A method for the manufacture of a component by composite fibre construction
One or more layers of fiber material (5) are braided or wound around a two part tool core. One part (3) of the core is then removed and the wound fiber structure(6) remaining on the other half is compressed to create a preform (7). The preform is placed in a resin transfer molding tool, impregnated...
Gespeichert in:
| Hauptverfasser: | , , , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | ANDREAS GESSLER TIM LEERAAR JURGEN FILSINGER MARTIN STAUB |
| description | One or more layers of fiber material (5) are braided or wound around a two part tool core. One part (3) of the core is then removed and the wound fiber structure(6) remaining on the other half is compressed to create a preform (7). The preform is placed in a resin transfer molding tool, impregnated with resin and cured. The core half remaining in the molded fiber reinforced plastic (FRP) component is then removed. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_AU2003200918A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>AU2003200918A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_AU2003200918A13</originalsourceid><addsrcrecordid>eNqNirEKwjAQQLM4iPoPB86F1i46BrEIrjqX9LzQgLkLyWXw7y3oBzg8Hg_e2twsRNJZnuAlg84E0XH1DrVmAvHgACUmYWKF6f2NEpTAh2k5ULhorqhBeGtW3r0K7X7emP1wuZ-vDSUZqSSHxKSjfRzatl84dUfb9f9dHwqKNiM</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>A method for the manufacture of a component by composite fibre construction</title><source>esp@cenet</source><creator>ANDREAS GESSLER ; TIM LEERAAR ; JURGEN FILSINGER ; MARTIN STAUB</creator><creatorcontrib>ANDREAS GESSLER ; TIM LEERAAR ; JURGEN FILSINGER ; MARTIN STAUB</creatorcontrib><description>One or more layers of fiber material (5) are braided or wound around a two part tool core. One part (3) of the core is then removed and the wound fiber structure(6) remaining on the other half is compressed to create a preform (7). The preform is placed in a resin transfer molding tool, impregnated with resin and cured. The core half remaining in the molded fiber reinforced plastic (FRP) component is then removed.</description><edition>7</edition><language>eng</language><subject>AEROPLANES ; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; HELICOPTERS ; INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULARARTICLES ; INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS ; PERFORMING OPERATIONS ; PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCESIN A PLASTIC STATE ; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR ; SHAPING OR JOINING OF PLASTICS ; TRANSPORTING ; WORKING OF PLASTICS ; WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL</subject><creationdate>2003</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20030925&DB=EPODOC&CC=AU&NR=2003200918A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20030925&DB=EPODOC&CC=AU&NR=2003200918A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>ANDREAS GESSLER</creatorcontrib><creatorcontrib>TIM LEERAAR</creatorcontrib><creatorcontrib>JURGEN FILSINGER</creatorcontrib><creatorcontrib>MARTIN STAUB</creatorcontrib><title>A method for the manufacture of a component by composite fibre construction</title><description>One or more layers of fiber material (5) are braided or wound around a two part tool core. One part (3) of the core is then removed and the wound fiber structure(6) remaining on the other half is compressed to create a preform (7). The preform is placed in a resin transfer molding tool, impregnated with resin and cured. The core half remaining in the molded fiber reinforced plastic (FRP) component is then removed.</description><subject>AEROPLANES</subject><subject>AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>COSMONAUTICS</subject><subject>HELICOPTERS</subject><subject>INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULARARTICLES</subject><subject>INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS</subject><subject>PERFORMING OPERATIONS</subject><subject>PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCESIN A PLASTIC STATE</subject><subject>SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR</subject><subject>SHAPING OR JOINING OF PLASTICS</subject><subject>TRANSPORTING</subject><subject>WORKING OF PLASTICS</subject><subject>WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2003</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNirEKwjAQQLM4iPoPB86F1i46BrEIrjqX9LzQgLkLyWXw7y3oBzg8Hg_e2twsRNJZnuAlg84E0XH1DrVmAvHgACUmYWKF6f2NEpTAh2k5ULhorqhBeGtW3r0K7X7emP1wuZ-vDSUZqSSHxKSjfRzatl84dUfb9f9dHwqKNiM</recordid><startdate>20030925</startdate><enddate>20030925</enddate><creator>ANDREAS GESSLER</creator><creator>TIM LEERAAR</creator><creator>JURGEN FILSINGER</creator><creator>MARTIN STAUB</creator><scope>EVB</scope></search><sort><creationdate>20030925</creationdate><title>A method for the manufacture of a component by composite fibre construction</title><author>ANDREAS GESSLER ; TIM LEERAAR ; JURGEN FILSINGER ; MARTIN STAUB</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_AU2003200918A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2003</creationdate><topic>AEROPLANES</topic><topic>AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>COSMONAUTICS</topic><topic>HELICOPTERS</topic><topic>INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULARARTICLES</topic><topic>INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS</topic><topic>PERFORMING OPERATIONS</topic><topic>PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCESIN A PLASTIC STATE</topic><topic>SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR</topic><topic>SHAPING OR JOINING OF PLASTICS</topic><topic>TRANSPORTING</topic><topic>WORKING OF PLASTICS</topic><topic>WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL</topic><toplevel>online_resources</toplevel><creatorcontrib>ANDREAS GESSLER</creatorcontrib><creatorcontrib>TIM LEERAAR</creatorcontrib><creatorcontrib>JURGEN FILSINGER</creatorcontrib><creatorcontrib>MARTIN STAUB</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>ANDREAS GESSLER</au><au>TIM LEERAAR</au><au>JURGEN FILSINGER</au><au>MARTIN STAUB</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>A method for the manufacture of a component by composite fibre construction</title><date>2003-09-25</date><risdate>2003</risdate><abstract>One or more layers of fiber material (5) are braided or wound around a two part tool core. One part (3) of the core is then removed and the wound fiber structure(6) remaining on the other half is compressed to create a preform (7). The preform is placed in a resin transfer molding tool, impregnated with resin and cured. The core half remaining in the molded fiber reinforced plastic (FRP) component is then removed.</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_AU2003200918A1 |
| source | esp@cenet |
| subjects | AEROPLANES AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULARARTICLES INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS PERFORMING OPERATIONS PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCESIN A PLASTIC STATE SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TRANSPORTING WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL |
| title | A method for the manufacture of a component by composite fibre construction |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-28T01%3A56%3A56IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=ANDREAS%20GESSLER&rft.date=2003-09-25&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EAU2003200918A1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |