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公开(公告)号：US20230407818A1
公开(公告)日：2023-12-21
申请号：US18132257
申请日：2023-04-07
发明人： Seung gyo JANG , Joo Young JIN
IPC分类号： F02K9/38
CPC分类号： F02K9/38 , F05D2260/99
摘要： Provided is a safety ignition device applied to a dual pulse motor, and by installing the safety ignition device in front of a combustion tube, accidental ignition of an ignition device or a propulsion engine may be prevented and reliability of ignition may increase, while space is efficiently used.
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公开(公告)号：US20190195171A1
公开(公告)日：2019-06-27
申请号：US16328752
申请日：2017-08-23
申请人： ARIANEGROUP SAS
发明人： Alain PYRE , Gérard ROZ
摘要： A rocket engine benefiting from better behavior during its starting stage, the rocket engine (1) including a diverging section (13) and a lashing system (40) configured to hold the diverging section (13) while starting the rocket engine (1), the lashing system (40) comprising: a plurality of radial cables (42) connected at respective first ends to a plurality of points of the diverging section (13), and a peripheral cable (41) connected to the second ends of the radial cables (42) and configured to co-operate with attachment points (43) of a launch platform (3).
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公开(公告)号：US20170191450A1
公开(公告)日：2017-07-06
申请号：US15129396
申请日：2015-04-02
申请人： AVIO S.P.A.
发明人： Paolo Bellomi , Vincenzo Mancini
CPC分类号： F02K9/36 , F02K7/105 , F02K9/10 , F02K9/26 , F02K9/32 , F02K9/34 , F02K9/343 , F02K9/38 , F02K9/86 , F05D2220/80 , F05D2250/411 , F05D2260/30 , F05D2300/501
摘要： A solid propellant rocket motor (1) has a tubular casing (3) accommodating a mass (5) of solid propellant material and at least one opening (10) for the space in the casing (3) to communicate with the outside closed by a closing head (11); the closing head (11) being coupled to the casing (3) by means of one or the other of two blocking portions (28) (21A) with different strength both carried by a movement device (21,35) which can be elastically deformed and operated from the outside.
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公开(公告)号：US20150241189A1
公开(公告)日：2015-08-27
申请号：US13799589
申请日：2013-03-13
CPC分类号： F42C11/065 , F02K9/08 , F02K9/38 , F02K9/95 , F42B15/00 , F42B15/36 , F42C11/02 , F42C11/06 , F42C15/24
摘要： A solid state ignition safety device for rocket assisted projectiles having a piezoelectric generator that charges a capacitor during the initial acceleration of the projectile by the launching propellant charge. The capacitor is then discharged after a delay to ignite an initiator, which ignites the rocket motor of the projectile. A time delay circuit can be integrated into the ignition safety device to further delay the ignition of the initiator until the projectile has reached the ideal point in its trajectory to ignite the rocket motor.
摘要翻译： 一种用于火箭辅助射弹的固态点火安全装置，具有压电发生器，其通过发射推进剂装料在弹丸的初始加速期间对电容器充电。 电容器然后在延迟之后放电以点燃发射器，其引燃射弹的火箭发动机。 时间延迟电路可以集成到点火安全装置中，以进一步延迟起动器的点火，直到弹丸到达其轨迹中的理想点以点燃火箭发动机。
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公开(公告)号：US20140102109A1
公开(公告)日：2014-04-17
申请号：US13864643
申请日：2013-04-17
申请人： Byeong Yeol PARK , Song Hoe KOO , Ji Chang YOO , Young Dae DOH
发明人： Byeong Yeol PARK , Song Hoe KOO , Ji Chang YOO , Young Dae DOH
IPC分类号： F02K9/97
摘要： Disclosed is a propulsion system and a rocket having the same. The propulsion system includes: a combustion tube having a propellant therein; a nozzle installed at a rear end of the combustion tube, and configured to discharge combustion gas generated when the propellant is ignited; and a nozzle separation unit coupled to the combustion tube and the nozzle, respectively, and configured to mount the nozzle to the combustion tube, and configured to separate the nozzle from the combustion tube as at least part thereof melts when reaching a preset temperature.
摘要翻译： 公开了一种推进系统和具有该推进系统的火箭。 推进系统包括：其中具有推进剂的燃烧管; 喷嘴，其安装在所述燃烧管的后端，并且被配置为排出当所述推进剂点燃时产生的燃烧气体; 以及喷嘴分离单元，其分别联接到所述燃烧管和所述喷嘴，并且被配置为将所述喷嘴安装到所述燃烧管，并且构造成当所述喷嘴至少部分在达到预设温度时熔化时将所述喷嘴与所述燃烧管分离。
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公开(公告)号：US07762195B2
公开(公告)日：2010-07-27
申请号：US12148027
申请日：2008-04-16
IPC分类号： F02K9/00
CPC分类号： F42C19/0819 , F02K9/38 , F02K9/566 , F02K9/95
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.
摘要翻译： 一种气体发生推进系统包括一个包含点火器推进剂和自动点火器的点火器。 火箭发动机联接到点火器并且具有容纳主推进剂，火箭发动机喉部和喷嘴的壳体。 释放口延伸穿过火箭发动机的一部分。 该气体释放口具有与主推进剂流体连通的可变直径通孔。 以这种方式，通孔具有可变区域，其形成无阻碍的开放区域，其横截面有效地排放由主推进剂产生的气体，使得壳体内的压力增加保持低于壳体的安全值。
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公开(公告)号：US06619029B2
公开(公告)日：2003-09-16
申请号：US10016697
申请日：2001-11-01
申请人： Mark A. Solberg , Robert E. Black
发明人： Mark A. Solberg , Robert E. Black
IPC分类号： F02K908
摘要： An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions charge. In a preferred embodiment, the rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.
摘要翻译： 本发明的火箭发动机的一个实施例采用不敏感的弹药方法，当受到升高的外部温度时，主要推进剂的热膨胀和次级不敏感弹药的气体产生被激活。 在优选实施例中，火箭发动机还包括压力平衡系统，该压力均衡系统在储存期间适应变化的温度条件，以及以允许更小的气缸设计和增加的推进剂体积的方式改变喷枪系统中固有的气体压力。
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公开(公告)号：US20020077794A1
公开(公告)日：2002-06-20
申请号：US09853076
申请日：2000-12-18
IPC分类号： G06G007/48
摘要： The present invention comprises a device which is inert and nullthermally-equivalentnull to actual ordnance. The device can travel with live ordnance and track the propellant temperatures in order to get a more precise propellant temperature for the ordnance. The device comprises a thermally equivalent inert grain instrumented with thermocouples, connected to a data recorder, and packaged in scaled-down ordnance hardware. The hardware is scaled down to enable the device to more easily travel with live munitions.
摘要翻译： 本发明包括与实际弹药惰性和“热等效”的装置。 该装置可以用活体运动并跟踪推进剂温度，以获得更精确的弹药推进剂温度。 该装置包括装有热电偶的热等效惰性颗粒，连接到数据记录器，并包装在按比例缩小的弹药硬件中。 硬件按比例缩小，使设备能够更容易地使用实时弹药旅行。
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公开(公告)号：US6360526B2
公开(公告)日：2002-03-26
申请号：US86482801
申请日：2001-05-24
申请人： US NAVY
发明人： KUNSTMANN JOHN F
摘要： A rocket motor having a desensitizing mechanism for preventing explosion or violent reaction during slow cook-off is provided. The rocket motor includes a case contained rocket propellant with a desensitizing assembly attached forward of the propellant charge. The desensitizing assembly is formed with an enclosure containing a desensitizing fluid, and connected to the interior of the rocket motor by a tube which is sealed by a heat sensitive plug. The heat sensitive plug melts at a temperature below the slow cook-off temperature of the rocket propellant. The melting of the plug allows the desensitizing fluid to be ejected into the interior of the casing and onto the propellant charges, thereby, desensitizing the propellant charge.
摘要翻译： 提供一种具有用于防止在慢速烹制期间的爆炸或剧烈反应的脱敏机构的火箭发动机。 火箭发动机包括一个包含火箭推进剂的壳体，其具有与推进剂装料前面相连的脱敏组件。 脱敏组件形成有包含脱敏流体的外壳，并且通过由热敏塞被密封的管连接到火箭发动机的内部。 热敏塞在温度低于火箭推进剂的慢蒸煮温度的温度下熔化。 塞子的熔化允许脱敏流体喷射到壳体的内部和推进剂装料中，从而使推进剂装料脱敏。
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公开(公告)号：US5212946A
公开(公告)日：1993-05-25
申请号：US702511
申请日：1991-05-20
摘要： A modular reusable rocket motor combined with reusable, disposable, and expendable assemblies to provide customized operational characteristics for a rocket launched therewith.
摘要翻译： 组合式可重复使用的火箭发动机结合了可重复使用的，一次性的和消耗性的组件，为与其一起发射的火箭提供定制的操作特性。
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