METHOD OF INDICATION OF DEFLECTION OF THRUST VECTOR DIRECTION FROM SOLID-PROPELLANT ROCKET ENGINE AXIS
testing of solid-propellant rocket engines; relieving malfunction of engines. SUBSTANCE: proposed method consists in creation of stressed-strained state of intermediate bearing member, scanning and recording in transient modes of operation of solid- propellant rocket engine under adiabatic condition...
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| creator | SHUMIKHIN A.G POPOV V.L IGNAT'EV B.S MOLCHANOV V.F EHNKIN EH.A ALIKIN V.N |
| description | testing of solid-propellant rocket engines; relieving malfunction of engines. SUBSTANCE: proposed method consists in creation of stressed-strained state of intermediate bearing member, scanning and recording in transient modes of operation of solid- propellant rocket engine under adiabatic conditions of flows of thermal radiation of elements of surface of structural intermediate bearing member. Heterogeneity of recorded thermal field (thermogram) is indicative of deflection of thrust force vector from axis of solid-propellant rocket engine. When thermal field is homogeneous (there is no thermal contrast between adjacent points of surface), thrust force vector coincides with engine axis, otherwise deflection of thrust force vector from engine force takes place. It is good practice to use quick-acting infra-red imager for analysis of thermal (temperature) field. EFFECT: enhanced reliability in transient modes of engine operation. 1 dwg |
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SUBSTANCE: proposed method consists in creation of stressed-strained state of intermediate bearing member, scanning and recording in transient modes of operation of solid- propellant rocket engine under adiabatic conditions of flows of thermal radiation of elements of surface of structural intermediate bearing member. Heterogeneity of recorded thermal field (thermogram) is indicative of deflection of thrust force vector from axis of solid-propellant rocket engine. When thermal field is homogeneous (there is no thermal contrast between adjacent points of surface), thrust force vector coincides with engine axis, otherwise deflection of thrust force vector from engine force takes place. It is good practice to use quick-acting infra-red imager for analysis of thermal (temperature) field. 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SUBSTANCE: proposed method consists in creation of stressed-strained state of intermediate bearing member, scanning and recording in transient modes of operation of solid- propellant rocket engine under adiabatic conditions of flows of thermal radiation of elements of surface of structural intermediate bearing member. Heterogeneity of recorded thermal field (thermogram) is indicative of deflection of thrust force vector from axis of solid-propellant rocket engine. When thermal field is homogeneous (there is no thermal contrast between adjacent points of surface), thrust force vector coincides with engine axis, otherwise deflection of thrust force vector from engine force takes place. It is good practice to use quick-acting infra-red imager for analysis of thermal (temperature) field. EFFECT: enhanced reliability in transient modes of engine operation. 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>2002</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNirEKwkAQRNNYiPoP-wMpolhYhrs9b_FyGzYbsQtBLpVoIP4_Roi9TDG8N7POhgrVswV2QNGSKZU4fsmiC2h-pF7aRuE6GxawJMvkhCtoOJDNa-EaQyijgrC5oALGM0WE8kbNNlsN_WNKu6U3GThU4_M0vro0jf09PdO7k3ZfnOYcTXH44_IBUxA04g</recordid><startdate>20021027</startdate><enddate>20021027</enddate><creator>SHUMIKHIN A.G</creator><creator>POPOV V.L</creator><creator>IGNAT'EV B.S</creator><creator>MOLCHANOV V.F</creator><creator>EHNKIN EH.A</creator><creator>ALIKIN V.N</creator><scope>EVB</scope></search><sort><creationdate>20021027</creationdate><title>METHOD OF INDICATION OF DEFLECTION OF THRUST VECTOR DIRECTION FROM SOLID-PROPELLANT ROCKET ENGINE AXIS</title><author>SHUMIKHIN A.G ; POPOV V.L ; IGNAT'EV B.S ; MOLCHANOV V.F ; EHNKIN EH.A ; ALIKIN V.N</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_RU2191915C13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2002</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>SHUMIKHIN A.G</creatorcontrib><creatorcontrib>POPOV V.L</creatorcontrib><creatorcontrib>IGNAT'EV B.S</creatorcontrib><creatorcontrib>MOLCHANOV V.F</creatorcontrib><creatorcontrib>EHNKIN EH.A</creatorcontrib><creatorcontrib>ALIKIN V.N</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>SHUMIKHIN A.G</au><au>POPOV V.L</au><au>IGNAT'EV B.S</au><au>MOLCHANOV V.F</au><au>EHNKIN EH.A</au><au>ALIKIN V.N</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>METHOD OF INDICATION OF DEFLECTION OF THRUST VECTOR DIRECTION FROM SOLID-PROPELLANT ROCKET ENGINE AXIS</title><date>2002-10-27</date><risdate>2002</risdate><abstract>testing of solid-propellant rocket engines; relieving malfunction of engines. SUBSTANCE: proposed method consists in creation of stressed-strained state of intermediate bearing member, scanning and recording in transient modes of operation of solid- propellant rocket engine under adiabatic conditions of flows of thermal radiation of elements of surface of structural intermediate bearing member. Heterogeneity of recorded thermal field (thermogram) is indicative of deflection of thrust force vector from axis of solid-propellant rocket engine. When thermal field is homogeneous (there is no thermal contrast between adjacent points of surface), thrust force vector coincides with engine axis, otherwise deflection of thrust force vector from engine force takes place. It is good practice to use quick-acting infra-red imager for analysis of thermal (temperature) field. EFFECT: enhanced reliability in transient modes of engine operation. 1 dwg</abstract><edition>7</edition><oa>free_for_read</oa></addata></record> |
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| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | METHOD OF INDICATION OF DEFLECTION OF THRUST VECTOR DIRECTION FROM SOLID-PROPELLANT ROCKET ENGINE AXIS |
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