发明名称 |
SOLID-PROPELLANT ROCKET ENGINE |
摘要 |
FIELD: rocketry. SUBSTANCE: rocket engine has charge armored over outer surface and mounted in combustion chamber at circular clearance and seal forming stagnant zone which is gas-dynamically communicated with combustion chamber. Cross-section area of circular clearance increases towards seal. Cross section area at circular clearance inlet ((F<SB>in</SB>)) is found from relationship F<SB>in</SB>>F<SB>cr</SB> where F<SB>cr</SB> is area of engine critical section. Construction of engine ensures avoidance of burn-out and carrying armor coat from charge. EFFECT: enhanced reliability and efficiency; reduced thickness of armor coat and heat insulation of inner surface of combustion chamber; reduced smoking at initial section of engine operation; increased coefficient of filling combustion chamber with charge. 1 dwg
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申请公布号 |
RU2138670(C1) |
申请公布日期 |
1999.09.27 |
申请号 |
RU19970121660 |
申请日期 |
1997.12.30 |
申请人 |
KONSTRUKTORSKOE BJURO PRIBOROSTROENIJA |
发明人 |
ANDREEV V.A.;GLUKHAREV N.N.;KORNEICHEV V.V.;PALAJCHEV A.A. |
分类号 |
F02K9/08;(IPC1-7):F02K9/08 |
主分类号 |
F02K9/08 |
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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