LAMINATE COMPOSITE WING STRUCTURES

A wing includes a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer is characterized by a stacked plurality of generally planar plies (500) of reinforcement material structurally joined as a stack to an interior surface (160) of the wi...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	SAMPEDRO-THOMPSON, WILLIAM M, SANTINI, GREGORY M, ROACHE, RYAN CHRISTOPHER, CHOY, WENDELL C. K, CHARLES, JORDAN, DOWNEY, TYLER W, GAMBLE, MICHAEL JOHN, WATKINS, JESSICA L
Format:	Patent
Sprache:	eng ; fre ; ger
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	SAMPEDRO-THOMPSON, WILLIAM M SANTINI, GREGORY M ROACHE, RYAN CHRISTOPHER CHOY, WENDELL C. K CHARLES, JORDAN DOWNEY, TYLER W GAMBLE, MICHAEL JOHN WATKINS, JESSICA L
description	A wing includes a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer is characterized by a stacked plurality of generally planar plies (500) of reinforcement material structurally joined as a stack to an interior surface (160) of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer has a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib (140a) is positioned adjacent the interior surface, and extends generally perpendicular to the span-wise direction. The trapezoidal cross section is interfaced with the rib flange (402). The fastener (400) extends through the wing skin, the trapezoidal cross section, and the rib flange.
format	Patent
fullrecord	<record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_EP3045384A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>EP3045384A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_EP3045384A13</originalsourceid><addsrcrecordid>eNrjZFDycfT19HMMcVVw9vcN8A_2BLLCPf3cFYJDgkKdQ0KDXIN5GFjTEnOKU3mhNDeDgptriLOHbmpBfnxqcUFicmpeakm8a4CxgYmpsYWJo6ExEUoAFOMiXg</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>LAMINATE COMPOSITE WING STRUCTURES</title><source>esp@cenet</source><creator>SAMPEDRO-THOMPSON, WILLIAM M ; SANTINI, GREGORY M ; ROACHE, RYAN CHRISTOPHER ; CHOY, WENDELL C. K ; CHARLES, JORDAN ; DOWNEY, TYLER W ; GAMBLE, MICHAEL JOHN ; WATKINS, JESSICA L</creator><creatorcontrib>SAMPEDRO-THOMPSON, WILLIAM M ; SANTINI, GREGORY M ; ROACHE, RYAN CHRISTOPHER ; CHOY, WENDELL C. K ; CHARLES, JORDAN ; DOWNEY, TYLER W ; GAMBLE, MICHAEL JOHN ; WATKINS, JESSICA L</creatorcontrib><description>A wing includes a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer is characterized by a stacked plurality of generally planar plies (500) of reinforcement material structurally joined as a stack to an interior surface (160) of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer has a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib (140a) is positioned adjacent the interior surface, and extends generally perpendicular to the span-wise direction. The trapezoidal cross section is interfaced with the rib flange (402). The fastener (400) extends through the wing skin, the trapezoidal cross section, and the rib flange.</description><language>eng ; fre ; ger</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2016</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=20160720&DB=EPODOC&CC=EP&NR=3045384A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20160720&DB=EPODOC&CC=EP&NR=3045384A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>SAMPEDRO-THOMPSON, WILLIAM M</creatorcontrib><creatorcontrib>SANTINI, GREGORY M</creatorcontrib><creatorcontrib>ROACHE, RYAN CHRISTOPHER</creatorcontrib><creatorcontrib>CHOY, WENDELL C. K</creatorcontrib><creatorcontrib>CHARLES, JORDAN</creatorcontrib><creatorcontrib>DOWNEY, TYLER W</creatorcontrib><creatorcontrib>GAMBLE, MICHAEL JOHN</creatorcontrib><creatorcontrib>WATKINS, JESSICA L</creatorcontrib><title>LAMINATE COMPOSITE WING STRUCTURES</title><description>A wing includes a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer is characterized by a stacked plurality of generally planar plies (500) of reinforcement material structurally joined as a stack to an interior surface (160) of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer has a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib (140a) is positioned adjacent the interior surface, and extends generally perpendicular to the span-wise direction. The trapezoidal cross section is interfaced with the rib flange (402). The fastener (400) extends through the wing skin, the trapezoidal cross section, and the rib flange.</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>2016</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFDycfT19HMMcVVw9vcN8A_2BLLCPf3cFYJDgkKdQ0KDXIN5GFjTEnOKU3mhNDeDgptriLOHbmpBfnxqcUFicmpeakm8a4CxgYmpsYWJo6ExEUoAFOMiXg</recordid><startdate>20160720</startdate><enddate>20160720</enddate><creator>SAMPEDRO-THOMPSON, WILLIAM M</creator><creator>SANTINI, GREGORY M</creator><creator>ROACHE, RYAN CHRISTOPHER</creator><creator>CHOY, WENDELL C. K</creator><creator>CHARLES, JORDAN</creator><creator>DOWNEY, TYLER W</creator><creator>GAMBLE, MICHAEL JOHN</creator><creator>WATKINS, JESSICA L</creator><scope>EVB</scope></search><sort><creationdate>20160720</creationdate><title>LAMINATE COMPOSITE WING STRUCTURES</title><author>SAMPEDRO-THOMPSON, WILLIAM M ; SANTINI, GREGORY M ; ROACHE, RYAN CHRISTOPHER ; CHOY, WENDELL C. K ; CHARLES, JORDAN ; DOWNEY, TYLER W ; GAMBLE, MICHAEL JOHN ; WATKINS, JESSICA L</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3045384A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2016</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>SAMPEDRO-THOMPSON, WILLIAM M</creatorcontrib><creatorcontrib>SANTINI, GREGORY M</creatorcontrib><creatorcontrib>ROACHE, RYAN CHRISTOPHER</creatorcontrib><creatorcontrib>CHOY, WENDELL C. K</creatorcontrib><creatorcontrib>CHARLES, JORDAN</creatorcontrib><creatorcontrib>DOWNEY, TYLER W</creatorcontrib><creatorcontrib>GAMBLE, MICHAEL JOHN</creatorcontrib><creatorcontrib>WATKINS, JESSICA L</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SAMPEDRO-THOMPSON, WILLIAM M</au><au>SANTINI, GREGORY M</au><au>ROACHE, RYAN CHRISTOPHER</au><au>CHOY, WENDELL C. K</au><au>CHARLES, JORDAN</au><au>DOWNEY, TYLER W</au><au>GAMBLE, MICHAEL JOHN</au><au>WATKINS, JESSICA L</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>LAMINATE COMPOSITE WING STRUCTURES</title><date>2016-07-20</date><risdate>2016</risdate><abstract>A wing includes a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer is characterized by a stacked plurality of generally planar plies (500) of reinforcement material structurally joined as a stack to an interior surface (160) of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer has a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib (140a) is positioned adjacent the interior surface, and extends generally perpendicular to the span-wise direction. The trapezoidal cross section is interfaced with the rib flange (402). The fastener (400) extends through the wing skin, the trapezoidal cross section, and the rib flange.</abstract><oa>free_for_read</oa></addata></record>
fulltext	fulltext_linktorsrc
identifier
ispartof
issn
language	eng ; fre ; ger
recordid	cdi_epo_espacenet_EP3045384A1
source	esp@cenet
subjects	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING
title	LAMINATE COMPOSITE WING STRUCTURES
url	https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-21T17%3A18%3A18IST&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=SAMPEDRO-THOMPSON,%20WILLIAM%20M&rft.date=2016-07-20&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EEP3045384A1%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