发明名称 |
Pintle injector rocket with expansion-deflection nozzle |
摘要 |
<p>The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A propellant injector (20) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end (14). A nozzle throat (18) is formed at the nozzle end (14) of the combustion chamber (12). A nozzle exit cone (22) extends outwardly from the nozzle throat (18). A plug support (30) is coupled between a nozzle plug (28) and the propellant injector (20). The nozzle plug (28) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone (22) such that the nozzle thrust coefficient is maximized for any ambient backpressure. <IMAGE></p> |
申请公布号 |
EP1243783(A1) |
申请公布日期 |
2002.09.25 |
申请号 |
EP20020005427 |
申请日期 |
2002.03.08 |
申请人 |
TRW INC. |
发明人 |
DRESSLER, GORDON A.;MUELLER, THOMAS J.;ROTENBERGER, SCOTT J. |
分类号 |
F02K9/52;F02K9/97;(IPC1-7):F02K9/52;F02K9/86;F02K9/80;F02K9/58 |
主分类号 |
F02K9/52 |
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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