SUPPORT PYLON FOR AIRCRAFT ENGINES
Support pylon (19) for aircraft engines joined to a section of the fuselage (17) that has a curved closed cross-section including a skin (31) and a plurality of frames (33); its structural configuration comprising a central box (41) inside the fuselage and two external lateral boxes (51, 61) on both...
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| creator | FOLCH CORTES, DIEGO SANZ MARTINEZ, PABLO TIMOTEO |
| description | Support pylon (19) for aircraft engines joined to a section of the fuselage (17) that has a curved closed cross-section including a skin (31) and a plurality of frames (33); its structural configuration comprising a central box (41) inside the fuselage and two external lateral boxes (51, 61) on both sides of it, all of which are made of composite material, the three boxes (41, 51, 61) being structured as multi-spar boxes with upper and lower skins (43, 45; 53, 55; 63, 65), lateral spars (47, 49; 57, 59, 67, 69) and at least one central spar (48, 58; 68); having an entirely continuous interface between the central box (41) and the skin (31) of the fuselage; being joined to the fuselage (17) maintaining total continuity in the skin (31) of the fuselage and full load transfer between any frame interrupted (33') where it reaches the central box (41).
Pilón (19) de soporte de motores de aeronaves unido a una sección del fuselaje (17) que tiene una sección transversal cerrada de una forma curva comprendiendo un revestimiento (31 ) y una pluralidad de cuadernas (33); comprendiendo su configuración estructural un cajón central (41 ) dentro del fuselaje y dos cajones laterales externos (51, 61 ) a sus dos lados, todos ellos hechos con material compuesto, estando estructurados los tres cajones (41, 51, 61 ) como cajones multi-larguero con revestimientos superiores e inferiores (43, 45; 53, 55; 63, 65), largueros laterales (47, 49; 57, 59, 67, 69) y al menos un larguero central (48, 58; 68); teniendo una interfaz plenamente continua entre el cajón central (41 ) y el revestimiento (31 ) del fuselaje; estando unido al fuselaje (17) manteniendo una plena continuidad en el revestimiento (31 ) del fuselaje y una plena transferencia de cargas entre cualquier cuaderna interrumpida (33') al alcanzar el cajón central (41 ).
La présente invention concerne une structure (19) de support pour moteurs d'aéronefs reliée à une section du fuselage (17) qui présente une section transversale fermée de forme courbe comprenant un revêtement (31 ) et une pluralité de couples de fuselage (33); la configuration structurale de la structure comportant un caisson central (41) à l'intérieur du fuselage et deux caissons latéraux extérieurs (51, 61) sur ses deux côtés, tous faits de matériau composite, les trois caissons (41, 51, 61 ) étant structurés comme des caissons multilongerons avec revêtements supérieurs et inférieurs (43, 45; 53, 55; 63, 65), longerons latéraux (47, 49; 57, 59, 67, 69) e |
| format | Patent |
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Pilón (19) de soporte de motores de aeronaves unido a una sección del fuselaje (17) que tiene una sección transversal cerrada de una forma curva comprendiendo un revestimiento (31 ) y una pluralidad de cuadernas (33); comprendiendo su configuración estructural un cajón central (41 ) dentro del fuselaje y dos cajones laterales externos (51, 61 ) a sus dos lados, todos ellos hechos con material compuesto, estando estructurados los tres cajones (41, 51, 61 ) como cajones multi-larguero con revestimientos superiores e inferiores (43, 45; 53, 55; 63, 65), largueros laterales (47, 49; 57, 59, 67, 69) y al menos un larguero central (48, 58; 68); teniendo una interfaz plenamente continua entre el cajón central (41 ) y el revestimiento (31 ) del fuselaje; estando unido al fuselaje (17) manteniendo una plena continuidad en el revestimiento (31 ) del fuselaje y una plena transferencia de cargas entre cualquier cuaderna interrumpida (33') al alcanzar el cajón central (41 ).
La présente invention concerne une structure (19) de support pour moteurs d'aéronefs reliée à une section du fuselage (17) qui présente une section transversale fermée de forme courbe comprenant un revêtement (31 ) et une pluralité de couples de fuselage (33); la configuration structurale de la structure comportant un caisson central (41) à l'intérieur du fuselage et deux caissons latéraux extérieurs (51, 61) sur ses deux côtés, tous faits de matériau composite, les trois caissons (41, 51, 61 ) étant structurés comme des caissons multilongerons avec revêtements supérieurs et inférieurs (43, 45; 53, 55; 63, 65), longerons latéraux (47, 49; 57, 59, 67, 69) et au moins un longeron central (48, 58; 68); une interface entièrement continue existant entre le caisson central (41 ) et le revêtement (31 ) du fuselage. La structure est reliée au fuselage (17) de façon à assurer une totale continuité au niveau du revêtement (31 ) du fuselage et un total transfert des charges entre n'importe quel couple de fuselage discontinu (33') à la jonction avec le caisson central (41).</description><language>eng ; fre ; spa</language><subject>AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; COSMONAUTICS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; PARACHUTES ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2012</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=20120628&DB=EPODOC&CC=WO&NR=2011086221A3$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20120628&DB=EPODOC&CC=WO&NR=2011086221A3$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>FOLCH CORTES, DIEGO</creatorcontrib><creatorcontrib>SANZ MARTINEZ, PABLO TIMOTEO</creatorcontrib><title>SUPPORT PYLON FOR AIRCRAFT ENGINES</title><description>Support pylon (19) for aircraft engines joined to a section of the fuselage (17) that has a curved closed cross-section including a skin (31) and a plurality of frames (33); its structural configuration comprising a central box (41) inside the fuselage and two external lateral boxes (51, 61) on both sides of it, all of which are made of composite material, the three boxes (41, 51, 61) being structured as multi-spar boxes with upper and lower skins (43, 45; 53, 55; 63, 65), lateral spars (47, 49; 57, 59, 67, 69) and at least one central spar (48, 58; 68); having an entirely continuous interface between the central box (41) and the skin (31) of the fuselage; being joined to the fuselage (17) maintaining total continuity in the skin (31) of the fuselage and full load transfer between any frame interrupted (33') where it reaches the central box (41).
Pilón (19) de soporte de motores de aeronaves unido a una sección del fuselaje (17) que tiene una sección transversal cerrada de una forma curva comprendiendo un revestimiento (31 ) y una pluralidad de cuadernas (33); comprendiendo su configuración estructural un cajón central (41 ) dentro del fuselaje y dos cajones laterales externos (51, 61 ) a sus dos lados, todos ellos hechos con material compuesto, estando estructurados los tres cajones (41, 51, 61 ) como cajones multi-larguero con revestimientos superiores e inferiores (43, 45; 53, 55; 63, 65), largueros laterales (47, 49; 57, 59, 67, 69) y al menos un larguero central (48, 58; 68); teniendo una interfaz plenamente continua entre el cajón central (41 ) y el revestimiento (31 ) del fuselaje; estando unido al fuselaje (17) manteniendo una plena continuidad en el revestimiento (31 ) del fuselaje y una plena transferencia de cargas entre cualquier cuaderna interrumpida (33') al alcanzar el cajón central (41 ).
La présente invention concerne une structure (19) de support pour moteurs d'aéronefs reliée à une section du fuselage (17) qui présente une section transversale fermée de forme courbe comprenant un revêtement (31 ) et une pluralité de couples de fuselage (33); la configuration structurale de la structure comportant un caisson central (41) à l'intérieur du fuselage et deux caissons latéraux extérieurs (51, 61) sur ses deux côtés, tous faits de matériau composite, les trois caissons (41, 51, 61 ) étant structurés comme des caissons multilongerons avec revêtements supérieurs et inférieurs (43, 45; 53, 55; 63, 65), longerons latéraux (47, 49; 57, 59, 67, 69) et au moins un longeron central (48, 58; 68); une interface entièrement continue existant entre le caisson central (41 ) et le revêtement (31 ) du fuselage. La structure est reliée au fuselage (17) de façon à assurer une totale continuité au niveau du revêtement (31 ) du fuselage et un total transfert des charges entre n'importe quel couple de fuselage discontinu (33') à la jonction avec le caisson central (41).</description><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>COSMONAUTICS</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2012</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFAKDg0I8A8KUQiI9PH3U3DzD1Jw9AxyDnJ0C1Fw9XP39HMN5mFgTUvMKU7lhdLcDMpuriHOHrqpBfnxqcUFicmpeakl8eH-RgaGhgYWZkZGho7GxsSpAgDT-CN2</recordid><startdate>20120628</startdate><enddate>20120628</enddate><creator>FOLCH CORTES, DIEGO</creator><creator>SANZ MARTINEZ, PABLO TIMOTEO</creator><scope>EVB</scope></search><sort><creationdate>20120628</creationdate><title>SUPPORT PYLON FOR AIRCRAFT ENGINES</title><author>FOLCH CORTES, DIEGO ; SANZ MARTINEZ, PABLO TIMOTEO</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_WO2011086221A33</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; spa</language><creationdate>2012</creationdate><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>COSMONAUTICS</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>FOLCH CORTES, DIEGO</creatorcontrib><creatorcontrib>SANZ MARTINEZ, PABLO TIMOTEO</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>FOLCH CORTES, DIEGO</au><au>SANZ MARTINEZ, PABLO TIMOTEO</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>SUPPORT PYLON FOR AIRCRAFT ENGINES</title><date>2012-06-28</date><risdate>2012</risdate><abstract>Support pylon (19) for aircraft engines joined to a section of the fuselage (17) that has a curved closed cross-section including a skin (31) and a plurality of frames (33); its structural configuration comprising a central box (41) inside the fuselage and two external lateral boxes (51, 61) on both sides of it, all of which are made of composite material, the three boxes (41, 51, 61) being structured as multi-spar boxes with upper and lower skins (43, 45; 53, 55; 63, 65), lateral spars (47, 49; 57, 59, 67, 69) and at least one central spar (48, 58; 68); having an entirely continuous interface between the central box (41) and the skin (31) of the fuselage; being joined to the fuselage (17) maintaining total continuity in the skin (31) of the fuselage and full load transfer between any frame interrupted (33') where it reaches the central box (41).
Pilón (19) de soporte de motores de aeronaves unido a una sección del fuselaje (17) que tiene una sección transversal cerrada de una forma curva comprendiendo un revestimiento (31 ) y una pluralidad de cuadernas (33); comprendiendo su configuración estructural un cajón central (41 ) dentro del fuselaje y dos cajones laterales externos (51, 61 ) a sus dos lados, todos ellos hechos con material compuesto, estando estructurados los tres cajones (41, 51, 61 ) como cajones multi-larguero con revestimientos superiores e inferiores (43, 45; 53, 55; 63, 65), largueros laterales (47, 49; 57, 59, 67, 69) y al menos un larguero central (48, 58; 68); teniendo una interfaz plenamente continua entre el cajón central (41 ) y el revestimiento (31 ) del fuselaje; estando unido al fuselaje (17) manteniendo una plena continuidad en el revestimiento (31 ) del fuselaje y una plena transferencia de cargas entre cualquier cuaderna interrumpida (33') al alcanzar el cajón central (41 ).
La présente invention concerne une structure (19) de support pour moteurs d'aéronefs reliée à une section du fuselage (17) qui présente une section transversale fermée de forme courbe comprenant un revêtement (31 ) et une pluralité de couples de fuselage (33); la configuration structurale de la structure comportant un caisson central (41) à l'intérieur du fuselage et deux caissons latéraux extérieurs (51, 61) sur ses deux côtés, tous faits de matériau composite, les trois caissons (41, 51, 61 ) étant structurés comme des caissons multilongerons avec revêtements supérieurs et inférieurs (43, 45; 53, 55; 63, 65), longerons latéraux (47, 49; 57, 59, 67, 69) et au moins un longeron central (48, 58; 68); une interface entièrement continue existant entre le caisson central (41 ) et le revêtement (31 ) du fuselage. La structure est reliée au fuselage (17) de façon à assurer une totale continuité au niveau du revêtement (31 ) du fuselage et un total transfert des charges entre n'importe quel couple de fuselage discontinu (33') à la jonction avec le caisson central (41).</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS PARACHUTES PERFORMING OPERATIONS TRANSPORTING |
| title | SUPPORT PYLON FOR AIRCRAFT ENGINES |
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