发明名称 |
SOLID PROPELLANT ROCKET ENGINE |
摘要 |
FIELD: engines and pumps.SUBSTANCE: rocket engine comprises a body with a nozzle block, front and rear bottoms, an insert charge burning on the outer surface and a sleeve. The cylindrical part of the sleeve is arranged with a gap relative to the body and the outer surface of the charge, and the bottom contacts with the end of the charge and the rear bottom of the engine. The circular cavity between the sleeve and the bottom is sealed at the side of the rear bottom. The sleeve is made of combustible material on the basis of polyacryamide filled by nitrocellulose at the ratio of nitrocellulose:polyacrylamide - 2?3:1. In the bottom of the sleeve there are holes to gas passage from the slot gap "charge - sleeve" to the nozzle.EFFECT: invention makes it possible to reduce effect of a thermal flow of combustion products at a rocket engine body and to increase total thrust impulse.1 dwg |
申请公布号 |
RU2498100(C1) |
申请公布日期 |
2013.11.10 |
申请号 |
RU20120124618 |
申请日期 |
2012.06.14 |
申请人 |
OTKRYTOE AKTSIONERNOE OBSHCHESTVO "NAUCHNO-ISSLEDOVATEL'SKIJ INSTITUT POLIMERNYKH MATERIALOV" |
发明人 |
MOLCHANOV VLADIMIR FEDOROVICH;KOZ'JAKOV ALEKSEJ VASIL'EVICH;IBRAGIMOV NAIL' GUMEROVICH;JUKOV JURIJ MIKHAJLOVICH;AFIATULLOV EHNSAR KHALIULLOVICH;KISLITSYN ALEKSEJ ANATOL'EVICH;NESHEV SERGEJ SERGEEVICH;VALEEV TIMUR RAISOVICH;KUTSENKO GENNADIJ VASIL'EVICH;AMARANTOV GEORGIJ NIKOLAEVICH |
分类号 |
F02K9/32 |
主分类号 |
F02K9/32 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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