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1. 发明授权

US10006408B2 Three-pulse gas generator and operation method thereof 有权
公开(公告)号：US10006408B2
公开(公告)日：2018-06-26
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 , F02K9/12 , F02K9/20 , F02K9/18
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.

2. 发明申请

US20170284339A1 THRUSTER WITH SEGMENTED PROPELLANT 审中-公开
公开(公告)号：US20170284339A1
公开(公告)日：2017-10-05
申请号：US15091245
申请日：2016-04-05
申请人： Raytheon Company
发明人： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC分类号： F02K9/28
CPC分类号： F02K9/28 , F02K9/26 , F02K9/32 , F02K9/94 , F02K9/95
摘要： A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments into engagement with the electrodes. The segments may be configured to provide equal increments of thrust, or different amounts of thrust. The segments may each include an electrically-operated propellant material surrounded by a sealing material, so as to keep the propellant material away from moisture and other contaminants (and/or the vacuum of space) before each individual segment is to be used. The thruster may be included in any of a variety of flight vehicles, for example in a small satellite such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

3. 发明申请

US20170097213A1 ELECTRICALLY OPERATED PULSE INITIATORS AND IGNITION 审中-公开
公开(公告)号：US20170097213A1
公开(公告)日：2017-04-06
申请号：US14875741
申请日：2015-10-06
申请人： Raytheon Company
发明人： James Kendall Villarreal , Mark T. Langhenry , Matt H. Summers , Daniel V. Macinnis
IPC分类号： F42B3/04
CPC分类号： F42B3/04 , F02K9/28 , F02K9/95
摘要： A gas generation system for generating gases, such as for use as or as part of a rocket motor in propelling a projectile, includes two or more propellant charges and electrically operated propellant initiators operatively coupled to respective of the propellant charges, to initiate combustion in the propellant charges, wherein the propellant charges are operatively isolated from one another such that the propellant charges can be individually initiated and are not ignited due to gases generated from other of the propellant charges being combusted.

4. 发明授权

US08776526B2 Motor with solid fuel installed within combustion chamber and vortex generator installed on inner wall of combustion chamber 有权
标题翻译：安装在燃烧室内的固体燃料的电机和安装在燃烧室内壁上的涡流发生器
公开(公告)号：US08776526B2
公开(公告)日：2014-07-15
申请号：US13018517
申请日：2011-02-01
申请人： Yen-Sen Chen , Jong-Shinn Wu , Tzu-Hao Chou
发明人： Yen-Sen Chen , Jong-Shinn Wu , Tzu-Hao Chou
IPC分类号： F02K7/10
CPC分类号： F02K9/72 , F02K9/26 , F02K9/28
摘要： The present invention provides a motor including a combustion chamber, an oxidizer injector, a vortex generators and a nozzle. The combustion chamber can be used to dispose a solid fuel, and the oxidizer injector is used to control the flow rate of an oxidizer and to inject the oxidizer into the combustion chamber. The vortex generators is disposed on the inner wall of the combustion chamber for generating eddies to enhance the mixing of the fuel and the oxidizer. Additionally, the nozzle is connected with the combustion chamber for exhausting the gas generated by the combustion of the propellants.
摘要翻译：本发明提供一种电动机，其包括燃烧室，氧化剂喷射器，涡流发生器和喷嘴。燃烧室可用于处置固体燃料，氧化剂注射器用于控制氧化剂的流量并将氧化剂注入燃烧室。涡流发生器设置在燃烧室的内壁上，用于产生涡流以增强燃料和氧化剂的混合。此外，喷嘴与燃烧室连接，用于排出由推进剂的燃烧产生的气体。

5. 发明申请

US20120311993A1 MULTI-PULSE ROCKET MOTOR AND PULSE UNIT THEREOF 有权
标题翻译：多脉冲电动机及其脉冲单元
公开(公告)号：US20120311993A1
公开(公告)日：2012-12-13
申请号：US13491725
申请日：2012-06-08
申请人： Chiyako MIHARA , Tasuku SUZUKI , Katsunori IEKI
发明人： Chiyako MIHARA , Tasuku SUZUKI , Katsunori IEKI
IPC分类号： F02K9/10 , F02K9/34
CPC分类号： F02K9/10 , F02K9/28 , F02K9/34
摘要： A pulse unit of a multi-pulse rocket motor has: a propellant in an internal-burning type or internal-end-burning type shape that is loaded within a motor case; an igniter arranged at an end surface of the propellant; a barrier membrane arranged to cover a whole of an initial burning surface of the propellant and the igniter; a forward joint arranged at a forward end of the motor case; and a rearward joint arranged at a rearward end of the motor case. The forward joint is formed so as to be connectable with the rearward joint of another pulse unit. The rearward joint is formed so as to be connectable with the forward joint of still another pulse unit.
摘要翻译：多脉冲火箭发动机的脉冲单元具有：内燃式或内燃烧型的推进剂，其装载在电动机壳体内; 布置在推进剂的端面的点火器; 阻挡膜，布置成覆盖推进剂和点火器的整个初始燃烧表面; 布置在电动机壳体的前端的前方接头; 以及设置在电动机壳体的后端的后关节。前关节形成为可与另一脉冲单元的后关节连接。后关节形成为可与另一脉冲单元的前关节连接。

6. 发明申请

US20110167794A1 Multi-Functional Pulse-Divided Rocket 有权
标题翻译：多功能脉冲分割火箭
公开(公告)号：US20110167794A1
公开(公告)日：2011-07-14
申请号：US12041797
申请日：2008-03-04
申请人： Guy B. Spear , Katherine L. Clopeck , Richard T. Brown , Michael Digiacomo , William M. Wallace
发明人： Guy B. Spear , Katherine L. Clopeck , Richard T. Brown , Michael Digiacomo , William M. Wallace
IPC分类号： F02K9/00
CPC分类号： F02K9/28 , F02K9/80 , F05D2240/1281
摘要： A multi-pulse rocket is equipped with a thermally insulating barrier that serves as a rupture disk or a movable plug or plate separating staged propellant grains. When a rupture disk it used, the disk can be equipped with a pyrotechnic actuator to weaken the disk upon command, enabling the propellant grain on the fore side of the disk to burst the disk at a relatively low pressure when ignition of the propellant grain is needed for additional thrust. Rupturing of the disk can also be controlled by attitude maneuvering ports on the fore side of the barrier whose open or closed conditions are controlled by independently operable closures. When a movable plug is used, the plug is movable between a closed position separating rocket chamber into subchambers isolating the propellant grains from each other and an open position allowing the flow of combustion gas between the two subchambers to achieve additional axial thrust. In all cases, the barrier when intact serves to contain both propellant grains regardless of whether one or both is ignited. The propellant grain on the fore side of the barrier can thus be used for either axial thrust augmentation or for attitude maneuvering.
摘要翻译：多脉冲火箭配备有绝热障碍物，其用作破裂盘或分离分段推进剂颗粒的活动塞子或板。当使用破裂盘时，盘可以装备有烟火执行器，以便在命令时削弱盘，使得当推进剂颗粒点燃时点燃盘片的前侧上的推进剂颗粒以相对低的压力爆裂，需要额外的推力。盘的破裂也可以通过位于屏障前侧的姿态操纵端口来控制，其开放或关闭状态由独立可操作的闭合来控制。当使用可移动塞子时，塞子可以将分离火箭箱的关闭位置与将推进剂颗粒彼此隔离的子室和允许两个子室之间的燃烧气体流动以获得额外的轴向推力的打开位置之间移动。在所有情况下，完好无损的屏障用于包含两种推进剂颗粒，而不管其中一种或两种是否被点燃。因此，阻挡物前侧上的推进剂颗粒可用于轴向推力增加或姿态机动。

7. 发明申请

US20100218481A1 TWO-PULSE ROCKET MOTOR 有权
标题翻译：双脉冲电机
公开(公告)号：US20100218481A1
公开(公告)日：2010-09-02
申请号：US12599874
申请日：2008-05-09
申请人： Chiyako Mihara , Katsunori Ieki
发明人： Chiyako Mihara , Katsunori Ieki
IPC分类号： F02K5/02
CPC分类号： F02K9/08 , F02K9/12 , F02K9/28 , F02K9/95
摘要： In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted.
摘要翻译：在根据本发明的双脉冲火箭发动机中，第二推进剂设置在电动机壳体中的第一推进剂的外部，并且第一推进剂的内表面在整个长度方向上沿着电机箱。因此，可以确保初始燃烧区域而不会降低性能。此外，通过在屏障膜上粘合阻隔膜或成形狭缝来提供弱的部分，可以控制阻隔膜的断裂部分和断裂后的阻隔膜的行为。此外，通过在第二推进剂的内表面和内阻挡膜之间设置具有比第二推进剂更高的点火性和更高燃烧速率的点火器电荷，可以辅助阻隔膜的分离和第二推进剂的点燃。

8. 发明授权

US07210282B1 Case burning rocket 失效
标题翻译：案例燃火箭
公开(公告)号：US07210282B1
公开(公告)日：2007-05-01
申请号：US10916352
申请日：2004-08-11
申请人： Brian A. Floyd
发明人： Brian A. Floyd
IPC分类号： F02K9/32
CPC分类号： F02K9/72 , F02K9/28 , F02K9/34 , F02K9/343
摘要： A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case and fuel to generate thrust, and a drive system for pulling the combustion chamber and nozzle up the case as the case and fuel burn. A hybrid version of the case-burning rocket also includes an oxidizer supply system for supplying varying amounts of oxidizer to the combustion chamber to vary the thrust generated by burning the case and the fuel.
摘要翻译：一种燃烧式火箭助推器包括一个包含固体火箭燃料的可燃壳体，一个可调节地联接到壳体上用于燃烧壳体和固体火箭燃料的燃烧室，连接到燃烧室的喷嘴，用于排出燃烧的壳体和燃料以产生推力和驱动系统，用于拉动燃烧室并在壳体和燃料燃烧时将喷嘴向上喷出。壳体燃烧火箭的混合版本还包括用于向燃烧室供应不同量的氧化剂的氧化剂供应系统，以改变由燃烧壳体和燃料产生的推力。

9. 发明授权

US06226979B1 Propellant grain capable of generating buffered boundary layer for reducing rocket nozzle recession 失效
标题翻译：推进剂颗粒能够产生缓冲边界层，用于减少火箭喷嘴的衰退
公开(公告)号：US06226979B1
公开(公告)日：2001-05-08
申请号：US09503725
申请日：2000-02-15
申请人： Robert A. Pate , Frederick M. Perkins
发明人： Robert A. Pate , Frederick M. Perkins
IPC分类号： F02K928
CPC分类号： F02K9/26 , F02K9/12 , F02K9/28 , F02K9/62
摘要： This rocket motor propellant grain is designed to reduce recession of at least the converging portion of a converging/diverging rocket motor nozzle. The propellant grain has an oxidizer-deficient grain portion constructed and arranged in relation to the nozzle to create, upon ignition of the propellant, a boundary layer of oxygen-deficient combustion products that flows through the nozzle throat passage and over an internal surface region of the nozzle. The boundary layer functions to at least substantially isolate the internal surface region of the nozzle from oxidizers contained in the combustion products generated from portions of the propellant grain having higher concentrations of oxygen than the oxidizer-deficient grain portion. As a result, the oxygen-rich portions of the propellant are unable to react with and thereby cause recession of the nozzle internal surface.
摘要翻译：该火箭发动机推进剂颗粒被设计成减少至少会聚/发散火箭发动机喷嘴的会聚部分的凹陷。推进剂颗粒具有相对于喷嘴构造和布置的氧化剂缺乏的颗粒部分，其在点燃推进剂时产生氧缺乏的燃烧产物的边界层，其流过喷嘴喉部通道并在喷嘴。边界层的作用是至少基本上将喷嘴的内表面区域与包含在比不含氧化剂缺陷的颗粒部分的具有较高氧浓度的推进剂颗粒的部分产生的燃烧产物中所含的氧化剂基本上隔离。结果，推进剂的富氧部分不能与喷嘴内表面发生反应并从而导致喷嘴内表面的凹陷。

10. 发明授权

US5600946A Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture 失效
公开(公告)号：US5600946A
公开(公告)日：1997-02-11
申请号：US469759
申请日：1995-06-06
申请人： Daniel C. Dombrowski , Thomas J. Frey , Andrew G. Nevrincean , Clyde E. Carr, Jr.
发明人： Daniel C. Dombrowski , Thomas J. Frey , Andrew G. Nevrincean , Clyde E. Carr, Jr.
IPC分类号： F02K9/28 , F02K9/34 , F02K9/36 , F02K9/95 , F02K9/00
CPC分类号： F02K9/346 , F02K9/28 , F02K9/95
摘要： A solid propellant dual pulse rocket motor has a pressure vessel containing two pulse grains separated by a barrier insulator. An igniter assembly disposed at a fore end of the pressure vessel selectively ignites a first pulse grain from a central channel within the grain. The igniter assembly also ignites a second pulse grain by ejecting hot combustion gases onto the fore end of the grain. Using such an ignition arrangement, a dual pulse rocket motor may be constructed using standard off-the-shelf ignition components.

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