clinching the top and bottom ends of Z-axis fibers into the respective top and bottom surfaces of a composite laminate |
US6645333B2 (en) * | 2001-04-06 | 2003-11-11 | Ebert Composites Corporation | Method of inserting z-axis reinforcing fibers into a composite laminate |
US6984277B2 (en) * | 2003-07-31 | 2006-01-10 | Siemens Westinghouse Power Corporation | Bond enhancement for thermally insulated ceramic matrix composite materials |
EP1663625B1 (de) * | 2003-09-08 | 2009-08-26 | Evonik Röhm GmbH | Krafteinleitungsstelle in kernverbunden und verfahren zu ihrer herstellung mit in dickenrichtung des kernverbundes durchsetzenden armierungselementen |
US7563497B2 (en) * | 2004-12-27 | 2009-07-21 | Mkp Structural Design Associates, Inc. | Lightweight, rigid composite structures |
DE102005024408A1 (de) * | 2005-05-27 | 2006-11-30 | Airbus Deutschland Gmbh | Verstärkung von Schaumwerkstoffen |
DE102007055684A1 (de) * | 2007-11-21 | 2009-06-10 | Airbus Deutschland Gmbh | Vorrichtung zur Herstellung eines verstärkten Schaumwerkstoffes |
-
2005
- 2005-07-27 DE DE102005035681A patent/DE102005035681A1/de not_active Withdrawn
-
2006
- 2006-04-05 NZ NZ563572A patent/NZ563572A/en not_active IP Right Cessation
- 2006-04-05 WO PCT/EP2006/003110 patent/WO2007012353A1/de active Application Filing
- 2006-04-05 AU AU2006274270A patent/AU2006274270B2/en not_active Ceased
- 2006-04-05 CN CN2006800185389A patent/CN101198459B/zh not_active Expired - Fee Related
- 2006-04-05 DE DE502006009011T patent/DE502006009011D1/de active Active
- 2006-04-05 PL PL06724058T patent/PL1907193T3/pl unknown
- 2006-04-05 CA CA2616655A patent/CA2616655C/en not_active Expired - Fee Related
- 2006-04-05 EP EP06724058A patent/EP1907193B8/de not_active Not-in-force
- 2006-04-05 KR KR1020087002100A patent/KR101319703B1/ko not_active IP Right Cessation
- 2006-04-05 US US11/914,064 patent/US20080226876A1/en not_active Abandoned
- 2006-04-05 JP JP2008523137A patent/JP4751448B2/ja not_active Expired - Fee Related
- 2006-04-05 RU RU2008106981/12A patent/RU2419543C2/ru not_active IP Right Cessation
- 2006-04-05 AT AT06724058T patent/ATE500049T1/de active
- 2006-04-05 BR BRPI0613882-9A patent/BRPI0613882A2/pt not_active IP Right Cessation
- 2006-04-05 DK DK06724058.0T patent/DK1907193T3/da active
- 2006-04-05 ES ES06724058T patent/ES2361617T3/es active Active
- 2006-04-19 TW TW095113987A patent/TWI388429B/zh not_active IP Right Cessation
-
2007
- 2007-10-18 IL IL186761A patent/IL186761A/en not_active IP Right Cessation
-
2008
- 2008-01-25 ZA ZA200800782A patent/ZA200800782B/xx unknown
- 2008-11-13 HK HK08112447.6A patent/HK1120768A1/xx not_active IP Right Cessation
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2245862A (en) * | 1990-07-03 | 1992-01-15 | Short Brothers Plc | Manufacture of a composite material |
US5741574A (en) * | 1993-05-04 | 1998-04-21 | Foster-Miller, Inc. | Truss reinforced foam core sandwich |
US5935680A (en) * | 1995-11-01 | 1999-08-10 | The Boeing Company | Interlaced Z-pin sandwich structure |
US20060006023A1 (en) * | 2004-07-08 | 2006-01-12 | The United States Of America As Represented By Secretary Of The Army | Combination rear impact guard, ladder, and ramp for military cargo vehicles |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009010316A1 (de) * | 2007-07-13 | 2009-01-22 | Evonik Röhm Gmbh | Verbesserte stumpfstossverbindungen für kernwerkstoffe |
DE102007033120A1 (de) * | 2007-07-13 | 2009-01-15 | Evonik Röhm Gmbh | Verbesserte Stumpfstoßverbindungen für Kernwerkstoffe |
CN101417518B (zh) * | 2007-10-25 | 2013-08-14 | 赢创罗姆有限责任公司 | 双面-单针-底线-缝纫技术 |
CN101417518A (zh) * | 2007-10-25 | 2009-04-29 | 赢创罗姆有限责任公司 | 双面-单针-底线-缝纫技术 |
WO2009053129A1 (de) * | 2007-10-25 | 2009-04-30 | Evonik Röhm Gmbh | Zweiseiten-einnadel-unterfaden-nähtechnik |
JP2011502558A (ja) * | 2007-10-25 | 2011-01-27 | エボニック レーム ゲゼルシャフト ミット ベシュレンクテル ハフツング | 両面単針アンダースティッチ縫製法 |
US8474388B2 (en) | 2007-10-25 | 2013-07-02 | Evonik Roehm Gmbh | Two-sided single-needle understitch sewing technique |
US8741416B2 (en) | 2008-09-03 | 2014-06-03 | Airbus Operations Gmbh | Sandwich panel with integrated reinforcing structure and method for the production thereof |
WO2010026054A1 (de) | 2008-09-03 | 2010-03-11 | Airbus Operations Gmbh | Sandwichplatte mit integrierter verstärkungsstruktur sowie verfahren zu deren herstellung |
US9636901B2 (en) | 2008-09-03 | 2017-05-02 | Airbus Operations Gmbh | Method for producing a sandwich panel with an integrated reinforcing structure |
DE102013018158A1 (de) | 2013-12-05 | 2015-06-11 | Airbus Defence and Space GmbH | Verfahren zur Herstellung von verstärkten Materialien und Material erhältlich aus diesem Verfahren |
EP2886302A2 (de) | 2013-12-05 | 2015-06-24 | Airbus Defence and Space GmbH | Verfahren zur Herstellung von verstärkten Materialien und Material erhältlich aus diesem Verfahren |
US9937692B2 (en) | 2013-12-05 | 2018-04-10 | Airbus Defence and Space GmbH | Method for the manufacture of reinforced materials and material that can be obtained from this method |
DE102015202035A1 (de) * | 2015-02-05 | 2016-08-11 | Bayerische Motoren Werke Aktiengesellschaft | Verfahren zur Herstellung eines Faser-Kunststoff-Verbund-Bauteils |
EP3263321A1 (de) * | 2016-06-29 | 2018-01-03 | Airbus Defence and Space GmbH | Verfahren zur herstellung eines sandwich-paneels mit einem verstärkten schaumstoffkern |
US10737463B2 (en) | 2016-06-29 | 2020-08-11 | Airbus Defence and Space GmbH | Method for producing a sandwich panel comprising a reinforced foam core |
Also Published As
Publication number | Publication date |
---|---|
DE502006009011D1 (de) | 2011-04-14 |
CN101198459B (zh) | 2012-02-22 |
AU2006274270B2 (en) | 2011-06-16 |
RU2008106981A (ru) | 2009-09-10 |
ES2361617T3 (es) | 2011-06-20 |
EP1907193B8 (de) | 2011-10-12 |
ZA200800782B (en) | 2008-12-31 |
KR20080031908A (ko) | 2008-04-11 |
DE102005035681A1 (de) | 2007-02-08 |
AU2006274270A1 (en) | 2007-02-01 |
DK1907193T3 (da) | 2011-06-14 |
NZ563572A (en) | 2010-08-27 |
IL186761A (en) | 2011-01-31 |
EP1907193A1 (de) | 2008-04-09 |
BRPI0613882A2 (pt) | 2011-02-15 |
HK1120768A1 (en) | 2009-04-09 |
PL1907193T3 (pl) | 2011-08-31 |
TWI388429B (zh) | 2013-03-11 |
JP2009502562A (ja) | 2009-01-29 |
JP4751448B2 (ja) | 2011-08-17 |
CA2616655C (en) | 2014-01-07 |
IL186761A0 (en) | 2008-02-09 |
CN101198459A (zh) | 2008-06-11 |
EP1907193B1 (de) | 2011-03-02 |
RU2419543C2 (ru) | 2011-05-27 |
CA2616655A1 (en) | 2007-02-01 |
US20080226876A1 (en) | 2008-09-18 |
TW200709929A (en) | 2007-03-16 |
KR101319703B1 (ko) | 2013-10-17 |
ATE500049T1 (de) | 2011-03-15 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1907193B8 (de) | Fertigungsverfahren zur armierung von kernmaterialien für kernverbunde | |
WO2009053129A9 (de) | Zweiseiten-einnadel-unterfaden-nähtechnik | |
DE102014015976A1 (de) | Verbundkonstruktion für eine erhöhte Lebensdauer | |
EP1663625B1 (de) | Krafteinleitungsstelle in kernverbunden und verfahren zu ihrer herstellung mit in dickenrichtung des kernverbundes durchsetzenden armierungselementen | |
EP3489000A1 (de) | Verfahren zum herstellen eines faserverbundbauteils | |
EP3704180B1 (de) | Faserverstärktes verbundmaterial und verfahren zur herstellung eines faserverstärkten verbundmaterials | |
EP2280821B1 (de) | Ausschnittsverstärkung für kernverbunde und verfahren zu deren herstellung | |
EP2886302B1 (de) | Verfahren zur herstellung von verstärkten materialien und material erhältlich aus diesem verfahren | |
DE102012001055B4 (de) | Bauteil | |
DE102015012516B4 (de) | Verfahren zum Herstellen eines Bauteils | |
DE102013218572A1 (de) | Verfahren zum Verbinden von Preform-Strukturen | |
DE10342183A1 (de) | Krafteinleitungsstelle in Kernverbunden und Verfahren zu ihrer Herstellung mit in Dickenrichtung des Kernverbundes durchsetzenden Armierungselementen | |
DE102004054345B4 (de) | Dreidimensional verstärktes Faserverbundbauteil mit zumindest einem Schlaufenbereich sowie Verfahren zum Herstellen desselben | |
DE20314187U1 (de) | Krafteinleitungsstelle in Kernverbunden mit in Dickenrichtung des Kernverbundes durchsetzenden Armierungselementen | |
DE102018202727A1 (de) | Verfahren zum Herstellen eines Sandwichbauteils und Sandwichbauteil | |
WO2019161969A1 (de) | Fadenstruktur | |
DE102018108745A1 (de) | Faserverbundbauteil, Hybridbauteil und Verfahren zum Herstellen eines Faserverbundbauteils |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
WWE | Wipo information: entry into national phase |
Ref document number: 2006724058 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 186761 Country of ref document: IL |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2006274270 Country of ref document: AU |
|
WWE | Wipo information: entry into national phase |
Ref document number: 11914064 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 563572 Country of ref document: NZ |
|
WWE | Wipo information: entry into national phase |
Ref document number: 200680018538.9 Country of ref document: CN |
|
ENP | Entry into the national phase |
Ref document number: 2006274270 Country of ref document: AU Date of ref document: 20060405 Kind code of ref document: A |
|
WWP | Wipo information: published in national office |
Ref document number: 2006274270 Country of ref document: AU |
|
WWE | Wipo information: entry into national phase |
Ref document number: MX/a/2008/000859 Country of ref document: MX |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2616655 Country of ref document: CA Ref document number: 420/CHENP/2008 Country of ref document: IN Ref document number: 1020087002100 Country of ref document: KR |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2008523137 Country of ref document: JP |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2008106981 Country of ref document: RU |
|
WWP | Wipo information: published in national office |
Ref document number: 2006724058 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: PI0613882 Country of ref document: BR Kind code of ref document: A2 Effective date: 20080124 |