Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same

A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhibits a non-linear stress-strain response when mechanically load...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	FEWS ROBERT CLIVE, HOJJATI MEHDI, DERISI BIJAN, HOA SUONG VAN
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING
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	FEWS ROBERT CLIVE HOJJATI MEHDI DERISI BIJAN HOA SUONG VAN
description	A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhibits a non-linear stress-strain response when mechanically loaded to failure. A helicopter landing gear includes a pair of skids and one or more cross members extending between the pair of skids. The one or more cross members includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the cross members exhibit non-linear stress-strain responses when mechanically loaded to failure.
format	Patent
fullrecord	<record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US8998134B2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US8998134B2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US8998134B23</originalsourceid><addsrcrecordid>eNqNyzEOwjAMQNEuDAi4gw_QDFCGdgVRsQNz5bYOtUjsKEkljk-ROADTX95fF6HlnqKJxGI1DjSWMKgPmjhTCSnHechzRAee_AKB3hP3nFmeICrGsRDGr0MWk9VYZDdHApRxWfKkI6gFj6_vkdDTtlhZdIl2v24KaC_389VQ0I5SwIGEcve41U1T76vj6VD9QT71sENJ</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same</title><source>esp@cenet</source><creator>FEWS ROBERT CLIVE ; HOJJATI MEHDI ; DERISI BIJAN ; HOA SUONG VAN</creator><creatorcontrib>FEWS ROBERT CLIVE ; HOJJATI MEHDI ; DERISI BIJAN ; HOA SUONG VAN</creatorcontrib><description>A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhibits a non-linear stress-strain response when mechanically loaded to failure. A helicopter landing gear includes a pair of skids and one or more cross members extending between the pair of skids. The one or more cross members includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the cross members exhibit non-linear stress-strain responses when mechanically loaded to failure.</description><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2015</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=20150407&DB=EPODOC&CC=US&NR=8998134B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20150407&DB=EPODOC&CC=US&NR=8998134B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>FEWS ROBERT CLIVE</creatorcontrib><creatorcontrib>HOJJATI MEHDI</creatorcontrib><creatorcontrib>DERISI BIJAN</creatorcontrib><creatorcontrib>HOA SUONG VAN</creatorcontrib><title>Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same</title><description>A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhibits a non-linear stress-strain response when mechanically loaded to failure. A helicopter landing gear includes a pair of skids and one or more cross members extending between the pair of skids. The one or more cross members includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the cross members exhibit non-linear stress-strain responses when mechanically loaded to failure.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>COSMONAUTICS</subject><subject>HELICOPTERS</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2015</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyzEOwjAMQNEuDAi4gw_QDFCGdgVRsQNz5bYOtUjsKEkljk-ROADTX95fF6HlnqKJxGI1DjSWMKgPmjhTCSnHechzRAee_AKB3hP3nFmeICrGsRDGr0MWk9VYZDdHApRxWfKkI6gFj6_vkdDTtlhZdIl2v24KaC_389VQ0I5SwIGEcve41U1T76vj6VD9QT71sENJ</recordid><startdate>20150407</startdate><enddate>20150407</enddate><creator>FEWS ROBERT CLIVE</creator><creator>HOJJATI MEHDI</creator><creator>DERISI BIJAN</creator><creator>HOA SUONG VAN</creator><scope>EVB</scope></search><sort><creationdate>20150407</creationdate><title>Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same</title><author>FEWS ROBERT CLIVE ; HOJJATI MEHDI ; DERISI BIJAN ; HOA SUONG VAN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US8998134B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2015</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>COSMONAUTICS</topic><topic>HELICOPTERS</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>FEWS ROBERT CLIVE</creatorcontrib><creatorcontrib>HOJJATI MEHDI</creatorcontrib><creatorcontrib>DERISI BIJAN</creatorcontrib><creatorcontrib>HOA SUONG VAN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>FEWS ROBERT CLIVE</au><au>HOJJATI MEHDI</au><au>DERISI BIJAN</au><au>HOA SUONG VAN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same</title><date>2015-04-07</date><risdate>2015</risdate><abstract>A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhibits a non-linear stress-strain response when mechanically loaded to failure. A helicopter landing gear includes a pair of skids and one or more cross members extending between the pair of skids. The one or more cross members includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the cross members exhibit non-linear stress-strain responses when mechanically loaded to failure.</abstract><oa>free_for_read</oa></addata></record>
fulltext	fulltext_linktorsrc
identifier
ispartof
issn
language	eng
recordid	cdi_epo_espacenet_US8998134B2
source	esp@cenet
subjects	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING
title	Fiber-reinforced, composite, structural member exhibiting non-linear strain-to-failure and method of making same
url	https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-01T15%3A15%3A59IST&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=FEWS%20ROBERT%20CLIVE&rft.date=2015-04-07&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS8998134B2%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