AIRCRAFT ACTUATOR HYDRAULIC SYSTEM
PROBLEM TO BE SOLVED: To drive a control surface by a single actuator even when a loss or degradation in a function of an airframe side hydraulic power source and miniaturize a high output power actuator at low cost to install the actuator inside a thin wing.SOLUTION: A first actuator 14a drives the...
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| creator | FUKUI ATSUSHI TAKAGI NORIMASA |
| description | PROBLEM TO BE SOLVED: To drive a control surface by a single actuator even when a loss or degradation in a function of an airframe side hydraulic power source and miniaturize a high output power actuator at low cost to install the actuator inside a thin wing.SOLUTION: A first actuator 14a drives the control surface 103a by being operated by supply of pressure oil from a first airframe side hydraulic pump 104a of a first airframe side hydraulic power source 104. A second actuator 14b drives the control surface 103a by being operated by supply of pressure oil from a second airframe side hydraulic pump 105a of a second airframe side hydraulic power source 105. A backup hydraulic pump 18 is installed inside the wing 102a of an aircraft 100 and is provided so as to be able to supply pressure oil to the first actuator 14a when a loss or degradation in a function of at least one of the first airframe side hydraulic power source 104 and the second airframe side hydraulic power source 105 occurs. A maximum discharge pressure of the backup hydraulic pump 18 is set to be greater than maximum discharge pressures of the first airframe side hydraulic pump 104a and the second airframe side hydraulic pump 105a. |
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A second actuator 14b drives the control surface 103a by being operated by supply of pressure oil from a second airframe side hydraulic pump 105a of a second airframe side hydraulic power source 105. A backup hydraulic pump 18 is installed inside the wing 102a of an aircraft 100 and is provided so as to be able to supply pressure oil to the first actuator 14a when a loss or degradation in a function of at least one of the first airframe side hydraulic power source 104 and the second airframe side hydraulic power source 105 occurs. A maximum discharge pressure of the backup hydraulic pump 18 is set to be greater than maximum discharge pressures of the first airframe side hydraulic pump 104a and the second airframe side hydraulic pump 105a.</description><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; BLASTING ; COSMONAUTICS ; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR ; FLUID-PRESSURE ACTUATORS ; FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS ; HEATING ; HELICOPTERS ; HYDRAULICS OR PNEUMATICS IN GENERAL ; LIGHTING ; MECHANICAL ENGINEERING ; PERFORMING OPERATIONS ; SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL ; TRANSPORTING ; WEAPONS</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=20120621&DB=EPODOC&CC=JP&NR=2012116466A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20120621&DB=EPODOC&CC=JP&NR=2012116466A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>FUKUI ATSUSHI</creatorcontrib><creatorcontrib>TAKAGI NORIMASA</creatorcontrib><title>AIRCRAFT ACTUATOR HYDRAULIC SYSTEM</title><description>PROBLEM TO BE SOLVED: To drive a control surface by a single actuator even when a loss or degradation in a function of an airframe side hydraulic power source and miniaturize a high output power actuator at low cost to install the actuator inside a thin wing.SOLUTION: A first actuator 14a drives the control surface 103a by being operated by supply of pressure oil from a first airframe side hydraulic pump 104a of a first airframe side hydraulic power source 104. A second actuator 14b drives the control surface 103a by being operated by supply of pressure oil from a second airframe side hydraulic pump 105a of a second airframe side hydraulic power source 105. A backup hydraulic pump 18 is installed inside the wing 102a of an aircraft 100 and is provided so as to be able to supply pressure oil to the first actuator 14a when a loss or degradation in a function of at least one of the first airframe side hydraulic power source 104 and the second airframe side hydraulic power source 105 occurs. A maximum discharge pressure of the backup hydraulic pump 18 is set to be greater than maximum discharge pressures of the first airframe side hydraulic pump 104a and the second airframe side hydraulic pump 105a.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COSMONAUTICS</subject><subject>DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR</subject><subject>FLUID-PRESSURE ACTUATORS</subject><subject>FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>HYDRAULICS OR PNEUMATICS IN GENERAL</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>PERFORMING OPERATIONS</subject><subject>SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2012</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFBy9AxyDnJ0C1FwdA4JdQzxD1LwiHQJcgz18XRWCI4MDnH15WFgTUvMKU7lhdLcDEpuriHOHrqpBfnxqcUFicmpeakl8V4BRgaGRoaGZiZmZo7GRCkCAI7EIxA</recordid><startdate>20120621</startdate><enddate>20120621</enddate><creator>FUKUI ATSUSHI</creator><creator>TAKAGI NORIMASA</creator><scope>EVB</scope></search><sort><creationdate>20120621</creationdate><title>AIRCRAFT ACTUATOR HYDRAULIC SYSTEM</title><author>FUKUI ATSUSHI ; TAKAGI NORIMASA</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2012116466A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2012</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COSMONAUTICS</topic><topic>DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR</topic><topic>FLUID-PRESSURE ACTUATORS</topic><topic>FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>HYDRAULICS OR PNEUMATICS IN GENERAL</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>PERFORMING OPERATIONS</topic><topic>SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>FUKUI ATSUSHI</creatorcontrib><creatorcontrib>TAKAGI NORIMASA</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>FUKUI ATSUSHI</au><au>TAKAGI NORIMASA</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIRCRAFT ACTUATOR HYDRAULIC SYSTEM</title><date>2012-06-21</date><risdate>2012</risdate><abstract>PROBLEM TO BE SOLVED: To drive a control surface by a single actuator even when a loss or degradation in a function of an airframe side hydraulic power source and miniaturize a high output power actuator at low cost to install the actuator inside a thin wing.SOLUTION: A first actuator 14a drives the control surface 103a by being operated by supply of pressure oil from a first airframe side hydraulic pump 104a of a first airframe side hydraulic power source 104. A second actuator 14b drives the control surface 103a by being operated by supply of pressure oil from a second airframe side hydraulic pump 105a of a second airframe side hydraulic power source 105. A backup hydraulic pump 18 is installed inside the wing 102a of an aircraft 100 and is provided so as to be able to supply pressure oil to the first actuator 14a when a loss or degradation in a function of at least one of the first airframe side hydraulic power source 104 and the second airframe side hydraulic power source 105 occurs. A maximum discharge pressure of the backup hydraulic pump 18 is set to be greater than maximum discharge pressures of the first airframe side hydraulic pump 104a and the second airframe side hydraulic pump 105a.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| subjects | AEROPLANES AIRCRAFT AVIATION BLASTING COSMONAUTICS DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR FLUID-PRESSURE ACTUATORS FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS HEATING HELICOPTERS HYDRAULICS OR PNEUMATICS IN GENERAL LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL TRANSPORTING WEAPONS |
| title | AIRCRAFT ACTUATOR HYDRAULIC SYSTEM |
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