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31. 发明授权

US3442084A Multistage solid fuel rocket propulsion unit for the placing of depth charges 失效
标题翻译：用于配置深度充电的多功能固体燃料油门推进装置
公开(公告)号：US3442084A
公开(公告)日：1969-05-06
申请号：US3442084D
申请日：1967-09-21
申请人： DYNAMIT NOBEL AG
发明人： DILCHERT HEINZ , CRAMM RUDOLF , FIBRANZ JOACHIM
IPC分类号： F02K9/28 , F02K9/76 , F02K9/04
CPC分类号： F02K9/28 , F02K9/763

32. 发明授权

US2892308A Water spray cooling method and apparatus for supersonic nozzle 失效
标题翻译：喷水冷却方法及超音速喷嘴设备
公开(公告)号：US2892308A
公开(公告)日：1959-06-30
申请号：US65404957
申请日：1957-04-19
申请人： ANTONIO FERRI , LIBBY PAUL A , BLOOM MARTIN H
发明人： ANTONIO FERRI , LIBBY PAUL A , BLOOM MARTIN H
IPC分类号： F01D9/02 , F02K9/28 , F02K9/97
CPC分类号： F02K9/28 , F01D9/02 , F02K9/97

33. 发明授权

US12116957B1 3D-printed rocket fuel grains, rocket engines and an additive manufacturing process 有权
公开(公告)号：US12116957B1
公开(公告)日：2024-10-15
申请号：US17325558
申请日：2021-05-20
申请人： X-Bow Launch Systems Inc.
发明人： Jason Hundley , Mark Kaufman , Michael McPherson , Jillian Marsh , Matthew Hinton , Dane Fradenburg
IPC分类号： F02K9/10 , B64G1/40 , F02K9/18 , F02K9/24 , F02K9/28 , F02K9/34 , F02K9/72
CPC分类号： F02K9/10 , B64G1/404 , F02K9/18 , F02K9/24 , F02K9/28 , F02K9/34 , F02K9/72
摘要： A fuel grain for a rocket, the fuel grain having a plurality of layers of fuel grain material, each layer comprising a plurality of concentric circular structures of different diameter fused together to form a central opening therein, wherein the fuel grain material comprises an ignitable substance. The plurality of layers are stacked and joined securely to form a cylindrical fuel grain with the central opening of each one of the plurality of layers aligned to form a combustion unit extending axially through the fuel grain and bounded by a combustion surface, and wherein the fuel grain is configured to permit mixing of heterogenous materials to enhance thrust performance.

34. 发明授权

US11661907B2 Vortex hybrid rocket motor 有权
公开(公告)号：US11661907B2
公开(公告)日：2023-05-30
申请号：US16157669
申请日：2018-10-11
申请人： Sierra Space Corporation
发明人： Martin Chiaverini , Patrick Satyshur , Christopher St. Clair
IPC分类号： F02K9/72 , F02K9/42 , C06B23/00 , F02K9/28 , F23C3/00
CPC分类号： F02K9/72 , C06B23/00 , F02K9/28 , F02K9/42 , F23C3/006
摘要： Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.

35. 发明申请

US20180334996A1 Hybrid Rocket Motor 审中-公开
公开(公告)号：US20180334996A1
公开(公告)日：2018-11-22
申请号：US15983809
申请日：2018-05-18
申请人： Streamline Automation LLC
发明人： William Chew , Geoffrey Chew
IPC分类号： F02K9/28 , F02K9/97
CPC分类号： F02K9/28 , F02K9/97
摘要： Hybrid rocket motors having fuel grains containing glycidyl azide polymer (GAP) produce high regression rates and can be stopped and restarted. The fuel grains also contain carbon and optionally either hydroxyl-terminated polybutadiene (HTPB) or polyethylene glycol (PEG). TGAP self-deflagration in the hybrid rocket motors is controlled by at least one of motor design and the amount of carbon in the fuel grain.

36. 发明授权

US09784545B1 Rocket motors having controlled autoignition propellant systems 有权
公开(公告)号：US09784545B1
公开(公告)日：2017-10-10
申请号：US10376297
申请日：2003-03-03
申请人： Kenneth J. Graham , Edna M. Grove , Robert D. Lynch , Guy B. Spear
发明人： Kenneth J. Graham , Edna M. Grove , Robert D. Lynch , Guy B. Spear
IPC分类号： F02K9/28 , F02K9/12 , F02K9/95 , C06B45/10 , C06B45/12 , C06B25/34 , C06B29/22 , F42B15/00 , F42C15/36 , C06B45/34
CPC分类号： C06B45/34 , C06B25/34 , C06B29/22 , C06B45/10 , C06B45/12 , F02K9/12 , F02K9/28 , F02K9/95 , F42B39/20 , F42C15/36
摘要： Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

37. 发明授权

US09151245B2 Pulse rocket motor including a dividing sheet for separating the first grain propellant from the second grain propellant 有权
标题翻译：脉冲火箭发动机包括用于将第一颗粒推进剂与第二颗粒推进剂分离的分隔板
公开(公告)号：US09151245B2
公开(公告)日：2015-10-06
申请号：US13529836
申请日：2012-06-21
申请人： Hiroyuki Kawadu , Ichiro Yamaguchi , Shuji Hagiwara , Shoji Endo , Tokuichiro Ojima
发明人： Hiroyuki Kawadu , Ichiro Yamaguchi , Shuji Hagiwara , Shoji Endo , Tokuichiro Ojima
IPC分类号： F02K9/08 , F02K9/28 , F02K9/32 , F02K9/36
CPC分类号： F02K9/08 , F02K9/28 , F02K9/32 , F02K9/36
摘要： A pulse rocket motor has a hollow cylinder-like first grain situated in a rear section of a pressure vessel; a first igniter for igniting the first grain; a hollow cylinder-like second grain situated in a front section of the pressure vessel; a second igniter for igniting the second grain; and a dividing sheet member that covers the second grain within the pressure vessel. The dividing sheet member includes a dividing sheet expanding at least along the inner circumferential surface of the second grain and holders formed integrally with the dividing sheet at both ends of the dividing sheet by cure adhesion and attached to the pressure vessel. The dividing sheet includes a brittle portion that expands along the inner circumferential surface of the second grain through a rear end face of the second grain and is more brittle than other portions.
摘要翻译：脉冲火箭发动机具有位于压力容器后部的中空圆柱状的第一颗粒; 点燃第一颗谷子的第一个点火器; 位于所述压力容器的前部的中空的圆筒状的第二颗粒; 用于点燃第二颗粒的第二个点火器; 以及覆盖压力容器内的第二颗粒的分隔片部件。分隔片部件包括至少沿着第二颗粒的内周面延伸的分隔片，并且通过固化粘合力在分隔片的两端与分隔片一体形成的保持件并且附接到压力容器。分割片包括通过第二晶粒的后端面沿着第二晶粒的内周面膨胀并且比其它部分更脆的脆性部分。

38. 发明授权

US09108711B2 Generation of a pulsed jet by jet vectoring through a nozzle with multiple outlets 有权
标题翻译：通过喷嘴引导通过具有多个出口的喷嘴产生脉冲喷射
公开(公告)号：US09108711B2
公开(公告)日：2015-08-18
申请号：US12726826
申请日：2010-03-18
申请人： Paul S. Krueger
发明人： Paul S. Krueger
IPC分类号： B63H25/46 , F02K1/00 , F02K9/82 , F02K9/28 , E02F3/92 , F15D1/08
CPC分类号： F02K1/008 , B63H25/46 , E02F3/9206 , F02K1/002 , F02K9/28 , F02K9/82 , F15D1/08
摘要： A method of producing a pulsatile jet flow from a substantially constant flow primary jet in a way that is mechanically efficient, easy to implement, and allows direct control over pulse duration and pulsing frequency is disclosed herein. The invention includes at least two components: (a) a constant flow fluid jet produced by any normal method (e.g., propeller) that can be directionally vectored fluidically, mechanically, or electromagnetically and (b) a nozzle with multiple outlets (orifices) through which the vectored jet may be directed. By alternately vectoring the jet through different outlets, a transient (pulsatile) flow at an outlet is obtained even with a substantially constant primary jet flow. Additionally, the nozzle outlets may be oriented in different directions to provide thrust vectoring, making the invention useful for maneuvering, directional control, etc.
摘要翻译：本文公开了以机械效率，易于实施并且允许对脉冲持续时间和脉冲频率的直接控制的方式从基本上恒定的流量初级射流产生脉冲喷射流的方法。本发明包括至少两个部件：（a）通过任何常规方法（例如，螺旋桨）产生的恒定流动流体射流，其可以流体地，机械地或电磁地定向定向，以及（b）具有多个出口（孔口）通过的喷嘴向导可以被引导。通过交替地通过不同的出口引导射流，即使以基本上恒定的一次喷射流也可以获得出口处的瞬态（脉动）流动。此外，喷嘴出口可以沿不同方向定向以提供推力矢量化，使得本发明可用于操纵，方向控制等。

39. 发明申请

US20150047316A1 MULTI-PULSE GAS GENERATOR AND OPERATION METHOD THEREOF 有权
标题翻译：多脉冲气体发生器及其运行方法
公开(公告)号：US20150047316A1
公开(公告)日：2015-02-19
申请号：US14455037
申请日：2014-08-08
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Chiyako MIHARA , Tasuku SUZUKI , Katsunori IEKI
IPC分类号： F02K9/28 , F02K9/20 , F02K9/12
CPC分类号： F02K9/28 , F02K9/12 , F02K9/18 , F02K9/20 , F05D2210/12
摘要： A multi-pulse gas generator includes a pressure vessel, an outer propellant arranged in the pressure vessel and which has a tubular shape, an intermediate propellant arranged inside the outer propellant and which has a tubular shape, an inner propellant arranged inside the intermediate propellant and which has a tubular shape, an internal structure arranged inside the inner propellant and fixed to the pressure vessel, a first barrier membrane arranged between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other, and a second barrier membrane arranged between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other. The outer propellant is supported on its outer surface by the pressure vessel. The inner propellant is supported on its inner surface by the internal structure.
摘要翻译：多脉冲气体发生器包括压力容器，布置在压力容器中的外推进剂并具有管状形状，布置在外推进剂内部并具有管状形状的中间推进剂，布置在中间推进剂内部的内推进剂和其具有管状形状，内部结构布置在内部推进剂内并固定到压力容器，第一阻挡膜布置在外推进剂和中间推进剂之间，以将外推进剂和中间推进剂彼此隔离，以及布置在中间推进剂和内推进剂之间的第二阻隔膜，以便将中间推进剂和内推进剂彼此分离。外推进剂由压力容器支撑在其外表面上。内推进剂通过内部结构支撑在其内表面上。

40. 发明授权

US08667776B2 Pellet-loaded multiple impulse rocket motor 有权
标题翻译：颗粒装载多冲程火箭发动机
公开(公告)号：US08667776B2
公开(公告)日：2014-03-11
申请号：US12391216
申请日：2009-02-23
申请人： Thomas A. Olden , Robert J. Cavalleri
发明人： Thomas A. Olden , Robert J. Cavalleri
IPC分类号： F02K9/28 , F02K9/00
CPC分类号： F02K9/28 , F02K9/36
摘要： There is disclosed an apparatus which may include a common nozzle and a plurality of combustion chambers coupled to the nozzle. Each of the plurality of combustion chambers may include a case, a solid fuel propellant charge in the form of a plurality of fuel pellets, and an igniter disposed to ignite the propellant charge. Each of the plurality of combustion chambers may also include a pellet retainer disposed to retain unignited fuel pellets within the case and a burst disk disposed between the propellant charge and the nozzle. Each burst disk may adapted to rupture when the associated propellant charge is ignited and to not rupture when a propellant charge of any of the other combustion chambers is ignited.
摘要翻译：公开了一种可以包括公共喷嘴和联接到喷嘴的多个燃烧室的装置。多个燃烧室中的每一个可以包括壳体，多个燃料颗粒形式的固体燃料推进剂装料和设置成点燃推进剂装料的点火器。多个燃烧室中的每一个还可以包括一个颗粒保持器，该颗粒保持器被设置成将未被标记的燃料颗粒保持在壳体内，并且一个爆破盘设置在推进剂装料和喷嘴之间。当爆炸相关联的燃料被点燃时，每个爆破盘可适于破裂，并且当任何其它燃烧室的推进剂装料被点燃时不破裂。

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