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1. 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。

2. 发明授权

US5654522A Plume enhancement nozzle for achieving flare rotation 失效
标题翻译：羽流增强喷嘴用于实现火炬旋转
公开(公告)号：US5654522A
公开(公告)日：1997-08-05
申请号：US495716
申请日：1995-06-27
申请人： David W. Endicott, Jr. , Ross W. Guymon , Ralph S. Tappan, II
发明人： David W. Endicott, Jr. , Ross W. Guymon , Ralph S. Tappan, II
IPC分类号： F42B4/26 , F42B10/06 , F42B10/30 , F42B4/06
CPC分类号： F42B10/30 , F42B10/06 , F42B4/26
摘要： An aerodynamically stable, kinematic flare having an enhanced plume signature is disclosed. The flare includes a housing with a flare illuminant disposed within the housing. A primary nozzle is configured in the aft wall of the housing. Four secondary nozzles are configured in the aft end of the side wall of the housing and are positioned aft of the center of gravity of the flare. At least two of the secondary nozzles comprise off-center nozzles having a longitudinal axis which does not extend through the longitudinal axis of the flare. A shroud is attached to the housing and deploys to an extended position upon combustion of the illuminant. The shroud is configured with holes which correspond in size and position to each of the secondary nozzles when the shroud is in its extended position. The primary and secondary nozzles are sized and positioned to spin stabilize the flare during combustion of the illuminant.
摘要翻译：公开了具有增强的羽流签名的空气动力学稳定的运动火炬。火炬包括具有设置在壳体内的耀斑光源的壳体。主喷嘴配置在壳体的后壁上。四个二次喷嘴构造在壳体的侧壁的后端，并且位于火炬重心的后方。至少两个次级喷嘴包括偏心中心喷嘴，其具有不延伸穿过火炬的纵向轴线的纵向轴线。护罩附接到壳体并且在发光体燃烧时展开到延伸位置。当护罩处于其延伸位置时，护罩被配置有在尺寸和位置上对应于每个次级喷嘴的孔。主喷嘴和次喷嘴的尺寸和位置可以在发光体的燃烧期间旋转稳定火炬。

3. 发明授权

US5648556A Synthesis of bis(2,2-dinitropropyl)acetal (BDNPA) 失效
标题翻译：双（2,2-二硝基丙基）缩醛（BDNPA）的合成
公开(公告)号：US5648556A
公开(公告)日：1997-07-15
申请号：US339138
申请日：1994-11-14
申请人： R. Scott Hamilton , Robert B. Wardle
发明人： R. Scott Hamilton , Robert B. Wardle
IPC分类号： C07C201/12 , C07B61/00 , C07C205/29 , C07C41/50 , C07C43/30
CPC分类号： C07C201/12
摘要： A nonsolvent process of synthesizing bis(2,2-dinitropropyl)acetal (BDNPA) is disclosed. In the process, 2,2-dinitropropanol (DNPOH) is reacted at low temperature with an acetaldehyde source in the presence of an acid catalyst, such as a Lewis acid catalyst or protic acid catalyst. To inhibit by product formation, the reaction temperature is maintained from about -30.degree. C. to 30.degree. C. Upon completion of the reaction, the reaction solution is quenched with water and washed with an aqueous hydroxide solution. The hydroxide concentration should be sufficient to neutralize any acid formed during the quenching step and to solubilize unreacted 2,2-dinitropropanol as well as other aqueous soluble byproducts in the reaction solution. The BDNPA product is extracted with methyl tert-butyl ether (MTBE) or equivalent solvent. The organic solvent is evaporated to yield usable BDNPA product. The resulting yield is at least 50% based on the starting quantity of 2,2-dinitropropanol.
摘要翻译：公开了合成双（2,2-二硝基丙基）缩醛（BDNPA）的非溶剂方法。在此过程中，在酸催化剂如路易斯酸催化剂或质子酸催化剂存在下，将2,2-二硝基丙醇（DNPOH）在低温下与乙醛源反应。为了抑制产物形成，将反应温度保持在约-30℃至30℃。反应完成后，将反应溶液用水淬灭并用氢氧化钠水溶液洗涤。氢氧化物浓度应足以中和淬灭步骤中形成的任何酸，并将未反应的2,2-二硝基丙醇以及其他水溶性副产物溶解在反应溶液中。用甲基叔丁基醚（MTBE）或等效溶剂萃取BDNPA产物。将有机溶剂蒸发，得到可用的BDNPA产物。基于2,2-二硝基丙醇的起始量，所得产率为至少50％。

4. 发明授权

US5639984A Infrared tracer compositions 失效
标题翻译：红外示踪剂组合物
公开(公告)号：US5639984A
公开(公告)日：1997-06-17
申请号：US651617
申请日：1996-05-22
申请人： Daniel B. Nielson
发明人： Daniel B. Nielson
IPC分类号： C06B43/00 , C06C15/00 , F42B4/26
CPC分类号： C06B43/00 , C06C15/00 , Y10S149/116
摘要： Convert infrared tracer compositions are provided. The compositions are formed using peroxide such as strontium peroxide and barium peroxide. Added to these materials is a burn rate catalyst such as boron, iron oxide, cupric oxide, manganese dioxide, carbon, silicon, graphite fibrils, amorphous silica, copper oxide, potassium dodecaborate, the dipotassium salt of bitetrazole amine, and the potassium salt of dilituric acid. The composition also includes alkali metal compounds in order to enhance the infrared emissions. The compositions are bound together using a binder such that the composition results in a granular material having a mean particle size in the range of from about 500.mu. to about 800.mu..
摘要翻译：提供了转换红外示踪剂组合物。使用过氧化物如过氧化锶和过氧化钡形成组合物。添加到这些材料中的是燃烧速率催化剂，例如硼，氧化铁，氧化铜，二氧化锰，碳，硅，石墨原纤，无定形二氧化硅，氧化铜，十二硼酸钾，四唑硼酸二钾盐， d ic酸。该组合物还包括碱金属化合物以增强红外发射。使用粘合剂将组合物结合在一起，使得组合物得到平均粒度在约500μm至约800μm范围内的颗粒材料。

5. 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。

6. 发明授权

US5610364A Nozzle plug for plume enhancement in a kinematic flare 失效
标题翻译：喷嘴塞，用于在运动弹道中增强羽流
公开(公告)号：US5610364A
公开(公告)日：1997-03-11
申请号：US497277
申请日：1995-06-30
申请人： David W. Endicott, Jr. , Ross W. Guymon , James R. Kaminska
发明人： David W. Endicott, Jr. , Ross W. Guymon , James R. Kaminska
IPC分类号： F42B4/26 , F42B12/70 , F42C19/08 , F42B12/48 , F42B4/04
CPC分类号： F42C19/0807 , F42B12/70 , F42B4/26
摘要： A decoy flare is disclosed which includes illuminant disposed within a housing. A shroud is slidably attached to the housing for deployment from a retracted position to an extended position. A plug is attached to the aft end of the shroud and is configured with a radially beveled, nozzle-contacting surface. The plug is positioned and configured to sealingly engage the nozzle when the shroud is in the retracted position and to disengage the nozzle upon deployment of the shroud to the extended position. The plug is configured with a plume-contacting surface positioned at an angle to the path of the plume when the shroud is in the extended position for enhancing the cross-sectional area of the plume of the flare.
摘要翻译：公开了一种引诱装置，其包括设置在壳体内的发光体。护罩可滑动地附接到壳体，用于从缩回位置展开到延伸位置。插头附接到护罩的后端，并且构造为具有径向倾斜的喷嘴接触表面。塞子定位和构造成当护罩处于缩回位置时密封地接合喷嘴，并且在将护罩展开到延伸位置时使塞子脱离接头。当护罩处于延伸位置时，塞子构造有与羽流的路径成一定角度的羽流接触表面，以增强火炬的羽流的横截面积。

7. 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.

8. 发明授权

US5554820A High solids rocket motor propellants using diepoxy curing agents 失效
标题翻译：使用二环氧固化剂的高固体火箭发动机推进剂
公开(公告)号：US5554820A
公开(公告)日：1996-09-10
申请号：US406573
申请日：1995-03-20
申请人： Robert B. Wardle , R. Scott Hamilton
发明人： Robert B. Wardle , R. Scott Hamilton
IPC分类号： C06B45/10
CPC分类号： C06B45/10
摘要： A PBAN-based solid rocket motor propellant which includes more than 85% or more solids is provided. Propellants of this nature are possible using the combination of diepoxide curing agents and PBAN as a binder. The curing agents include diepoxides having 4 to about 10 carbon atoms. It has been observed that when a diepoxide curing agent is substituted for conventional curing agents, viscosities are significantly reduced, thus enabling the addition of higher percentages of solids in the propellant formulation. Total solids loading of over 85% are achievable while maintaining end-of-mix viscosities within acceptable ranges.
摘要翻译：提供了一种包含超过85％或更多固体的PBAN固体火箭发动机推进剂。这种性质的推进剂可以使用二环氧化物固化剂和PBAN作为粘合剂的组合。固化剂包括具有4至约10个碳原子的二环氧化物。已经观察到，当二环氧化物固化剂代替常规固化剂时，粘度显着降低，因此能够在推进剂制剂中添加更高百分比的固体。总固体含量超过85％是可以实现的，同时保持混合后的粘度在可接受的范围内。

9. 发明授权

US5540794A Energetic binder and thermoplastic elastomer-based low vulnerability ammunition gun propellants with improved mechanical properties 失效
标题翻译：具有改善机械性能的能量粘合剂和基于热塑性弹性体的低脆弱性弹药枪推进剂
公开(公告)号：US5540794A
公开(公告)日：1996-07-30
申请号：US880191
申请日：1992-05-11
申请人： Rodney L. Willer , Dennis J. Park
发明人： Rodney L. Willer , Dennis J. Park
IPC分类号： C06B45/10
CPC分类号： C06B45/105 , C06B45/10
摘要： An energetic binder system useful for making TPE-LOVA propellants and energetic composites comprises at least one thermoplastic elastomer, at least one plasticizer, and nitrocellulose.
摘要翻译：用于制备TPE-LOVA推进剂和能量复合材料的能量粘合剂体系包含至少一种热塑性弹性体，至少一种增塑剂和硝化纤维素。

10. 发明授权

US5511914A Propellant grain machining device and method 失效
标题翻译：推进剂谷物加工装置及方法
公开(公告)号：US5511914A
公开(公告)日：1996-04-30
申请号：US388249
申请日：1995-02-14
申请人： Paul W. Hoekstra
发明人： Paul W. Hoekstra
IPC分类号： B23C3/00 , B23Q11/00 , F02K9/24
CPC分类号： F02K9/24 , B23C3/00 , B23Q11/0046 , Y02P70/171 , Y10T407/1902 , Y10T407/195 , Y10T408/91 , Y10T408/98 , Y10T409/303808 , Y10T409/304088 , Y10T409/304424 , Y10T409/30756 , Y10T409/307784 , Y10T409/309576
摘要： An apparatus for cutting a path of propellant grain away from a solid rocket motor. The apparatus includes a telescoping arm connected to a rotatable body. A cutting tool having a primary and secondary cutter is connected to a distal end of the telescoping arm. The secondary cutter is disposed adjacent the primary cutter and configured to make cuts through the portion of propellant grain along the path such that the grain is cut away from the rocket motor in a plurality of pieces. The telescoping arm includes a plurality of interconnected extendable concentric cylinders configured with a plurality of ball/spring detents each bearing a resistance load for restraining one of the concentric cylinders such that the innermost unextended of said concentric cylinders extends prior to the extension of any other of said unextended concentric cylinders.
摘要翻译：一种用于切割远离固体火箭发动机的推进剂颗粒的路径的装置。该装置包括连接到可旋转主体的伸缩臂。具有初级和次级切割器的切割工具连接到伸缩臂的远端。辅助切割器设置在主切割器附近，并且构造成沿着路径切割穿过推进剂颗粒的部分，使得颗粒以多个片段从火箭发动机切除。伸缩臂包括多个相互连接的可延伸的同心圆柱体，其被构造成具有多个球/弹簧棘爪，每个球/弹簧棘爪均承受用于约束同心圆柱体之一的阻力载荷，使得所述同心圆柱体的最内部未延伸部分在扩展之前延伸所述未延伸的同心圆柱体。

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