HYBRID ROCKET PROPULSION SYSTEM INCLUDING ARRAY OF HYBRID OR FLUID ATTITUDE-CONTROL ROCKET ENGINES
This propulsion system of a rocket motor assembly includes an array of attitude-control rocket engines, one or more oxidizer-fluid sources, one or more ignition-fluid sources, and, optionally, one or more primary rocket engines. Each of the attitude-control rocket engines has a respective combustion...
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| creator | HAMKE, ROLF, E ROHRBAUGH, ERIC, M |
| description | This propulsion system of a rocket motor assembly includes an array of attitude-control rocket engines, one or more oxidizer-fluid sources, one or more ignition-fluid sources, and, optionally, one or more primary rocket engines. Each of the attitude-control rocket engines has a respective combustion chamber and is offset from the longitudinal axis of the rocket motor assembly so that when a selected one or group of the attitude-control rocket engines is fired, the flight path of the assembly is diverted and/or the rocket assembly spins. The oxidizer-fluid and ignition-fluid sources are in operative communication with the attitude-control rocket engines to respectively permit oxidizer fluid and ignition fluid to be supplied to selected ones or groups of the attitude-control rocket engines. Optionally, a portion of the ignition fluid from the ignition-fluid source can be cooled and used to pressurize the oxidizer-fluid source. |
| format | Patent |
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Each of the attitude-control rocket engines has a respective combustion chamber and is offset from the longitudinal axis of the rocket motor assembly so that when a selected one or group of the attitude-control rocket engines is fired, the flight path of the assembly is diverted and/or the rocket assembly spins. The oxidizer-fluid and ignition-fluid sources are in operative communication with the attitude-control rocket engines to respectively permit oxidizer fluid and ignition fluid to be supplied to selected ones or groups of the attitude-control rocket engines. 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Each of the attitude-control rocket engines has a respective combustion chamber and is offset from the longitudinal axis of the rocket motor assembly so that when a selected one or group of the attitude-control rocket engines is fired, the flight path of the assembly is diverted and/or the rocket assembly spins. The oxidizer-fluid and ignition-fluid sources are in operative communication with the attitude-control rocket engines to respectively permit oxidizer fluid and ignition fluid to be supplied to selected ones or groups of the attitude-control rocket engines. Optionally, a portion of the ignition fluid from the ignition-fluid source can be cooled and used to pressurize the oxidizer-fluid source.</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>eNqNjLEOgjAURbs4GPUf3g8wEBJ0hfKAxtrXvL4OTARNnYyS4P9HB9yd7hnOuVt17YeaTQNM-owCnslHGww5CEMQvIBx2sbGuA4q5moAamFNiKG18QuViJHYYKbJCZP9naHrjMOwV5v79FjSYd2dghZF91maX2Na5umWnuk9os_zY1GWpzov_lA-wQw0CA</recordid><startdate>20030924</startdate><enddate>20030924</enddate><creator>HAMKE, ROLF, E</creator><creator>ROHRBAUGH, ERIC, M</creator><scope>EVB</scope></search><sort><creationdate>20030924</creationdate><title>HYBRID ROCKET PROPULSION SYSTEM INCLUDING ARRAY OF HYBRID OR FLUID ATTITUDE-CONTROL ROCKET ENGINES</title><author>HAMKE, ROLF, E ; ROHRBAUGH, ERIC, M</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP1173668B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</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>HAMKE, ROLF, E</creatorcontrib><creatorcontrib>ROHRBAUGH, ERIC, M</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>HAMKE, ROLF, E</au><au>ROHRBAUGH, ERIC, M</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>HYBRID ROCKET PROPULSION SYSTEM INCLUDING ARRAY OF HYBRID OR FLUID ATTITUDE-CONTROL ROCKET ENGINES</title><date>2003-09-24</date><risdate>2003</risdate><abstract>This propulsion system of a rocket motor assembly includes an array of attitude-control rocket engines, one or more oxidizer-fluid sources, one or more ignition-fluid sources, and, optionally, one or more primary rocket engines. Each of the attitude-control rocket engines has a respective combustion chamber and is offset from the longitudinal axis of the rocket motor assembly so that when a selected one or group of the attitude-control rocket engines is fired, the flight path of the assembly is diverted and/or the rocket assembly spins. The oxidizer-fluid and ignition-fluid sources are in operative communication with the attitude-control rocket engines to respectively permit oxidizer fluid and ignition fluid to be supplied to selected ones or groups of the attitude-control rocket engines. Optionally, a portion of the ignition fluid from the ignition-fluid source can be cooled and used to pressurize the oxidizer-fluid source.</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | HYBRID ROCKET PROPULSION SYSTEM INCLUDING ARRAY OF HYBRID OR FLUID ATTITUDE-CONTROL ROCKET ENGINES |
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