NO20061589L - Kraftinnforingspunkt i kjernekompositter og fremgangsmate for a fremstille nevnte punkt ved bruk av forsterkningelementer som gar igjennom tykkelsen av kjernekompositten - Google Patents

Kraftinnforingspunkt i kjernekompositter og fremgangsmate for a fremstille nevnte punkt ved bruk av forsterkningelementer som gar igjennom tykkelsen av kjernekompositten

Info

Publication number
NO20061589L
NO20061589L NO20061589A NO20061589A NO20061589L NO 20061589 L NO20061589 L NO 20061589L NO 20061589 A NO20061589 A NO 20061589A NO 20061589 A NO20061589 A NO 20061589A NO 20061589 L NO20061589 L NO 20061589L
Authority
NO
Norway
Prior art keywords
core
reinforcing elements
point
composites
sewing
Prior art date
Application number
NO20061589A
Other languages
English (en)
Inventor
Matthias Alexander Roth
Original Assignee
Roehm 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
Priority claimed from DE20314187U external-priority patent/DE20314187U1/de
Priority claimed from DE2003142183 external-priority patent/DE10342183A1/de
Application filed by Roehm Gmbh filed Critical Roehm Gmbh
Publication of NO20061589L publication Critical patent/NO20061589L/no

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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • 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
    • B29C70/06—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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • 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
    • 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
    • Y10T428/249921—Web or sheet containing structurally defined element or component
    • Y10T428/249923—Including interlaminar mechanical fastener

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
  • Reinforced Plastic Materials (AREA)
  • Analysing Materials By The Use Of Radiation (AREA)
  • Geophysics And Detection Of Objects (AREA)

Abstract

Oppfinnelsen vedrører en utforming av så vel som fremstilling av kraftinnføringssteder i kjernekompositter med armeringselementer som i innføringsstedsområdet går igjennom kjernekomposittet i dennes tykkelsesretning. Kraftinnføringsstedene i kjernekompositter er i området ved innføringsstedet forsynt med armeringselementer som går igjennom kjernekomposittet, i dennes tykkelsesretning. Anordningen av armeringselementene (eksempelvis sytråder) kan fortrinnsvis skje ved hjelp av en syteknikk og med bruk av en synål. Etter syingen blir dekksjiktene (a og c), som fortrinnsvis består av tekstile halvfabrikata, og det gjennomgående hull samt armeringselementene, impregnert med flytende polymert matrisemateriale, idet det derved samtidig skjer en stoffsluttende binding av kjernematerialet til dekksjiktene.
NO20061589A 2003-09-08 2006-04-07 Kraftinnforingspunkt i kjernekompositter og fremgangsmate for a fremstille nevnte punkt ved bruk av forsterkningelementer som gar igjennom tykkelsen av kjernekompositten NO20061589L (no)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE20314187U DE20314187U1 (de) 2003-09-08 2003-09-08 Krafteinleitungsstelle in Kernverbunden mit in Dickenrichtung des Kernverbundes durchsetzenden Armierungselementen
DE2003142183 DE10342183A1 (de) 2003-09-08 2003-09-08 Krafteinleitungsstelle in Kernverbunden und Verfahren zu ihrer Herstellung mit in Dickenrichtung des Kernverbundes durchsetzenden Armierungselementen
PCT/EP2004/010033 WO2005023526A1 (de) 2003-09-08 2004-09-08 Krafteinleitungsstelle in kernverbunden und verfahren zu ihrer herstellung mit in dickenrichtung des kernverbundes durchsetzenden armierungselementen

Publications (1)

Publication Number Publication Date
NO20061589L true NO20061589L (no) 2006-06-08

Family

ID=34276551

Family Applications (1)

Application Number Title Priority Date Filing Date
NO20061589A NO20061589L (no) 2003-09-08 2006-04-07 Kraftinnforingspunkt i kjernekompositter og fremgangsmate for a fremstille nevnte punkt ved bruk av forsterkningelementer som gar igjennom tykkelsen av kjernekompositten

Country Status (14)

Country Link
US (1) US20070009712A1 (no)
EP (1) EP1663625B1 (no)
JP (1) JP4861176B2 (no)
KR (1) KR101111993B1 (no)
AT (1) ATE440717T1 (no)
AU (1) AU2004270389B2 (no)
BR (1) BRPI0414160B1 (no)
CA (1) CA2537651C (no)
DE (1) DE502004009977D1 (no)
DK (1) DK1663625T3 (no)
ES (1) ES2331076T3 (no)
HK (1) HK1094179A1 (no)
NO (1) NO20061589L (no)
WO (1) WO2005023526A1 (no)

Families Citing this family (18)

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DE102005035681A1 (de) * 2005-07-27 2007-02-08 Röhm Gmbh Fertigungsverfahren zur Armierung von Kernmaterialien für Kernverbunde sowie von Kernverbund-Strukturen
ES2329317B1 (es) * 2006-05-16 2011-10-18 Bosnor, Sl Metodo de fabricacion de placas conductivas, aplicables al recubrimiento de suelos o paredes, placa conductiva y maquina inyectora.
DE102007033120A1 (de) * 2007-07-13 2009-01-15 Evonik Röhm Gmbh Verbesserte Stumpfstoßverbindungen für Kernwerkstoffe
DE102008041788A1 (de) 2008-09-03 2010-03-11 Airbus Deutschland Gmbh Sandwichplatte mit integrierter Verstärkungsstruktur sowie Verfahren zu deren Herstellung
FR2970238B1 (fr) * 2011-01-07 2013-01-25 Airbus Operations Sas Piece et procede de reparation d'une structure endommagee, en particulier de peau d'aeronef, ainsi qu'un kit de reparation de mise en oeuvre
FR2970898B1 (fr) * 2011-01-28 2014-09-26 Snecma Piece en materiau composite comportant des elements de bossage
US20120295062A1 (en) * 2011-05-19 2012-11-22 Paul Szasz Multi-ply laminate composite materials having apertures defined therein
CN103975142B (zh) 2011-12-07 2016-09-28 株式会社Ihi 安装用凸台以及风扇壳
FR2989618A1 (fr) * 2012-04-24 2013-10-25 Skf Aerospace France Dispositif de renfort destine a ameliorer le comportement d'au moins une partie d'une piece composite
FR2998210B1 (fr) * 2012-11-20 2017-03-10 Plastic Omnium Cie Ensemble d'un insert metallique et d'une nappe de materiau composite, procede d'incorporation d'un tel insert dans une telle nappe et piece obtenue par moulage d'une telle nappe
FR3003233B1 (fr) * 2013-03-18 2016-05-06 Airbus Operations Sas Panneau de voilure pour aeronef
EP2842865B1 (en) * 2013-08-28 2019-12-18 Airbus Operations GmbH Window panel for an airframe and method of producing same
WO2015118005A2 (de) * 2014-02-07 2015-08-13 Fraunhofer-Gesellschaft Verbundbauteil und verfahren zur herstellung des verbundbauteils
US9457540B2 (en) * 2014-07-29 2016-10-04 The Boeing Company Panel-insert assembly and method
US9284972B1 (en) 2014-11-17 2016-03-15 The Boeing Company Panel-insert assembly and method
GB2541169A (en) * 2015-07-27 2017-02-15 Airbus Operations Ltd Composite structure
CN106250035B (zh) * 2015-10-19 2019-07-26 威锋数位开发股份有限公司 动态生成个人化手写字型的系统和方法
DE102016125660A1 (de) * 2016-12-23 2018-06-28 Böllhoff Verbindungstechnik GmbH Befestigungseinleger für ein Bauteil aus Kunststoff-, Schaum- oder Verbundmaterial

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DE2834237C2 (de) * 1978-08-04 1980-05-22 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Verfahren zum Einbauen von Einsätzen in Leichtbau-Sandwichplatten
JPH06126869A (ja) * 1992-10-14 1994-05-10 Mitsubishi Electric Corp ハニカムサンドイッチパネル
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FR2768076B1 (fr) * 1997-09-10 2000-08-04 Peguform France Procede de realisation d'une zone rigidifiee formant insert dans un panneau composite du type sandwich, et panneau comprenant une telle zone
JPH11179569A (ja) * 1997-12-19 1999-07-06 Nippon Light Metal Co Ltd サンドイッチパネル
DE19806484A1 (de) * 1998-02-17 1999-08-26 Abb Daimler Benz Transp Verbundteil und Verfahren zu dessen Herstellung
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JP2001246686A (ja) * 2000-03-07 2001-09-11 Toyota Autom Loom Works Ltd 複合材料構造体
EP1412164B1 (en) * 2001-08-02 2011-05-18 Ebert Composites Corporation Method of clinching top and bottom ends of z-axis fibers into the respective top and bottom surfaces of a composite laminate and composite laminate

Also Published As

Publication number Publication date
HK1094179A1 (en) 2007-03-23
BRPI0414160B1 (pt) 2014-12-02
AU2004270389B2 (en) 2009-07-30
JP4861176B2 (ja) 2012-01-25
US20070009712A1 (en) 2007-01-11
ATE440717T1 (de) 2009-09-15
KR20060079212A (ko) 2006-07-05
JP2007504968A (ja) 2007-03-08
WO2005023526A1 (de) 2005-03-17
ES2331076T3 (es) 2009-12-21
AU2004270389A1 (en) 2005-03-17
CA2537651A1 (en) 2005-03-17
DE502004009977D1 (de) 2009-10-08
EP1663625B1 (de) 2009-08-26
BRPI0414160A (pt) 2006-10-31
KR101111993B1 (ko) 2012-02-15
EP1663625A1 (de) 2006-06-07
CA2537651C (en) 2011-08-30
DK1663625T3 (da) 2009-11-30

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