METHOD FOR ADJUSTING PRESSURE IN FIRST PROPELLANT TANK OF ROCKET ENGINE
PROBLEM TO BE SOLVED: To simplify complex structure of an existing pressure adjustment device as well as its method of use for adjusting a pressure in a propellant tank of a rocket engine and presence of a plurality of variable hole opening valves and means for controlling them.SOLUTION: This invent...
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| creator | LE GONIDEC SERGE VALENTIN HUE |
| description | PROBLEM TO BE SOLVED: To simplify complex structure of an existing pressure adjustment device as well as its method of use for adjusting a pressure in a propellant tank of a rocket engine and presence of a plurality of variable hole opening valves and means for controlling them.SOLUTION: This invention relates to a method for adjusting a pressure in a first propellant tank of a rocket engine comprising a first propulsion tank [16] including first propellant; a second propulsion tank [18] including a second propellant and an adjustment device for adjusting a pressure in the first tank. This invention has a feature that the adjustment device comprises: a gas generator [60]; and a heat exchanger [74] for evaporating at least a part of the first propellant in cooperation with the gas generator, thereafter re-feeding it into the first tank [16], the first propellant is supplied to both the gas generator and the heat exchanger by a first motor driving pump [64], a flow rate of the first motor driving pump is controlled in response to a first parameter and a flow rate of a second motor driving pump is controlled in response to a second parameter.SELECTED DRAWING: Figure 1
【課題】ロケットエンジンの推進剤タンク内の圧力を調整する、既知の圧力調整装置は構造も使用法も複雑であり、それらには複数の可変開孔弁と共にそれらを制御する手段とが存在するが、それらを簡略化する。【解決手段】第１推進剤を含む第１推進タンク（１６）と、第２推進剤を含む第２推進タンク（１８）と、第１タンク内の圧力を調整する調整装置とを有するロケットエンジンの第１推進タンク内の圧力を調整する調整方法において、調整装置は、ガス発生機（６０）と、ガス発生機と協働して第１推進剤の少なくとも一部を蒸発させるようにした後それを第１タンク（１６）内へと再導入する熱交換機（７４）とを備え、ガス発生機と熱交換機の両方に第１推進剤が単一の第１モータ駆動ポンプ（６４）によって供給され、ガス発生機に第２推進剤が単一の第２モータ駆動ポンプによって供給され、第１モータ駆動ポンプの流量は第１パラメータに応じて制御され、第２モータ駆動ポンプの流量は第２パラメータに応じて制御されることを特徴とする、調整方法。【選択図】図１ |
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【課題】ロケットエンジンの推進剤タンク内の圧力を調整する、既知の圧力調整装置は構造も使用法も複雑であり、それらには複数の可変開孔弁と共にそれらを制御する手段とが存在するが、それらを簡略化する。【解決手段】第１推進剤を含む第１推進タンク（１６）と、第２推進剤を含む第２推進タンク（１８）と、第１タンク内の圧力を調整する調整装置とを有するロケットエンジンの第１推進タンク内の圧力を調整する調整方法において、調整装置は、ガス発生機（６０）と、ガス発生機と協働して第１推進剤の少なくとも一部を蒸発させるようにした後それを第１タンク（１６）内へと再導入する熱交換機（７４）とを備え、ガス発生機と熱交換機の両方に第１推進剤が単一の第１モータ駆動ポンプ（６４）によって供給され、ガス発生機に第２推進剤が単一の第２モータ駆動ポンプによって供給され、第１モータ駆動ポンプの流量は第１パラメータに応じて制御され、第２モータ駆動ポンプの流量は第２パラメータに応じて制御されることを特徴とする、調整方法。【選択図】図１</description><language>eng ; jpn</language><subject>AIRCRAFT ; AVIATION ; BLASTING ; COMBUSTION ENGINES ; COSMONAUTICS ; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES ; FIXED-CAPACITY GAS-HOLDERS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; PERFORMING OPERATIONS ; STORING OF DISTRIBUTING GASES OR LIQUIDS ; TRANSPORTING ; VEHICLES OR EQUIPMENT THEREFOR ; VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES ; WEAPONS</subject><creationdate>2017</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=20170525&DB=EPODOC&CC=JP&NR=2017089625A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76294</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170525&DB=EPODOC&CC=JP&NR=2017089625A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>LE GONIDEC SERGE</creatorcontrib><creatorcontrib>VALENTIN HUE</creatorcontrib><title>METHOD FOR ADJUSTING PRESSURE IN FIRST PROPELLANT TANK OF ROCKET ENGINE</title><description>PROBLEM TO BE SOLVED: To simplify complex structure of an existing pressure adjustment device as well as its method of use for adjusting a pressure in a propellant tank of a rocket engine and presence of a plurality of variable hole opening valves and means for controlling them.SOLUTION: This invention relates to a method for adjusting a pressure in a first propellant tank of a rocket engine comprising a first propulsion tank [16] including first propellant; a second propulsion tank [18] including a second propellant and an adjustment device for adjusting a pressure in the first tank. This invention has a feature that the adjustment device comprises: a gas generator [60]; and a heat exchanger [74] for evaporating at least a part of the first propellant in cooperation with the gas generator, thereafter re-feeding it into the first tank [16], the first propellant is supplied to both the gas generator and the heat exchanger by a first motor driving pump [64], a flow rate of the first motor driving pump is controlled in response to a first parameter and a flow rate of a second motor driving pump is controlled in response to a second parameter.SELECTED DRAWING: Figure 1
【課題】ロケットエンジンの推進剤タンク内の圧力を調整する、既知の圧力調整装置は構造も使用法も複雑であり、それらには複数の可変開孔弁と共にそれらを制御する手段とが存在するが、それらを簡略化する。【解決手段】第１推進剤を含む第１推進タンク（１６）と、第２推進剤を含む第２推進タンク（１８）と、第１タンク内の圧力を調整する調整装置とを有するロケットエンジンの第１推進タンク内の圧力を調整する調整方法において、調整装置は、ガス発生機（６０）と、ガス発生機と協働して第１推進剤の少なくとも一部を蒸発させるようにした後それを第１タンク（１６）内へと再導入する熱交換機（７４）とを備え、ガス発生機と熱交換機の両方に第１推進剤が単一の第１モータ駆動ポンプ（６４）によって供給され、ガス発生機に第２推進剤が単一の第２モータ駆動ポンプによって供給され、第１モータ駆動ポンプの流量は第１パラメータに応じて制御され、第２モータ駆動ポンプの流量は第２パラメータに応じて制御されることを特徴とする、調整方法。【選択図】図１</description><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>COSMONAUTICS</subject><subject>FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES</subject><subject>FIXED-CAPACITY GAS-HOLDERS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>PERFORMING OPERATIONS</subject><subject>STORING OF DISTRIBUTING GASES OR LIQUIDS</subject><subject>TRANSPORTING</subject><subject>VEHICLES OR EQUIPMENT THEREFOR</subject><subject>VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZHD3dQ3x8HdRcPMPUnB08QoNDvH0c1cICHINDg4NclXw9FNw8wwKDgGK-Ae4-vg4-oUohDj6eSv4uykE-Tt7u4YouPq5e_q58jCwpiXmFKfyQmluBiU31xBnD93Ugvz41OKCxOTUvNSSeK8AIwNDcwMLSzMjU0djohQBADw5LR0</recordid><startdate>20170525</startdate><enddate>20170525</enddate><creator>LE GONIDEC SERGE</creator><creator>VALENTIN HUE</creator><scope>EVB</scope></search><sort><creationdate>20170525</creationdate><title>METHOD FOR ADJUSTING PRESSURE IN FIRST PROPELLANT TANK OF ROCKET ENGINE</title><author>LE GONIDEC SERGE ; VALENTIN HUE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2017089625A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; jpn</language><creationdate>2017</creationdate><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>COSMONAUTICS</topic><topic>FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES</topic><topic>FIXED-CAPACITY GAS-HOLDERS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>PERFORMING OPERATIONS</topic><topic>STORING OF DISTRIBUTING GASES OR LIQUIDS</topic><topic>TRANSPORTING</topic><topic>VEHICLES OR EQUIPMENT THEREFOR</topic><topic>VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>LE GONIDEC SERGE</creatorcontrib><creatorcontrib>VALENTIN HUE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>LE GONIDEC SERGE</au><au>VALENTIN HUE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>METHOD FOR ADJUSTING PRESSURE IN FIRST PROPELLANT TANK OF ROCKET ENGINE</title><date>2017-05-25</date><risdate>2017</risdate><abstract>PROBLEM TO BE SOLVED: To simplify complex structure of an existing pressure adjustment device as well as its method of use for adjusting a pressure in a propellant tank of a rocket engine and presence of a plurality of variable hole opening valves and means for controlling them.SOLUTION: This invention relates to a method for adjusting a pressure in a first propellant tank of a rocket engine comprising a first propulsion tank [16] including first propellant; a second propulsion tank [18] including a second propellant and an adjustment device for adjusting a pressure in the first tank. This invention has a feature that the adjustment device comprises: a gas generator [60]; and a heat exchanger [74] for evaporating at least a part of the first propellant in cooperation with the gas generator, thereafter re-feeding it into the first tank [16], the first propellant is supplied to both the gas generator and the heat exchanger by a first motor driving pump [64], a flow rate of the first motor driving pump is controlled in response to a first parameter and a flow rate of a second motor driving pump is controlled in response to a second parameter.SELECTED DRAWING: Figure 1
【課題】ロケットエンジンの推進剤タンク内の圧力を調整する、既知の圧力調整装置は構造も使用法も複雑であり、それらには複数の可変開孔弁と共にそれらを制御する手段とが存在するが、それらを簡略化する。【解決手段】第１推進剤を含む第１推進タンク（１６）と、第２推進剤を含む第２推進タンク（１８）と、第１タンク内の圧力を調整する調整装置とを有するロケットエンジンの第１推進タンク内の圧力を調整する調整方法において、調整装置は、ガス発生機（６０）と、ガス発生機と協働して第１推進剤の少なくとも一部を蒸発させるようにした後それを第１タンク（１６）内へと再導入する熱交換機（７４）とを備え、ガス発生機と熱交換機の両方に第１推進剤が単一の第１モータ駆動ポンプ（６４）によって供給され、ガス発生機に第２推進剤が単一の第２モータ駆動ポンプによって供給され、第１モータ駆動ポンプの流量は第１パラメータに応じて制御され、第２モータ駆動ポンプの流量は第２パラメータに応じて制御されることを特徴とする、調整方法。【選択図】図１</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED,LIQUEFIED, OR SOLIDIFIED GASES FIXED-CAPACITY GAS-HOLDERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS STORING OF DISTRIBUTING GASES OR LIQUIDS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED ORSOLIDIFIED GASES WEAPONS |
| title | METHOD FOR ADJUSTING PRESSURE IN FIRST PROPELLANT TANK OF ROCKET ENGINE |
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