Multi-pulse solid rocket motor ignition method
A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber contain...
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| creator | McNeil, Isaiah M Copeland, Curtis S Pinello-Benavides, Jacob A Langhenry, Mark T Kadlec, Paul Brunacini, Lauren E Koehler, Frederick B |
| description | A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged. |
| format | Patent |
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The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.</description><language>eng</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2022</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=20221129&DB=EPODOC&CC=US&NR=11512668B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20221129&DB=EPODOC&CC=US&NR=11512668B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>McNeil, Isaiah M</creatorcontrib><creatorcontrib>Copeland, Curtis S</creatorcontrib><creatorcontrib>Pinello-Benavides, Jacob A</creatorcontrib><creatorcontrib>Langhenry, Mark T</creatorcontrib><creatorcontrib>Kadlec, Paul</creatorcontrib><creatorcontrib>Brunacini, Lauren E</creatorcontrib><creatorcontrib>Koehler, Frederick B</creatorcontrib><title>Multi-pulse solid rocket motor ignition method</title><description>A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.</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>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNDzLc0pydQtKM0pTlUozs_JTFEoyk_OTi1RyM0vyS9SyEzPyyzJzM9TyE0tychP4WFgTUsEKuWF0twMim6uIc4euqkF-fGpxQWJyal5qSXxocGGhqaGRmZmFk5GxsSoAQAbpir8</recordid><startdate>20221129</startdate><enddate>20221129</enddate><creator>McNeil, Isaiah M</creator><creator>Copeland, Curtis S</creator><creator>Pinello-Benavides, Jacob A</creator><creator>Langhenry, Mark T</creator><creator>Kadlec, Paul</creator><creator>Brunacini, Lauren E</creator><creator>Koehler, Frederick B</creator><scope>EVB</scope></search><sort><creationdate>20221129</creationdate><title>Multi-pulse solid rocket motor ignition method</title><author>McNeil, Isaiah M ; Copeland, Curtis S ; Pinello-Benavides, Jacob A ; Langhenry, Mark T ; Kadlec, Paul ; Brunacini, Lauren E ; Koehler, Frederick B</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US11512668B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2022</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>McNeil, Isaiah M</creatorcontrib><creatorcontrib>Copeland, Curtis S</creatorcontrib><creatorcontrib>Pinello-Benavides, Jacob A</creatorcontrib><creatorcontrib>Langhenry, Mark T</creatorcontrib><creatorcontrib>Kadlec, Paul</creatorcontrib><creatorcontrib>Brunacini, Lauren E</creatorcontrib><creatorcontrib>Koehler, Frederick B</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>McNeil, Isaiah M</au><au>Copeland, Curtis S</au><au>Pinello-Benavides, Jacob A</au><au>Langhenry, Mark T</au><au>Kadlec, Paul</au><au>Brunacini, Lauren E</au><au>Koehler, Frederick B</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Multi-pulse solid rocket motor ignition method</title><date>2022-11-29</date><risdate>2022</risdate><abstract>A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
| recordid | cdi_epo_espacenet_US11512668B2 |
| source | esp@cenet |
| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Multi-pulse solid rocket motor ignition method |
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