发明名称 |
SOLID PROPELLANT ROCKET ENGINE |
摘要 |
FIELD: aircraft engineering; rocket manufacturing. SUBSTANCE: engine has nozzle diaphragm formed by set of equidistant thin-walled cups with flange made of foil. Height of cup flange is equal to value protected by invention. Longitudinal zigzag corrugations are uniformly spaced over circumference of cup flange and antiadhesion layers are placed between cup bottoms. Design of engine provides reliable division of diaphragm into small mass parts of high sailing capacity. EFFECT: provision of safe starting of rockets from aircraft guides. 2 dwg
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申请公布号 |
RU2135812(C1) |
申请公布日期 |
1999.08.27 |
申请号 |
RU19970120199 |
申请日期 |
1997.11.25 |
申请人 |
KONSTRUKTORSKOE BJURO PRIBOROSTROENIJA |
发明人 |
SURNACHEV A.F.;SOKOLOV G.F.;MOROZOV V.D.;FILIMONOV G.D.;MAKHONIN V.V. |
分类号 |
F02K9/95;(IPC1-7):F02K9/95 |
主分类号 |
F02K9/95 |
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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