Yaw control device for a nozzle having a rectangular outlet section
The invention relates to a yaw control device for an aircraft fitted with a supersonic nozzle having a rectangular or flat section comprising a supersonic throat extended by a diverging portion in which supersonic flow occurs. In order to enable the aircraft to be controlled in yaw in the absence of...
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| creator | BUFFENOIR FRANCOIS LAFOND ANTOINE |
| description | The invention relates to a yaw control device for an aircraft fitted with a supersonic nozzle having a rectangular or flat section comprising a supersonic throat extended by a diverging portion in which supersonic flow occurs. In order to enable the aircraft to be controlled in yaw in the absence of a vertical fin, the device of the invention makes use of jet control surfaces in the form of airfoils disposed in the diverging portion of the nozzle. The control surfaces are movable about respective pivot axes in order to generate a lateral force when in a deflected position, so as to enable the aircraft to turn about its yaw axis.
Dispositivo de pilotaje en guiñada para aeronave equipada con una tobera supersónica de sección rectangular o aplanada, que comprende un cuello sónico prolongado por un divergente en el cual se produce el flujo supersónico. A fin de permitir el pilotaje en guiñada de la aeronave en ausencia de deriva vertical, el dispositivo de la invención utiliza unos timones de chorro en forma de alerón que están dispuestos en el divergente de la tobera. Los timones son móviles alrededor del eje de rotación para generar un esfuerzo lateral en posición girada y permitir la rotación de la aeronave alrededor de su eje de guiñada. |
| format | Patent |
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Dispositivo de pilotaje en guiñada para aeronave equipada con una tobera supersónica de sección rectangular o aplanada, que comprende un cuello sónico prolongado por un divergente en el cual se produce el flujo supersónico. A fin de permitir el pilotaje en guiñada de la aeronave en ausencia de deriva vertical, el dispositivo de la invención utiliza unos timones de chorro en forma de alerón que están dispuestos en el divergente de la tobera. Los timones son móviles alrededor del eje de rotación para generar un esfuerzo lateral en posición girada y permitir la rotación de la aeronave alrededor de su eje de guiñada.</description><language>eng ; spa</language><subject>AEROPLANES ; AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; COSMONAUTICS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; HELICOPTERS ; PARACHUTES ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2007</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=20071201&DB=EPODOC&CC=ES&NR=2286957A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20071201&DB=EPODOC&CC=ES&NR=2286957A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BUFFENOIR FRANCOIS</creatorcontrib><creatorcontrib>LAFOND ANTOINE</creatorcontrib><title>Yaw control device for a nozzle having a rectangular outlet section</title><description>The invention relates to a yaw control device for an aircraft fitted with a supersonic nozzle having a rectangular or flat section comprising a supersonic throat extended by a diverging portion in which supersonic flow occurs. In order to enable the aircraft to be controlled in yaw in the absence of a vertical fin, the device of the invention makes use of jet control surfaces in the form of airfoils disposed in the diverging portion of the nozzle. The control surfaces are movable about respective pivot axes in order to generate a lateral force when in a deflected position, so as to enable the aircraft to turn about its yaw axis.
Dispositivo de pilotaje en guiñada para aeronave equipada con una tobera supersónica de sección rectangular o aplanada, que comprende un cuello sónico prolongado por un divergente en el cual se produce el flujo supersónico. A fin de permitir el pilotaje en guiñada de la aeronave en ausencia de deriva vertical, el dispositivo de la invención utiliza unos timones de chorro en forma de alerón que están dispuestos en el divergente de la tobera. Los timones son móviles alrededor del eje de rotación para generar un esfuerzo lateral en posición girada y permitir la rotación de la aeronave alrededor de su eje de guiñada.</description><subject>AEROPLANES</subject><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>HELICOPTERS</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2007</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZHCOTCxXSM7PKynKz1FISS3LTE5VSMsvUkhUyMuvqspJVchILMvMSwfyi1KTSxLz0ktzEosU8ktLclJLFIqBQpn5eTwMrGmJOcWpvFCam0HBzTXE2UM3tSA_PrW4IDE5NS-1JN412MjIwszS1NzR0JgIJQAKdDIa</recordid><startdate>20071201</startdate><enddate>20071201</enddate><creator>BUFFENOIR FRANCOIS</creator><creator>LAFOND ANTOINE</creator><scope>EVB</scope></search><sort><creationdate>20071201</creationdate><title>Yaw control device for a nozzle having a rectangular outlet section</title><author>BUFFENOIR FRANCOIS ; LAFOND ANTOINE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_ES2286957A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; spa</language><creationdate>2007</creationdate><topic>AEROPLANES</topic><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>HELICOPTERS</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>BUFFENOIR FRANCOIS</creatorcontrib><creatorcontrib>LAFOND ANTOINE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BUFFENOIR FRANCOIS</au><au>LAFOND ANTOINE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Yaw control device for a nozzle having a rectangular outlet section</title><date>2007-12-01</date><risdate>2007</risdate><abstract>The invention relates to a yaw control device for an aircraft fitted with a supersonic nozzle having a rectangular or flat section comprising a supersonic throat extended by a diverging portion in which supersonic flow occurs. In order to enable the aircraft to be controlled in yaw in the absence of a vertical fin, the device of the invention makes use of jet control surfaces in the form of airfoils disposed in the diverging portion of the nozzle. The control surfaces are movable about respective pivot axes in order to generate a lateral force when in a deflected position, so as to enable the aircraft to turn about its yaw axis.
Dispositivo de pilotaje en guiñada para aeronave equipada con una tobera supersónica de sección rectangular o aplanada, que comprende un cuello sónico prolongado por un divergente en el cual se produce el flujo supersónico. A fin de permitir el pilotaje en guiñada de la aeronave en ausencia de deriva vertical, el dispositivo de la invención utiliza unos timones de chorro en forma de alerón que están dispuestos en el divergente de la tobera. Los timones son móviles alrededor del eje de rotación para generar un esfuerzo lateral en posición girada y permitir la rotación de la aeronave alrededor de su eje de guiñada.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HELICOPTERS PARACHUTES PERFORMING OPERATIONS TRANSPORTING |
| title | Yaw control device for a nozzle having a rectangular outlet section |
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