发明名称 |
Gaseous secondary injection thrust vector control device |
摘要 |
Apparatus for modulating the thrust vector of a rocket motor by injecting hot gas into the divergent section of the rocket nozzle and modulating injection of the hot gas by varying the flow from a solid propellant gas generator by controlling its flow rate with a vortex throttling valve arrangement.
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申请公布号 |
US4686824(A) |
申请公布日期 |
1987.08.18 |
申请号 |
US19820362017 |
申请日期 |
1982.03.25 |
申请人 |
UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE ARMY |
发明人 |
DUNAWAY, J. C.;JACOBS, PAUL L. |
分类号 |
F02K9/82;(IPC1-7):F02K1/00;F02K1/28 |
主分类号 |
F02K9/82 |
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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