HIGH-LIFT DEVICE OF FLIGHT VEHICLE
A high-lift device of a flight vehicle, the high-lift device comprising: a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and a vortex supp...
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| creator | HAYAMA, KENJI ISOTANI, KAZUHIDE |
| description | A high-lift device of a flight vehicle, the high-lift device comprising: a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein: the vortex suppressing portion is a flow suppressing portion formed at an upper surface side of a leading edge portion of the tip end portion of the flap main body and configured to cause a flow along the upper surface of the tip end portion of the flap main body to be separated from the upper surface; and the flow suppressing portion is a projection provided along the wing span direction and projecting upward from the upper surface of the flap main body.
L'invention concerne un dispositif hypersustentateur (3) destiné à un aéronef, comprenant : un corps principal de volet (11) se trouvant au niveau de la partie de bord de fuite de l'aile principale (2) de l'aéronef de façon à pouvoir être déployé et logé et s'étendant le long de la direction de l'envergure de l'aile principale (2) ; et une partie de suppression de tourbillons (100, 200, 300, 400, 500, 600) se trouvant au niveau d'une partie d'extrémité dans la direction d'envergure de l'aile du corps principal de volet (11) et servant à supprimer les tourbillons allant de la surface inférieure de la partie d'extrémité (11a) du corps principal de volet (11) à la surface supérieure de la partie d'extrémité (11a). |
| format | Patent |
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L'invention concerne un dispositif hypersustentateur (3) destiné à un aéronef, comprenant : un corps principal de volet (11) se trouvant au niveau de la partie de bord de fuite de l'aile principale (2) de l'aéronef de façon à pouvoir être déployé et logé et s'étendant le long de la direction de l'envergure de l'aile principale (2) ; et une partie de suppression de tourbillons (100, 200, 300, 400, 500, 600) se trouvant au niveau d'une partie d'extrémité dans la direction d'envergure de l'aile du corps principal de volet (11) et servant à supprimer les tourbillons allant de la surface inférieure de la partie d'extrémité (11a) du corps principal de volet (11) à la surface supérieure de la partie d'extrémité (11a).</description><language>eng ; fre</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=20160927&DB=EPODOC&CC=CA&NR=2830352C$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20160927&DB=EPODOC&CC=CA&NR=2830352C$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>HAYAMA, KENJI</creatorcontrib><creatorcontrib>ISOTANI, KAZUHIDE</creatorcontrib><title>HIGH-LIFT DEVICE OF FLIGHT VEHICLE</title><description>A high-lift device of a flight vehicle, the high-lift device comprising: a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein: the vortex suppressing portion is a flow suppressing portion formed at an upper surface side of a leading edge portion of the tip end portion of the flap main body and configured to cause a flow along the upper surface of the tip end portion of the flap main body to be separated from the upper surface; and the flow suppressing portion is a projection provided along the wing span direction and projecting upward from the upper surface of the flap main body.
L'invention concerne un dispositif hypersustentateur (3) destiné à un aéronef, comprenant : un corps principal de volet (11) se trouvant au niveau de la partie de bord de fuite de l'aile principale (2) de l'aéronef de façon à pouvoir être déployé et logé et s'étendant le long de la direction de l'envergure de l'aile principale (2) ; et une partie de suppression de tourbillons (100, 200, 300, 400, 500, 600) se trouvant au niveau d'une partie d'extrémité dans la direction d'envergure de l'aile du corps principal de volet (11) et servant à supprimer les tourbillons allant de la surface inférieure de la partie d'extrémité (11a) du corps principal de volet (11) à la surface supérieure de la partie d'extrémité (11a).</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>eNrjZFDy8HT30PXxdAtRcHEN83R2VfB3U3DzAQqGKIS5eng6-7jyMLCmJeYUp_JCaW4GeTfXEGcP3dSC_PjU4oLE5NS81JJ4Z0cjC2MDY1MjZ2PCKgCIySEc</recordid><startdate>20160927</startdate><enddate>20160927</enddate><creator>HAYAMA, KENJI</creator><creator>ISOTANI, KAZUHIDE</creator><scope>EVB</scope></search><sort><creationdate>20160927</creationdate><title>HIGH-LIFT DEVICE OF FLIGHT VEHICLE</title><author>HAYAMA, KENJI ; ISOTANI, KAZUHIDE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA2830352C3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</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>HAYAMA, KENJI</creatorcontrib><creatorcontrib>ISOTANI, KAZUHIDE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>HAYAMA, KENJI</au><au>ISOTANI, KAZUHIDE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>HIGH-LIFT DEVICE OF FLIGHT VEHICLE</title><date>2016-09-27</date><risdate>2016</risdate><abstract>A high-lift device of a flight vehicle, the high-lift device comprising: a flap main body provided at a trailing portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in an extending direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of the tip end portion of the flap main body to an upper surface of the tip end portion of the flap main body, wherein: the vortex suppressing portion is a flow suppressing portion formed at an upper surface side of a leading edge portion of the tip end portion of the flap main body and configured to cause a flow along the upper surface of the tip end portion of the flap main body to be separated from the upper surface; and the flow suppressing portion is a projection provided along the wing span direction and projecting upward from the upper surface of the flap main body.
L'invention concerne un dispositif hypersustentateur (3) destiné à un aéronef, comprenant : un corps principal de volet (11) se trouvant au niveau de la partie de bord de fuite de l'aile principale (2) de l'aéronef de façon à pouvoir être déployé et logé et s'étendant le long de la direction de l'envergure de l'aile principale (2) ; et une partie de suppression de tourbillons (100, 200, 300, 400, 500, 600) se trouvant au niveau d'une partie d'extrémité dans la direction d'envergure de l'aile du corps principal de volet (11) et servant à supprimer les tourbillons allant de la surface inférieure de la partie d'extrémité (11a) du corps principal de volet (11) à la surface supérieure de la partie d'extrémité (11a).</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre |
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| subjects | AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING |
| title | HIGH-LIFT DEVICE OF FLIGHT VEHICLE |
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