SOLID PROPELLANT ROCKET CHARGE
FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom pa...
Gespeichert in:
| Hauptverfasser: | , , , , , , , , , , , , , , , , , , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | VINOKUROV JU.A DENEZHKIN G.A AMARANTOV G.N KASHIRKIN A.A TREGUBOV V.I SEMILET V.V SHUBKIN E.A MAKAROV L.B TALALAEV A.P KOROLEVA N.B KUZ'MITSKIJ G.EH ROMANOVICH A.P BOZH'JA-VOLJA N.S KOLESNIKOV V.I MAKAROVETS N.A NEKRASOV V.I PODCHUFAROV V.I FEDCHENKO N.N KOLACH P.K |
| description | FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom part of charge is made with cantilever section of length equal to 0.6-1.8 e1 where e1 is mean in charge length initial thickness of burning arch. Distance between cross section of charge with at maximum ratio of burning surface to said section to area of through section o channel in said section and bottom end face of change is 0.8-0.9 L where L is length of charge. EFFECT: reliable functioning of charge made of high-energy high-elasticity propellants at simultaneous increase of specific loading density. 1 dwg |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_RU2220311C1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>RU2220311C1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_RU2220311C13</originalsourceid><addsrcrecordid>eNrjZJAL9vfxdFEICPIPcPXxcfQLUQjyd_Z2DVFw9nAMcnflYWBNS8wpTuWF0twMCm6uIc4euqkF-fGpxQWJyal5qSXxQaFGRkYGxoaGzobGRCgBAHYqIPk</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>SOLID PROPELLANT ROCKET CHARGE</title><source>esp@cenet</source><creator>VINOKUROV JU.A ; DENEZHKIN G.A ; AMARANTOV G.N ; KASHIRKIN A.A ; TREGUBOV V.I ; SEMILET V.V ; SHUBKIN E.A ; MAKAROV L.B ; TALALAEV A.P ; KOROLEVA N.B ; KUZ'MITSKIJ G.EH ; ROMANOVICH A.P ; BOZH'JA-VOLJA N.S ; KOLESNIKOV V.I ; MAKAROVETS N.A ; NEKRASOV V.I ; PODCHUFAROV V.I ; FEDCHENKO N.N ; KOLACH P.K</creator><creatorcontrib>VINOKUROV JU.A ; DENEZHKIN G.A ; AMARANTOV G.N ; KASHIRKIN A.A ; TREGUBOV V.I ; SEMILET V.V ; SHUBKIN E.A ; MAKAROV L.B ; TALALAEV A.P ; KOROLEVA N.B ; KUZ'MITSKIJ G.EH ; ROMANOVICH A.P ; BOZH'JA-VOLJA N.S ; KOLESNIKOV V.I ; MAKAROVETS N.A ; NEKRASOV V.I ; PODCHUFAROV V.I ; FEDCHENKO N.N ; KOLACH P.K</creatorcontrib><description>FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom part of charge is made with cantilever section of length equal to 0.6-1.8 e1 where e1 is mean in charge length initial thickness of burning arch. Distance between cross section of charge with at maximum ratio of burning surface to said section to area of through section o channel in said section and bottom end face of change is 0.8-0.9 L where L is length of charge. EFFECT: reliable functioning of charge made of high-energy high-elasticity propellants at simultaneous increase of specific loading density. 1 dwg</description><edition>7</edition><language>eng</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2003</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=20031227&DB=EPODOC&CC=RU&NR=2220311C1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20031227&DB=EPODOC&CC=RU&NR=2220311C1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>VINOKUROV JU.A</creatorcontrib><creatorcontrib>DENEZHKIN G.A</creatorcontrib><creatorcontrib>AMARANTOV G.N</creatorcontrib><creatorcontrib>KASHIRKIN A.A</creatorcontrib><creatorcontrib>TREGUBOV V.I</creatorcontrib><creatorcontrib>SEMILET V.V</creatorcontrib><creatorcontrib>SHUBKIN E.A</creatorcontrib><creatorcontrib>MAKAROV L.B</creatorcontrib><creatorcontrib>TALALAEV A.P</creatorcontrib><creatorcontrib>KOROLEVA N.B</creatorcontrib><creatorcontrib>KUZ'MITSKIJ G.EH</creatorcontrib><creatorcontrib>ROMANOVICH A.P</creatorcontrib><creatorcontrib>BOZH'JA-VOLJA N.S</creatorcontrib><creatorcontrib>KOLESNIKOV V.I</creatorcontrib><creatorcontrib>MAKAROVETS N.A</creatorcontrib><creatorcontrib>NEKRASOV V.I</creatorcontrib><creatorcontrib>PODCHUFAROV V.I</creatorcontrib><creatorcontrib>FEDCHENKO N.N</creatorcontrib><creatorcontrib>KOLACH P.K</creatorcontrib><title>SOLID PROPELLANT ROCKET CHARGE</title><description>FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom part of charge is made with cantilever section of length equal to 0.6-1.8 e1 where e1 is mean in charge length initial thickness of burning arch. Distance between cross section of charge with at maximum ratio of burning surface to said section to area of through section o channel in said section and bottom end face of change is 0.8-0.9 L where L is length of charge. EFFECT: reliable functioning of charge made of high-energy high-elasticity propellants at simultaneous increase of specific loading density. 1 dwg</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</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>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2003</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZJAL9vfxdFEICPIPcPXxcfQLUQjyd_Z2DVFw9nAMcnflYWBNS8wpTuWF0twMCm6uIc4euqkF-fGpxQWJyal5qSXxQaFGRkYGxoaGzobGRCgBAHYqIPk</recordid><startdate>20031227</startdate><enddate>20031227</enddate><creator>VINOKUROV JU.A</creator><creator>DENEZHKIN G.A</creator><creator>AMARANTOV G.N</creator><creator>KASHIRKIN A.A</creator><creator>TREGUBOV V.I</creator><creator>SEMILET V.V</creator><creator>SHUBKIN E.A</creator><creator>MAKAROV L.B</creator><creator>TALALAEV A.P</creator><creator>KOROLEVA N.B</creator><creator>KUZ'MITSKIJ G.EH</creator><creator>ROMANOVICH A.P</creator><creator>BOZH'JA-VOLJA N.S</creator><creator>KOLESNIKOV V.I</creator><creator>MAKAROVETS N.A</creator><creator>NEKRASOV V.I</creator><creator>PODCHUFAROV V.I</creator><creator>FEDCHENKO N.N</creator><creator>KOLACH P.K</creator><scope>EVB</scope></search><sort><creationdate>20031227</creationdate><title>SOLID PROPELLANT ROCKET CHARGE</title><author>VINOKUROV JU.A ; DENEZHKIN G.A ; AMARANTOV G.N ; KASHIRKIN A.A ; TREGUBOV V.I ; SEMILET V.V ; SHUBKIN E.A ; MAKAROV L.B ; TALALAEV A.P ; KOROLEVA N.B ; KUZ'MITSKIJ G.EH ; ROMANOVICH A.P ; BOZH'JA-VOLJA N.S ; KOLESNIKOV V.I ; MAKAROVETS N.A ; NEKRASOV V.I ; PODCHUFAROV V.I ; FEDCHENKO N.N ; KOLACH P.K</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_RU2220311C13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2003</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</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>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>VINOKUROV JU.A</creatorcontrib><creatorcontrib>DENEZHKIN G.A</creatorcontrib><creatorcontrib>AMARANTOV G.N</creatorcontrib><creatorcontrib>KASHIRKIN A.A</creatorcontrib><creatorcontrib>TREGUBOV V.I</creatorcontrib><creatorcontrib>SEMILET V.V</creatorcontrib><creatorcontrib>SHUBKIN E.A</creatorcontrib><creatorcontrib>MAKAROV L.B</creatorcontrib><creatorcontrib>TALALAEV A.P</creatorcontrib><creatorcontrib>KOROLEVA N.B</creatorcontrib><creatorcontrib>KUZ'MITSKIJ G.EH</creatorcontrib><creatorcontrib>ROMANOVICH A.P</creatorcontrib><creatorcontrib>BOZH'JA-VOLJA N.S</creatorcontrib><creatorcontrib>KOLESNIKOV V.I</creatorcontrib><creatorcontrib>MAKAROVETS N.A</creatorcontrib><creatorcontrib>NEKRASOV V.I</creatorcontrib><creatorcontrib>PODCHUFAROV V.I</creatorcontrib><creatorcontrib>FEDCHENKO N.N</creatorcontrib><creatorcontrib>KOLACH P.K</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>VINOKUROV JU.A</au><au>DENEZHKIN G.A</au><au>AMARANTOV G.N</au><au>KASHIRKIN A.A</au><au>TREGUBOV V.I</au><au>SEMILET V.V</au><au>SHUBKIN E.A</au><au>MAKAROV L.B</au><au>TALALAEV A.P</au><au>KOROLEVA N.B</au><au>KUZ'MITSKIJ G.EH</au><au>ROMANOVICH A.P</au><au>BOZH'JA-VOLJA N.S</au><au>KOLESNIKOV V.I</au><au>MAKAROVETS N.A</au><au>NEKRASOV V.I</au><au>PODCHUFAROV V.I</au><au>FEDCHENKO N.N</au><au>KOLACH P.K</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>SOLID PROPELLANT ROCKET CHARGE</title><date>2003-12-27</date><risdate>2003</risdate><abstract>FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom part of charge is made with cantilever section of length equal to 0.6-1.8 e1 where e1 is mean in charge length initial thickness of burning arch. Distance between cross section of charge with at maximum ratio of burning surface to said section to area of through section o channel in said section and bottom end face of change is 0.8-0.9 L where L is length of charge. EFFECT: reliable functioning of charge made of high-energy high-elasticity propellants at simultaneous increase of specific loading density. 1 dwg</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_RU2220311C1 |
| source | esp@cenet |
| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | SOLID PROPELLANT ROCKET CHARGE |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-26T11%3A25%3A22IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=VINOKUROV%20JU.A&rft.date=2003-12-27&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3ERU2220311C1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |