REACTIVE CONTROL SYSTEM BASED ON ROCKET MICRO MOTORS WITH HYBRID FUEL, WITH TILTING NOZZLES

The invention relates to a reactive control system based on rocket micro motors with hybrid fuel, with tilting nozzles, intended to be used in a suborbital launcher for testing. According to the invention, the reactive control system comprises an oxidizer tank (1), the solid fuel rod with frontal co...

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Hauptverfasser:	CHELARU ADRIAN, CHELARU TEODOR-VIOREL, RĂDULESCU MARIUS TITUS, ENACHE VASILE, DUMITRU GABRIEL, ENACHE CRISTIAN, COMAN FLORENTINA
Format:	Patent
Sprache:	eng ; rum
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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creator	CHELARU ADRIAN CHELARU TEODOR-VIOREL RĂDULESCU MARIUS TITUS ENACHE VASILE DUMITRU GABRIEL ENACHE CRISTIAN COMAN FLORENTINA
description	The invention relates to a reactive control system based on rocket micro motors with hybrid fuel, with tilting nozzles, intended to be used in a suborbital launcher for testing. According to the invention, the reactive control system comprises an oxidizer tank (1), the solid fuel rod with frontal combustion, it has an external shielding (2), a primary nozzle (3) for combustion gases, supplementary oxidizer injectors (4), a combustion chamber (5), four secondary tilting nozzles (6) with independent control surface deflection, so as to ensure the control of the suborbital testing launcher attitude. Invenţia se referă la un sistem de control reactiv, bazat pe micromotoare rachetă cu combustibil hibrid, cu ajutaje basculante, utilizat pentru un lansator suborbital de testare. Sistemul de control reactiv, conform invenţiei, este format dintr-un rezervor (1) de oxidant, batonul de combustibil solid, cu ardere frontală, are un blindaj (2) la exterior, un ajutaj (3) primar pentru gazele de ardere, injectoare de oxidant (4) suplimentar, o cameră (5) de ardere, patru ajutaje (6) secundare basculante, cu bracaj independent, astfel încât să asigure controlul altitudinii lansatorului suborbital de testare.
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According to the invention, the reactive control system comprises an oxidizer tank (1), the solid fuel rod with frontal combustion, it has an external shielding (2), a primary nozzle (3) for combustion gases, supplementary oxidizer injectors (4), a combustion chamber (5), four secondary tilting nozzles (6) with independent control surface deflection, so as to ensure the control of the suborbital testing launcher attitude. Invenţia se referă la un sistem de control reactiv, bazat pe micromotoare rachetă cu combustibil hibrid, cu ajutaje basculante, utilizat pentru un lansator suborbital de testare. Sistemul de control reactiv, conform invenţiei, este format dintr-un rezervor (1) de oxidant, batonul de combustibil solid, cu ardere frontală, are un blindaj (2) la exterior, un ajutaj (3) primar pentru gazele de ardere, injectoare de oxidant (4) suplimentar, o cameră (5) de ardere, patru ajutaje (6) secundare basculante, cu bracaj independent, astfel încât să asigure controlul altitudinii lansatorului suborbital de testare.</description><language>eng ; rum</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2016</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=20160530&DB=EPODOC&CC=RO&NR=131134A2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20160530&DB=EPODOC&CC=RO&NR=131134A2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>CHELARU ADRIAN</creatorcontrib><creatorcontrib>CHELARU TEODOR-VIOREL</creatorcontrib><creatorcontrib>RĂDULESCU MARIUS TITUS</creatorcontrib><creatorcontrib>ENACHE VASILE</creatorcontrib><creatorcontrib>DUMITRU GABRIEL</creatorcontrib><creatorcontrib>ENACHE CRISTIAN</creatorcontrib><creatorcontrib>COMAN FLORENTINA</creatorcontrib><title>REACTIVE CONTROL SYSTEM BASED ON ROCKET MICRO MOTORS WITH HYBRID FUEL, WITH TILTING NOZZLES</title><description>The invention relates to a reactive control system based on rocket micro motors with hybrid fuel, with tilting nozzles, intended to be used in a suborbital launcher for testing. 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According to the invention, the reactive control system comprises an oxidizer tank (1), the solid fuel rod with frontal combustion, it has an external shielding (2), a primary nozzle (3) for combustion gases, supplementary oxidizer injectors (4), a combustion chamber (5), four secondary tilting nozzles (6) with independent control surface deflection, so as to ensure the control of the suborbital testing launcher attitude. Invenţia se referă la un sistem de control reactiv, bazat pe micromotoare rachetă cu combustibil hibrid, cu ajutaje basculante, utilizat pentru un lansator suborbital de testare. Sistemul de control reactiv, conform invenţiei, este format dintr-un rezervor (1) de oxidant, batonul de combustibil solid, cu ardere frontală, are un blindaj (2) la exterior, un ajutaj (3) primar pentru gazele de ardere, injectoare de oxidant (4) suplimentar, o cameră (5) de ardere, patru ajutaje (6) secundare basculante, cu bracaj independent, astfel încât să asigure controlul altitudinii lansatorului suborbital de testare.</abstract><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	REACTIVE CONTROL SYSTEM BASED ON ROCKET MICRO MOTORS WITH HYBRID FUEL, WITH TILTING NOZZLES
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