发明名称 |
Slow cook off rocket igniter |
摘要 |
A gas generating propulsion system includes an igniter containing an igniter propellant and an auto igniter. A rocket motor is coupled to the igniter and has a housing containing a main propellant, a rocket motor throat and a nozzle. A release port extends through a portion of the rocket motor. This gas release port has a variable diameter through bore in fluid communication with the main propellant. In this way, the through bore has a variable area that forms an unobstructed open area with a cross-section effective to discharge gas generated by the main propellant such that a pressure increase within the housing remains below a safety value for the housing.
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申请公布号 |
US2009044716(A1) |
申请公布日期 |
2009.02.19 |
申请号 |
US20080148027 |
申请日期 |
2008.04.16 |
申请人 |
AEROJET-GENERAL CORPORATION, A CORPORATION OF THESTATE OF OHIO |
发明人 |
FRIEDLANDER, III MARK P.;BLACK, III ROBERT E.;VENARCHICK JULIA |
分类号 |
F02K9/95;F42B15/10 |
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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