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1. 发明授权

US6094906A Design for a gun-launched rocket 有权
标题翻译：设计一枚发射火箭的火箭
公开(公告)号：US6094906A
公开(公告)日：2000-08-01
申请号：US301157
申请日：1999-04-28
申请人： Victor Singer , Mark A. Solberg
发明人： Victor Singer , Mark A. Solberg
IPC分类号： F02K9/34 , F42B15/00 , F42B39/20 , F02K9/08
CPC分类号： F42B39/20 , F02K9/343 , F42B15/00
摘要： One embodiment of this novel rocket system employs at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at lunch. Another embodiment of this novel rocket involves an insensitive munitions approach that does not require use of such retainers by developing different normal and abnormal burn paths. The rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well 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：这种新型火箭系统的一个实施例采用至少一个火箭发动机闭合器，其包括低和高负载能力的保持器，其分别在午餐期间在喷嘴组件的存储和正锁定期间分别提供不灵敏的弹药系统。这种新型火箭的另一个实施例涉及不敏感的弹药方法，其不需要通过开发不同的正常和异常燃烧路径来使用这种保持器。火箭发动机还包括压力均衡系统，其在储存期间适应变化的温度条件以及喷枪系统中固有的气体压力，其允许更薄的气缸设计和增加的推进剂体积。

2. 发明授权

US5792981A Gun-launched rocket 失效
标题翻译：枪弹发射火箭
公开(公告)号：US5792981A
公开(公告)日：1998-08-11
申请号：US739469
申请日：1996-10-28
申请人： Victor Singer , Mark A. Solberg
发明人： Victor Singer , Mark A. Solberg
IPC分类号： F02K9/34 , F42B15/00 , F42B39/20 , F42B15/10 , F02K9/00
CPC分类号： F42B39/20 , F02K9/343 , F42B15/00
摘要： A rocket system employing at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at launch. 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 rocket systems in a manner that allows for thinner case cylinder design and increased propellant volume.
摘要翻译：火箭系统采用至少一个火箭发动机闭合器，其包括低负载能力和高负载能力的保持器，其分别在发射时在喷嘴组件的存储和正锁定期间提供不敏感的弹药系统。火箭发动机还包括压力平衡系统，其适应存储期间变化的温度条件以及枪射发射火箭系统固有的气体压力变化，从而允许更薄的气缸设计和增加的推进剂体积。

3. 发明授权

US5755401A Missile diverter integration method and system 失效
标题翻译：导弹分流器整合方法与系统
公开(公告)号：US5755401A
公开(公告)日：1998-05-26
申请号：US551006
申请日：1995-10-31
申请人： Thomas J. Frey , Philip H. Dara , Michael A. Gerace , Mark A. Solberg
发明人： Thomas J. Frey , Philip H. Dara , Michael A. Gerace , Mark A. Solberg
IPC分类号： F42B10/60
CPC分类号： F42B10/663 , Y10T137/7036 , Y10T137/87877
摘要： A missile diverter for controlling yaw and pitch includes several valve housings secured to an inside surface of a bridge or to a removable cylinder. The valve housings are secured in aligned positions by a layer of integral cured insulation. Gas valves are placed in the housings, and control lines are connected to the valves to allow remote control of the valves during flight. Cups loaded with propellant are secured in place near the valve housings. The valve housings, valves, cured insulation, and propellant cups are then overwrapped and secured within the outer shell of a missile. One method for making the missile diverter includes the step of applying a quantity of uncured insulation to an inside surface of a bridge and to an outside surface of each valve housing. Each valve housing is then positioned within the bridge and the insulation is cured to form an integral layer that holds the valve housings in their aligned positions and forms a hot gas seal.
摘要翻译：用于控制偏航和俯仰的导弹分流器包括固定到桥的内表面或可移除气缸的多个阀壳。阀壳通过整体固化绝缘层固定在对准位置。气阀被放置在壳体中，并且控制线连接到阀，以允许在飞行期间对阀进行远程控制。装有推进剂的杯子固定在阀壳体附近。然后将阀壳，阀，固化绝缘和推进剂杯包裹并固定在导弹的外壳内。用于制造导弹转向器的一种方法包括将一定量的未固化绝缘施加到桥的内表面和每个阀壳体的外表面的步骤。然后将每个阀壳体定位在桥内，并且绝缘体被固化以形成将阀壳体保持在其对准位置并形成热气体密封的整体层。

4. 发明授权

US4930541A Variable orifice diverter valve 失效
标题翻译：可变孔分流阀
公开(公告)号：US4930541A
公开(公告)日：1990-06-05
申请号：US308497
申请日：1989-02-10
申请人： Mark A. Solberg
发明人： Mark A. Solberg
IPC分类号： B64G1/26 , F02K9/80 , F16K47/04
CPC分类号： B64G1/26 , F02K9/805 , F16K47/04 , Y10T137/86847 , Y10T137/87812
摘要： The functions of a diverter valve and a variable orifice valve are combined in a single valve including an elongated magnetic member that is pivoted at a first end with a portion of the second end being positioned between opposed restrictors, a coil assembly for producing a magnetic field for selectively pulling the magnetic member toward one of the restrictors, sealing the restrictor it is pulled against thereby enabling the diversion of fluid flow, for example, from one nozzle to another, and further including a ball screw and torque motor attached to the first end of the magnetic member for selective movement thereof fore and aft, with the second end of the magnetic member being tapered and positioned in cooperative relation with respect to an orifice in a fluid inlet member whereby the fore and aft movement of the magnetic member controls the size of the orifice and the amount of fluid flow.
摘要翻译：分流阀和可变节流阀的功能组合在单个阀中，其包括在第一端枢转的细长磁性构件，第二端的一部分位于相对的限制器之间，用于产生磁场的线圈组件为了选择性地将磁性构件拉向限制器中的一个，密封限流器被拉动，从而能够将流体流从例如从一个喷嘴转移到另一个喷嘴，并且还包括附接到第一端的滚珠丝杠和扭矩马达磁性构件的前后选择性地移动，磁性构件的第二端是锥形的并且相对于流体入口构件中的孔定位成协调关系，由此磁性构件的前后运动控制尺寸的孔口和流体的流量。

5. 发明授权

US4856276A Variable mass flow rate solid propellant grain 失效
标题翻译：可变质量流量固体推进剂颗粒
公开(公告)号：US4856276A
公开(公告)日：1989-08-15
申请号：US62531
申请日：1987-06-12
申请人： Mark A. Solberg
发明人： Mark A. Solberg
IPC分类号： F02K9/18 , B64G5/00 , F02K9/12 , F02K9/22 , F02K9/36 , F42B3/04
CPC分类号： F02K9/12 , F02K9/36
摘要： A solid propellant grain for a gas generator such as a missile canister erection actuator. The grain provides a sustain phase followed by a boost phase which may then be followed by another sustain phase. The aft portion of the grain may have the configuration of an end burner to provide the initial sustain phase. The middle portion contains a longitudinally extending cavity in which is disposed a plug for supporting the grain during the initial sustain phase against collapse or cracking. A gap is provided between the plug and the wall of the cavity to provide effective propellant burnign surface area along the cavity wall for the boost phase. The cavity and plug, which terminate at the aft portion, may extend longitudinally through the forward portion of the grain. In order to provide another sustain phase after the boost phase, an insulating inhibitor material is disposed between the plug and the propellant material in the forward portion and is bonded to the propellant material so that the forward portion of the grain becomes an end burner.
摘要翻译：用于气体发生器的固体推进剂颗粒，例如导弹筒安装致动器。晶粒提供维持阶段，随后是升压阶段，然后可以跟随另一维持阶段。颗粒的后部可以具有端部燃烧器的构造以提供初始维持阶段。中间部分包含纵向延伸的空腔，其中设置有用于在初始维持阶段期间支撑颗粒的塞子，以防止塌陷或开裂。在空腔的塞子和壁之间提供间隙，以提供沿着用于升压阶段的腔壁的有效的推进剂燃烧表面积。终止于后部的腔和塞可以纵向延伸穿过谷物的前部。为了在升压阶段之后提供另一个维持阶段，绝缘抑制剂材料设置在前部的塞子和推进剂材料之间，并且被结合到推进剂材料上，使得谷物的前部部分成为端部燃烧器。

6. 发明授权

US06966264B2 Rocket motors with insensitive munitions systems and projectiles including same 有权
标题翻译：具有不灵敏弹药系统的火箭发动机和包括其的射弹
公开(公告)号：US06966264B2
公开(公告)日：2005-11-22
申请号：US10645706
申请日：2003-08-21
申请人： Mark A. Solberg , Robert E. Black
发明人： Mark A. Solberg , Robert E. Black
IPC分类号： F02K9/38 , F42B15/00 , F42B15/10 , F02K9/08
CPC分类号： F02K9/38 , F42B15/00
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。

7. 发明授权

US5363768A Propellant gas-generation system for canister ejection 失效
标题翻译：用于罐喷射的推进剂气体发生系统
公开(公告)号：US5363768A
公开(公告)日：1994-11-15
申请号：US679305
申请日：1991-04-02
申请人： Mark A. Solberg , James A. Hartwell
发明人： Mark A. Solberg , James A. Hartwell
IPC分类号： C06B45/12 , F02K9/14 , F42B5/16 , F42B5/38 , F42B5/00
CPC分类号： C06B45/12 , F02K9/14 , F42B5/16 , F42B5/38
摘要： A propellant system is disclosed which includes a propellant applied to at least one surface of a substrate which is in the form of a strip. The propellant strip is adhesively attached to itself in a configuration which conceals propellant within the configuration and which allows the attached strip to peel away from itself under applied forces thereby resulting in smooth and continuous exposure of propellant for burning. The system is directed to use with ejectable projectiles which are slidably disposed within a canister or casing. The propellant system is interconnected between the projectile and the canister which houses the projectile. The propellant is urged to peel, and thus expose propellant for burning, as the projectile is ejected from the canister.
摘要翻译：公开了一种推进剂系统，其包括施加到条带形式的基底的至少一个表面上的推进剂。推进剂条以其结构隐藏推进剂的结构粘附到自身上，并且允许附着的条在施加的力下从其自身剥离，从而导致推进剂燃烧的平滑和连续的暴露。该系统旨在与可滑动地设置在罐或套管内的可弹出射弹一起使用。推进剂系统在弹丸和容纳射弹的罐之间相互连接。推动剂被迫剥离，从而暴露推进剂燃烧，因为射弹从罐中排出。

8. 发明授权

US5354066A Projectile target 失效
标题翻译：射弹目标
公开(公告)号：US5354066A
公开(公告)日：1994-10-11
申请号：US170711
申请日：1993-12-21
申请人： Dale A. Swanson , Mark A. Solberg
发明人： Dale A. Swanson , Mark A. Solberg
IPC分类号： F41J3/00
CPC分类号： F41J3/0004
摘要： An archery target is disclosed that is formed from multiple front layers formed from a woven material having laterally displaceable strands to permit penetration of an arrowhead, multiple backing layers formed from material which resists penetration of an arrowhead and a plurality of aligned pockets formed between the front and backing layers. Stuffing material such as raw cotton is compressibly forced into each of the pockets resists lateral displacement of the stuffing material upon penetration of an arrowhead and causes the stuffing material to be compressed in front of the arrowhead to effectively stop the arrow.
摘要翻译：公开了一种射箭靶，其由具有横向可移位的股线的织造材料形成的多个前层形成，以允许箭头穿透，由材料形成的多个背衬层，其抵抗箭头的穿透和形成在前面的多个对准的袋和背衬层。诸如原棉的填充材料被可压缩地压入每个袋中，抵抗在箭头穿透时填充材料的横向位移，并使填充材料在箭头前方被压缩以有效地停止箭头。

9. 发明授权

US06619029B2 Rocket motors with insensitive munitions systems 有权
标题翻译：具有不灵敏弹药系统的火箭发动机
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
CPC分类号： F02K9/38 , F42B15/00
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。

10. 发明授权

US5616884A Propellant gas-generation system for canister ejection 失效
标题翻译：用于罐喷射的推进剂气体发生系统
公开(公告)号：US5616884A
公开(公告)日：1997-04-01
申请号：US911941
申请日：1992-07-10
申请人： Mark A. Solberg , James A. Hartwell
发明人： Mark A. Solberg , James A. Hartwell
IPC分类号： C06B45/12 , C06D5/06 , F02K9/14 , F42B5/16 , F42B5/38 , F42B4/06
CPC分类号： F02K9/14 , C06B45/12 , C06D5/06 , F42B5/16 , F42B5/38
摘要： A propellant system is disclosed which includes a propellant applied to at least one surface of a substrate which is in the form of a strip. The propellant strip is adhesively attached to itself in a configuration which conceals propellant within the configuration and which allows the attached strip to peel away from itself under applied forces thereby resulting in smooth and continuous exposure of propellant for burning. The system is directed to use with ejectable projectiles which are slidably disposed within a canister or casing. The propellant system is interconnected between the projectile and the cannister which houses the projectile. The propellant is urged to peel, and thus expose propellant for burning, as the projectile is ejected from the canister. Alternatively, the propellant is telescoped and covered with a sleeve which peels away as the projectile is ejected.
摘要翻译：公开了一种推进剂系统，其包括施加到条带形式的基底的至少一个表面上的推进剂。推进剂条以其结构隐藏推进剂的结构粘附到自身上，并且允许附着的条在施加的力下从其自身剥离，从而导致推进剂燃烧的平滑和连续的暴露。该系统旨在与可滑动地设置在罐或套管内的可弹出射弹一起使用。推进剂系统在射弹和容纳射弹的罐之间相互连接。推动剂被迫剥离，从而暴露推进剂燃烧，因为射弹从罐中排出。或者，推进剂被套叠并用套筒覆盖，当弹丸被弹出时，推进剂被剥去。

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