FUEL SUPPLY SYSTEM FOR HYDROGEN AIRCRAFT, AND TANK INTERNAL PRESSURE ADJUSTMENT METHOD
A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increase...
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| creator | SHIMIZU, Kazuko YASUDA, Shigenori SASAKI, Koichi TSURU, Kazunari TANAKA, Shota |
| description | A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increases a tank internal pressure being a pressure in an inner part of the fuel tank (2); a flow rate controller (71) that controls a flow rate of the liquefied hydrogen to be supplied from the fuel tank (2) to the propulsion device (102); and a pressure controller (73) that controls, on the basis of information which is about the flow rate of the liquefied hydrogen and is input from the flow rate controller (71), the pressure increasing mechanism (3) to adjust the tank internal pressure. |
| format | Patent |
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a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increases a tank internal pressure being a pressure in an inner part of the fuel tank (2); a flow rate controller (71) that controls a flow rate of the liquefied hydrogen to be supplied from the fuel tank (2) to the propulsion device (102); and a pressure controller (73) that controls, on the basis of information which is about the flow rate of the liquefied hydrogen and is input from the flow rate controller (71), the pressure increasing mechanism (3) to adjust the tank internal pressure.</description><language>eng</language><subject>AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; BLASTING ; COSMONAUTICS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES ; FIXED-CAPACITY GAS-HOLDERS ; FLYING SUITS ; HEATING ; LIGHTING ; MECHANICAL ENGINEERING ; PARACHUTES ; PERFORMING OPERATIONS ; STORING OF DISTRIBUTING GASES OR LIQUIDS ; TRANSPORTING ; VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES ; WEAPONS</subject><creationdate>2024</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=20240808&DB=EPODOC&CC=US&NR=2024263745A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240808&DB=EPODOC&CC=US&NR=2024263745A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>SHIMIZU, Kazuko</creatorcontrib><creatorcontrib>YASUDA, Shigenori</creatorcontrib><creatorcontrib>SASAKI, Koichi</creatorcontrib><creatorcontrib>TSURU, Kazunari</creatorcontrib><creatorcontrib>TANAKA, Shota</creatorcontrib><title>FUEL SUPPLY SYSTEM FOR HYDROGEN AIRCRAFT, AND TANK INTERNAL PRESSURE ADJUSTMENT METHOD</title><description>A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increases a tank internal pressure being a pressure in an inner part of the fuel tank (2); a flow rate controller (71) that controls a flow rate of the liquefied hydrogen to be supplied from the fuel tank (2) to the propulsion device (102); and a pressure controller (73) that controls, on the basis of information which is about the flow rate of the liquefied hydrogen and is input from the flow rate controller (71), the pressure increasing mechanism (3) to adjust the tank internal pressure.</description><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COSMONAUTICS</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES</subject><subject>FIXED-CAPACITY GAS-HOLDERS</subject><subject>FLYING SUITS</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>STORING OF DISTRIBUTING GASES OR LIQUIDS</subject><subject>TRANSPORTING</subject><subject>VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyrEKwjAQANAuDqL-w4GrgrZV56O52GqbhruL0KkUiZNoof4_Ln6A01vePLnZQDVI8L7uQDpRasC2DGVnuD2TA6y4YLS6AXQGFN0VKqfEDmvwTCKBCdBcgmhDTqEhLVuzTGaP4TnF1c9FsrakRbmN47uP0zjc4yt--iDpLs3TY3bKD7jP_ltfdsEx6w</recordid><startdate>20240808</startdate><enddate>20240808</enddate><creator>SHIMIZU, Kazuko</creator><creator>YASUDA, Shigenori</creator><creator>SASAKI, Koichi</creator><creator>TSURU, Kazunari</creator><creator>TANAKA, Shota</creator><scope>EVB</scope></search><sort><creationdate>20240808</creationdate><title>FUEL SUPPLY SYSTEM FOR HYDROGEN AIRCRAFT, AND TANK INTERNAL PRESSURE ADJUSTMENT METHOD</title><author>SHIMIZU, Kazuko ; YASUDA, Shigenori ; SASAKI, Koichi ; TSURU, Kazunari ; TANAKA, Shota</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2024263745A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2024</creationdate><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COSMONAUTICS</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES</topic><topic>FIXED-CAPACITY GAS-HOLDERS</topic><topic>FLYING SUITS</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>STORING OF DISTRIBUTING GASES OR LIQUIDS</topic><topic>TRANSPORTING</topic><topic>VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>SHIMIZU, Kazuko</creatorcontrib><creatorcontrib>YASUDA, Shigenori</creatorcontrib><creatorcontrib>SASAKI, Koichi</creatorcontrib><creatorcontrib>TSURU, Kazunari</creatorcontrib><creatorcontrib>TANAKA, Shota</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SHIMIZU, Kazuko</au><au>YASUDA, Shigenori</au><au>SASAKI, Koichi</au><au>TSURU, Kazunari</au><au>TANAKA, Shota</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>FUEL SUPPLY SYSTEM FOR HYDROGEN AIRCRAFT, AND TANK INTERNAL PRESSURE ADJUSTMENT METHOD</title><date>2024-08-08</date><risdate>2024</risdate><abstract>A fuel supply system (1) for a hydrogen-powered aircraft includes: a fuel tank (2) that stores liquefied hydrogen; a pump (5) that discharges the liquefied hydrogen from the fuel tank (2) to supply the liquefied hydrogen to a propulsion device (102); a pressure increasing mechanism (3) that increases a tank internal pressure being a pressure in an inner part of the fuel tank (2); a flow rate controller (71) that controls a flow rate of the liquefied hydrogen to be supplied from the fuel tank (2) to the propulsion device (102); and a pressure controller (73) that controls, on the basis of information which is about the flow rate of the liquefied hydrogen and is input from the flow rate controller (71), the pressure increasing mechanism (3) to adjust the tank internal pressure.</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 BLASTING COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES FIXED-CAPACITY GAS-HOLDERS FLYING SUITS HEATING LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS STORING OF DISTRIBUTING GASES OR LIQUIDS TRANSPORTING VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES WEAPONS |
| title | FUEL SUPPLY SYSTEM FOR HYDROGEN AIRCRAFT, AND TANK INTERNAL PRESSURE ADJUSTMENT METHOD |
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