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1. 发明授权

US11512668B2 Multi-pulse solid rocket motor ignition method 有权
公开(公告)号：US11512668B2
公开(公告)日：2022-11-29
申请号：US17106089
申请日：2020-11-28
申请人： Raytheon Company
发明人： Frederick B. Koehler , Jacob A. Pinello-Benavides , Curtis S. Copeland , Isaiah M. McNeil , Paul Kadlec , Lauren E. Brunacini , Mark T. Langhenry
IPC分类号： F02K9/95 , F02K9/28 , F02K9/38 , F02K9/94
摘要： A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.

2. 发明申请

US20190195171A1 ROCKET ENGINE INCLUDING A LASHING DEVICE 审中-公开
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
IPC分类号： F02K9/38 , B64G5/00 , F02K9/95 , F02K9/96 , F02K9/97
CPC分类号： F02K9/38 , B64G5/00 , F02K9/95 , F02K9/96 , F02K9/97
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).

3. 发明授权

US08191351B2 Insensitive rocket motor 有权
标题翻译：不敏感火箭发动机
公开(公告)号：US08191351B2
公开(公告)日：2012-06-05
申请号：US12261905
申请日：2008-10-30
申请人： Richard D. Loehr , Gerald M. Turner , Jeremy C. Danforth
发明人： Richard D. Loehr , Gerald M. Turner , Jeremy C. Danforth
IPC分类号： F02K9/08 , F02K9/38
CPC分类号： F02K9/18 , F02K9/22 , F02K9/26
摘要： There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.
摘要翻译：公开了一种固体燃料火箭发动机，其包括中心穿孔的固体燃料颗粒。固体燃料颗粒可以适于在正常操作模式期间被主要点火器点燃时从面向中心穿孔的中心表面向外燃烧。固体燃料颗粒可以进一步适于在安全操作模式期间被二次点火器点燃时从端面纵向燃烧。

4. 发明授权

US07003942B2 System and method of controlling pressure oscillations of hydrodynamic origin for a solid propellant thruster 有权
标题翻译：控制固体推进剂推进器的流体动力学起源的压力振荡的系统和方法
公开(公告)号：US07003942B2
公开(公告)日：2006-02-28
申请号：US10648983
申请日：2003-08-27
申请人： Philippe Le Helley , Louis Jacques , Christophe Magniére , Gilles Uhrig , Bernard Bondon , Jean-Claude Tricot , Didier Boury , Marco Telara , Paolo Bellomi , Georgio Mastrangelo
发明人： Philippe Le Helley , Louis Jacques , Christophe Magniére , Gilles Uhrig , Bernard Bondon , Jean-Claude Tricot , Didier Boury , Marco Telara , Paolo Bellomi , Georgio Mastrangelo
IPC分类号： F02K9/08 , F02K9/38
CPC分类号： F02K9/26 , F02K9/32
摘要： The invention provides a system for passively controlling pressure oscillations of hydrodynamic origin in a solid propellant thruster comprising a body containing a charge of solid propellant, the system comprising at least one insert disposed in the thruster body transversely relative to the flow direction of the combustion gases of the solid propellant. The insert has an opening of non-axisymmetric shape so as to generate a three-dimensional effect on the flow and prevent axisymmetric turbulent modes from forming in the thruster. Thus, the control system of the invention serves to break the symmetry of the flow and thus prevents axisymmetric turbulence forming which is the source of instability that the present invention seeks to control. The present system is applicable to existing thrusters.
摘要翻译：本发明提供了一种用于被动地控制固体推进剂推进器中的流体动力源的压力振荡的系统，其包括含有固体推进剂装料的主体，该系统包括相对于燃烧气体的流动方向横向设置在推进器主体中的至少一个插入件的固体推进剂。插入件具有非轴对称形状的开口，以便对流动产生三维效果，并防止在推进器中形成轴对称湍流模式。因此，本发明的控制系统用于破坏流动的对称性，从而防止作为本发明寻求控制的不稳定性源的轴对称湍流形成。本系统适用于现有的推进器。

5. 发明授权

US6360526B2 Rocket motor with desensitizer injector 失效
标题翻译：火箭发动机带脱敏剂注射器
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
IPC分类号： F02K9/38 , F42B39/20
CPC分类号： F42B39/20 , F02K9/38
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。

6. 发明授权

US06148606A Low-vulnerability solid-propellant motor 失效
标题翻译：低脆弱性固体推进剂电机
公开(公告)号：US06148606A
公开(公告)日：2000-11-21
申请号：US96613
申请日：1998-06-12
申请人： Augustin Grossi , Patrick Fiandesio
发明人： Augustin Grossi , Patrick Fiandesio
IPC分类号： F42B39/20 , F02K9/38
CPC分类号： F42B39/20
摘要： The present invention relates to a low-vulnerability solid-propellant motor (1) comprising a charge (11) of solid propellant, a heat shield (2) covering the inside of a metal structure with a front end wall (3) and a rear end wall (4) which carries at least one nozzle (10), the said front and rear end walls being fastened to a cylindrical shell (5) having wide apertures which are circumferentially distributed and temporarily sealed by sealing plugs (8). The object of the present invention is to provide a motor which has a simple structure and avoids the use of detection and actuation means for freeing the plugs. The motor according to the invention is such that the sealing plugs (8) are held in the apertures between the heat shield and a composite winding (7) of fibres impregnated in a matrix which surrounds the cylindrical shell (5).
摘要翻译：本发明涉及一种低脆弱性固体推进剂电动机（1），其包括固体推进剂的电荷（11），覆盖金属结构的内部的隔热罩（2），其具有前端壁（3）和后端端壁（4），其承载至少一个喷嘴（10），所述前端和后端壁紧固到具有宽孔的圆柱形外壳（5），所述圆形壳体周向分布并通过密封塞（8）临时密封。本发明的目的是提供一种具有简单结构并避免使用用于释放插头的检测和致动装置的电动机。根据本发明的电动机使得密封塞（8）保持在隔热件和浸渍在围绕圆柱形壳体（5）的矩阵中的纤维的复合绕组（7）之间的孔中。

7. 发明授权

US5212946A Reloadable/modular solid propellant rocket motor 失效
标题翻译：可重装/模块式固体推进剂火箭发动机
公开(公告)号：US5212946A
公开(公告)日：1993-05-25
申请号：US702511
申请日：1991-05-20
申请人： Paul C. Hans , Gary C. Rosenfield , Daniel H. Meyer
发明人： Paul C. Hans , Gary C. Rosenfield , Daniel H. Meyer
IPC分类号： F02K9/34 , F02K9/38
CPC分类号： F02K9/34 , F02K9/38
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。

8. 发明授权

US5160070A Reverse bulged forward acting scored rupture disc bulkhead structure for multi-stage rocket motor 失效
标题翻译：多级火箭发动机反向隆起正向作用刻痕防爆片隔板结构
公开(公告)号：US5160070A
公开(公告)日：1992-11-03
申请号：US651338
申请日：1991-03-25
申请人： Donald R. Hibler , James O. Hinrichs
发明人： Donald R. Hibler , James O. Hinrichs
IPC分类号： F02K9/28 , F02K9/38 , F02K9/76 , F02K9/97 , F42B15/36
CPC分类号： F02K9/978 , F02K9/28 , F02K9/38 , F02K9/763 , F42B15/36
摘要： Rupture disc bulkhead structure for use in a multi-stage rocket motor for missiles or the like wherein the disc is supported by a multiple apertured backup member. The disc has a series of bulges which define dimples that conform to the configuration of the apertures in the backup member. Bulging of the disc is carried out under a pressure exceeding that of the withstand pressure of the supported disc. Score lines in the disc aligned with the support segments of the apertured backup member permit the disc to rupture and open at a pressure significantly lower than the back pressure withstand value. The construction provides bulkhead structure which will withstand back pressures in the range of 2,000 to 10,000 static psig yet fully open in a forward direction at a static pressure of no more than about 100 to 400 psig.
摘要翻译： PCT No.PCT / US89 / 03425 Sec。 371日期1991年3月25日 102（e）日期1991年3月25日PCT申请1988年8月11日。用于导弹等的多级火箭发动机的隔离盘隔板结构，其中盘由多孔径支撑构件支撑。盘具有一系列凸起，其形成符合备用构件中的孔的构造的凹坑。盘的膨胀在超过所支撑的盘的耐压的压力下进行。与圆孔支撑构件的支撑段对准的盘中的刻痕线允许盘在显着低于背压耐受值的压力下破裂和打开。该结构提供了隔板结构，其将承受2000至10,000静态压力范围内的背压，并且在不超过约100至400psig的静压下在向前方向上完全打开。

9. 发明授权

US5129326A Ordnance device with explosion protection 失效
标题翻译：防爆装置
公开(公告)号：US5129326A
公开(公告)日：1992-07-14
申请号：US38082
申请日：1987-04-14
申请人： Robert Brogan
发明人： Robert Brogan
IPC分类号： F02K9/38 , F42B39/20
CPC分类号： F42B39/20 , F02K9/38
摘要： Controlled venting of combustion gases from an explosive material encased in a shell, as used in ordnance constructions such as rocket motors, warheads and bombs, is achieved by affixing a composite solid mass to the shell casing at a preselected location presenting low risk of damage to surrounding equipment or personnel. The solid mass is in two portions, the first being an ignition mix (in direct contact with the shell) which ignites at a temperature of 400.degree. F. to 600.degree. F. to react exothermally. The second is a reaction mix ignitable by the energy released by the ignition mix to itself release sufficient energy to degrade the metallurgical structure of the case. With the case thus weakened at a localized point, the case will rupture preferentially at that point upon an interior pressure buildup, and explosion of the entire case can be avoided.
摘要翻译：通过在诸如火箭发动机，弹头和炸弹等兵器结构中使用的封装在外壳中的爆炸性材料的燃烧气体的控制排放是通过将复合固体物质固定在壳体上的预选位置来实现的，其具有低的损害风险周边设备或人员。固体物质分为两部分，第一部分是点燃混合物（与壳体直接接触），其在400°F至600°F的温度下点燃，以进行放热反应。第二种是由点燃混合物释放的能量自身释放足够的能量来降低壳体的冶金结构而可燃的反应混合物。由于在局部点处的情况因此被削弱，在内部压力积聚时，该情况将在该点处优先断裂，并且可以避免整个壳体的爆炸。

10. 发明授权

US4803925A Device for the limitation of gas pressure in a combustion chamber provided inside a projectile 失效
标题翻译：用于限制设置在抛射体内部的燃烧室中的气体压力的装置
公开(公告)号：US4803925A
公开(公告)日：1989-02-14
申请号：US101217
申请日：1987-09-25
申请人： Sigfrid Buchele-Buecher
发明人： Sigfrid Buchele-Buecher
IPC分类号： F02K9/80 , F42B15/00 , F02K9/38
CPC分类号： F02K9/805 , F42B10/663
摘要： A device for the limitation of gas pressure in a projectile having an outer shell by the production of a control stream comprises a combustion chamber disposed inside the projectile; the combustion chamber having a combustion chamber lid; control lines connected to be changed by gas from the combustion chamber for transferring the gas pressure from the combustion chamber; monostable fluidic elements being arranged in the control lines in a region of the combustion chamber lid for assisting in confining the control stream; branching lines disposed in the lid and connected with the monostable fluidic elements, the branching lines including vent openings in the outer shell for releasing gas to the atmosphere and an overpressure element for permitting gas to be expelled from the combustion chamber when an overpressure exists therein, whereby gas expelled via the overpressure element assists in the production of the control stream.
摘要翻译：用于通过产生控制流来限制具有外壳的射弹中的气体压力的装置包括设置在射弹内部的燃烧室; 所述燃烧室具有燃烧室盖; 连接到燃烧室的气体连接的控制线路，用于从燃烧室传送气体压力; 单燃料流体元件布置在燃烧室盖的区域中的控制线中，用于辅助限制控制流; 设置在盖中并与单稳态流体元件连接的分支管线，分支管线包括用于将气体释放到大气中的用于释放气体的外壳中的通气口，以及当其中存在超压时允许气体从燃烧室排出的过压元件，由此通过超压元件排出的气体有助于控制流的生产。

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