公开(公告)号：USH1824H

公开(公告)日：1999-12-07

申请号：US912969

申请日：1997-08-01

申请人： Paul T. Johnsen ,  Alfred O. Smith ,  Robert B. Dillinger

发明人： Paul T. Johnsen ,  Alfred O. Smith ,  Robert B. Dillinger

IPC分类号： B05D7/24 ,  C06B21/00 ,  C06B45/12 ,  C23C16/00

CPC分类号： B05D1/60 ,  C06B21/0083 ,  C06B45/12

摘要： A thin film of ignition inhibitor is applied uniformly to a rocket propelt grain which may be large and have a complex shape. The film is applied by condensation and polymerization of a vaporized monomer to which the grain is subjected. The monomer is prepared by thermally cracking the dimer of paraxylylene or a halogenated paraxylylene derivative.

摘要翻译： 点火抑制剂的薄膜均匀地施加到可能很大并且具有复杂形状的火箭推进剂颗粒上。 该薄膜通过使谷物所经受的气化单体的冷凝和聚合而被施加。 单体通过热裂解对二甲苯或二卤代对二甲苯衍生物的二聚体来制备。

公开(公告)号：US5996501A

公开(公告)日：1999-12-07

申请号：US148906

申请日：1997-08-27

申请人： Arthur F. Spencer ,  John D. Corley

发明人： Arthur F. Spencer ,  John D. Corley

IPC分类号： F42B1/00

CPC分类号： C06B45/12 ,  F42B1/00

摘要： A dual explosive charge is described that simultaneously enhances blast and fragmentation characteristics of the charge, including an inner driven charge of a non-ideal explosive surrounded by an outer charge sleeve of a more nearly ideal explosive, detonation of the outer charge resulting in an extremely high temperature, high pressure environment that accelerates reaction kinetics in the inner charge, resulting in enhanced blast and fragmentation performance of the explosive charge.

摘要翻译： 描述了一种双重爆炸装置，其同时增强了电荷的爆炸和碎裂特性，包括由外部电荷引起的更接近理想的爆炸物的外部电荷套筒包围的非理想爆炸物的内部驱动电荷导致极端的电荷 高温，高压的环境，加速了内部电荷的反应动力学，导致炸药的爆炸和碎裂性能增强。

公开(公告)号：US5767221A

公开(公告)日：1998-06-16

申请号：US448825

申请日：1995-05-24

申请人： Larry W. Poulter ,  Ronald W. Nelson ,  Robert B. Smalley, Jr. ,  Marvin C. Hawkins

发明人： Larry W. Poulter ,  Ronald W. Nelson ,  Robert B. Smalley, Jr. ,  Marvin C. Hawkins

IPC分类号： C06B21/00 ,  C06B45/12 ,  C08G18/18 ,  C08G18/65 ,  C08G18/75 ,  C08G18/76 ,  F02K9/34 ,  C08G18/16

CPC分类号： C08G18/1875 ,  C06B21/0083 ,  C06B45/12 ,  C08G18/6594 ,  C08G18/751 ,  C08G18/765 ,  F02K9/346

摘要： A robust polyurethane liner is disclosed for solid propellant rocket motors which is insensitive to large variations in stoichiometry, exhibits increased cohesive strength and, when used in combination with a unique two coat (wet coat) liner process described below, modifies the ballistic properties of the adjacent interfacial propellant layer. The liner compositions include a polymeric binder having a plurality of reactive hydroxyl functional groups and a curing agent having a plurality of reactive isocyanate functional groups. The quantity of binder and curing agent is selected such that the NCO/OH ratio is in the range from 1.5 to 4.5. Diisocyanate curing agents are particularly useful. A bonding agent, such as a polyfunctional aziridine compound, is typically present in the liner composition in an amount ranging from about 3% to about 5%, by weight. An oligomer catalyst is included in the liner composition in an amount ranging from about 15% to about 50%, by weight. Diammonium phosphate ((NH.sub.4).sub.2 HPO.sub.4) functions as an oligomer catalyst and as a ballistic modifier to inhibit propellant burn rate when the liner is cured concurrently with the propellant. A colorant, such as rhodamine B, may optionally be included to assist in determining coverage or thickness of the liner coating.

公开(公告)号：US5690868A

公开(公告)日：1997-11-25

申请号：US744392

申请日：1996-11-07

申请人： Bernard Strauss ,  Thelma Manning ,  Joseph P. Prezelski ,  Sam Moy

发明人： Bernard Strauss ,  Thelma Manning ,  Joseph P. Prezelski ,  Sam Moy

IPC分类号： C06B45/00 ,  C06B45/10 ,  C06B45/12 ,  C06B21/00

CPC分类号： C06B45/105 ,  C06B45/00 ,  C06B45/12

摘要： A multi-layer propellant and a method for making the same is provided, in ich the propellant has at least one slow burning formulation and at least one fast burning formulation, such that the ratio of these burning rates is at least 2:1. The propellant produces an impetus of at least 1300 Joules/gm. The preferred binder is a high energy oxetane thermoplastic elastomer. The preferred slow burning formulation employs RDX, while the preferred fast burning formulation employs CL-20. The two formulations are formed separately, such as in layers that are then fused, using the bonding strength of the binder. The shape may be any shape that is useful in munitions and may include one or many layers of each burning rate. Preferred shapes include a multi-layered propellant with one slow burning formulation on top and a bottom layer of the fast burning formulation. The layers may be formed from ribbons, discs, cones, truncated cones and partial spheres. The amount of binder in each formulation should be sufficient to provide a uniformly dispersed oxidizer throughout the layer. Preferred amounts of binder range from about five percent to about thirty percent by weight, based on the total weight of the propellant.

摘要翻译： 提供了多层推进剂及其制备方法，其中推进剂具有至少一种缓慢燃烧制剂和至少一种快速燃烧制剂，使得这些燃烧速率的比例至少为2:1。 推进剂产生至少1300焦耳/克的推动力。 优选的粘合剂是高能氧杂环丁烷热塑性弹性体。 优选的缓慢燃烧制剂采用RDX，而优选的快速燃烧配方采用CL-20。 两种制剂分别形成，例如使用粘合剂的粘合强度然后熔化的层。 形状可以是在弹药中有用的任何形状，并且可以包括每个燃烧速率的一层或多层。 优选的形状包括在快速燃烧制剂的顶部和底层上具有一种缓慢燃烧制剂的多层推进剂。 这些层可以由带状物，圆盘，锥体，截锥体和局部球体形成。 每种制剂中粘合剂的量应足以在整个层中提供均匀分散的氧化剂。 基于推进剂的总重量，粘合剂的优选量为约5重量％至约30重量％。

公开(公告)号：US5682009A

公开(公告)日：1997-10-28

申请号：US635852

申请日：1996-04-22

申请人： William L. O'Meara ,  Terry A. Murray

发明人： William L. O'Meara ,  Terry A. Murray

IPC分类号： C06B21/00 ,  C06B25/18 ,  C06B45/12 ,  C06B45/22 ,  C06B45/00

CPC分类号： C06B21/0016 ,  C06B25/18 ,  C06B45/12 ,  C06B45/22

摘要： There is disclosed a propellent having a deterred burn rate. The propellent is a particulate containing an energetic binder base and a thermoplastic burn deterrent. The energetic binder has in impetus (energy) in excess of 200,000 foot pounds per pound (mass) and the thermoplastic burn deterrent is both a solid at room temperature and soluble in an organic solvent. The burn deterrent is gradationally dispersed within the particulate with the greatest concentration of burn deterrent at the particulate periphery.

摘要翻译： 公开了具有阻止燃烧速率的推进剂。 推进剂是含有能量粘合剂基质和热塑性烧伤威慑物的颗粒。 能量粘合剂的动力（能量）超过20万磅磅/磅（质量），热塑性燃烧威慑物在室温下均为固体，并溶于有机溶剂。 烧伤威慑力逐渐分散在颗粒周围的最大程度的燃烧威慑浓度的颗粒内。

公开(公告)号：US5501751A

公开(公告)日：1996-03-26

申请号：US351672

申请日：1994-12-08

申请人： Alfonso L. Baldi ,  Frank J. Clark

发明人： Alfonso L. Baldi ,  Frank J. Clark

IPC分类号： C06B45/12 ,  C06C15/00 ,  C06B45/14

CPC分类号： C06B45/12 ,  C06C15/00

摘要： The present invention is directed to the encapsulation of pyrophoric materials in a high temperature resistant membrane having at least one perforation which allows air to contact the pyrophoric material. By controlling the accessibility of the pyrophoric material to the surrounding air, it is possible to reduce the kinetics of the oxidation reaction without affecting the thermodynamics of the reaction. This results in a product that demonstrates a lower peak temperature, longer dwell time at the lower temperature and, in most cases, an increase in the total heat energy output in comparison to an identical pyrophoric material that is not so encapsulated.

摘要翻译： 本发明涉及将自燃材料包封在耐高温膜中，其具有允许空气与自燃材料接触的至少一个穿孔。 通过控制发火材料对周围空气的可及性，可以降低氧化反应的动力学而不影响反应的热力学。 这导致产品在较低的温度下表现出更低的峰值温度，更长的停留时间，并且在大多数情况下，与未被包封的相同的发火材料相比，总热能输出的增加。

公开(公告)号：US5398612A

公开(公告)日：1995-03-21

申请号：US14949

申请日：1987-02-17

申请人： William H. Graham ,  Robert E. Askins ,  Robert L. Stanley

发明人： William H. Graham ,  Robert E. Askins ,  Robert L. Stanley

IPC分类号： C06B23/00 ,  C06B45/12 ,  F02K9/34 ,  C06D5/06 ,  C06B45/10

CPC分类号： F02K9/346 ,  C06B23/006 ,  C06B45/12

摘要： Compositions and methods for increasing the storage life of a propellant grain by reducing the rate of decomposition of its nitrate ester components. A nitrate ester stabilizer is placed in a layer adjacent to a nonburning surface of the propellant grain. The stabilizer migrates from the layer into the grain's nonburning surface to provide additional stabilization for the entire grain, especially portions of the grain adjacent to the protected nonburning surface.

摘要翻译： 通过降低其硝酸酯组分的分解速率来增加推进剂颗粒的储存寿命的组合物和方法。 将硝酸酯稳定剂置于邻近推进剂颗粒的非燃烧表面的层中。 稳定剂从层移动到谷物的不燃表面，为整个晶粒，特别是与受保护的不燃烧表面相邻的颗粒部分提供额外的稳定性。

公开(公告)号：US5237928A

公开(公告)日：1993-08-24

申请号：US870235

申请日：1992-04-20

申请人： Klaus Redecker

发明人： Klaus Redecker

IPC分类号： C06B45/12 ,  F42B5/192

CPC分类号： F42B5/192 ,  C06B45/12

摘要： Combustible cartridge shells have cylindrical walls formed of combustible material. The walls comprise one or more wraps or windings of textile fibers, which are bound together with bonding agents having propellant charge characteristics. The bonding agents comprise either a mixture of polymers and explosives with decomposition temperatures above 180.degree. C. or a mixture of polymeric nitro-aromatic compounds which have two or more nitro groups per aromatic nucleus and also have a decomposition temperature above 180.degree. C. Mixtures of these two bonding agents may also be used to form the cylindrical wall of the combustible cartridge shell. The cartridge shells have inherently stable walls with a high mechanical resistance and are unaffected by changes in temperature up to 240.degree. C. Advantageously, these shells burn practically free of any residuals.

摘要翻译： 可燃筒体具有由可燃材料形成的圆柱形壁。 这些壁包括纺织纤维的一个或多个包装或卷绕物，其与具有推进剂充电特性的粘合剂结合在一起。 粘合剂包括分解温度高于180℃的聚合物和爆炸物的混合物，或每个芳香核具有两个或多个硝基并且还具有高于180℃的分解温度的聚合硝基芳族化合物的混合物。混合物 这两种粘结剂也可用于形成可燃筒壳体的圆柱形壁。 盒壳具有固有的稳定的壁，具有高的机械阻力，并且不受温度变化高达240℃的影响。有利地，这些壳实际上不含任何残留物。

公开(公告)号：US5085725A

公开(公告)日：1992-02-04

申请号：US564897

申请日：1990-08-06

申请人： David C. Sayles

发明人： David C. Sayles

IPC分类号： C06B21/00 ,  C06B45/12 ,  F02K9/24 ,  F02K9/34

CPC分类号： C06B45/12 ,  C06B21/0083 ,  F02K9/24 ,  F02K9/346 ,  Y10T428/31536

摘要： The trimer of 1,6-hexanediisocyanate, which has the chemical name in acconce with (International Union of Pure and Applied Chemistry) (IUPAC) nomenclature of 7-aza-8-oxo-7[1-isocyanato-6-oxohexyl]pentadecanediisocyanate, is employed in a method of chemical bonding of solid propellant grains to the internal insulation of an interceptor motor. Both the propellant composition and the insulation are chemically reactive with the trimmer identified hereinabove. The method comprises providing a solid propellant rocket motor case having the internal insulation installed therein. Following degreasing of the insulation outer surface, the trimer identified hereinabove is spray coated onto the insulation, and the solid propellant composition is placed onto the trimer. A chemical bond is formed between the propellant and the trimer and the insulation to achieve the chemical bonding of an isocyanate curable solid propellant composition to the internal insulation. The insulation employed in the preferred embodiment is formulated with ethylene-propylene-diene monomer prepolymer, peroxide-cured, and plasticized with 9% dioctyl sebacate. The propellant composition is cast onto the spray coated insulation surface where the chemical insulation-to-polyisocyanate-to-propellant bond is achieved which shows superior tensile, shear, and peel strength when compared to conventional insulation-liner-propellant bonding by prior art.

摘要翻译： 1,6-己二异氰酸酯的三聚体，其化学名称符合（International Union of Pure and Applied Chemistry）（IUPAC）7-氮杂-8-氧代-7 [1-异氰酸基-6-氧己基]十五碳二异氰酸酯的命名法 用于将固体推进剂颗粒与拦截器电机的内部绝缘体化学粘合的方法。 推进剂组合物和绝缘体都与上文所确定的修剪剂发生化学反应。 该方法包括提供其中安装有内部绝缘体的固体推进剂火箭发动机壳体。 在绝缘外表面脱脂之后，将上述鉴定的三聚体喷涂在绝缘体上，并将固体推进剂组合物置于三聚体上。 在推进剂和三聚体之间形成化学键，并且形成绝缘体以实现异氰酸酯可固化的固体推进剂组合物与内部绝缘体的化学键合。 在优选实施方案中使用的绝缘体用乙烯 - 丙烯 - 二烯单体预聚物配制，过氧化物固化，并用9％癸二酸二辛酯增塑。 将推进剂组合物浇铸到喷涂的绝缘表面上，其中与现有技术的传统绝缘衬垫推进剂粘合相比，实现了与绝缘 - 聚异氰酸酯 - 推进剂结合的化学绝缘 - 聚异氰酸酯 - 推进剂粘合，其显示出优异的拉伸，剪切和剥离强度。

公开(公告)号：US5042385A

公开(公告)日：1991-08-27

申请号：US460682

申请日：1983-01-24

申请人： Russell Reed, Jr. ,  May L. Chan

发明人： Russell Reed, Jr. ,  May L. Chan

IPC分类号： C06B45/12 ,  F02K9/34

CPC分类号： F02K9/346 ,  C06B45/12

摘要： A flame inhibitor coating for application to those surfaces of a solid prllant grain in a rocket motor where burning is not desired such as the aft end of a perforated propellant grain which includes a barrier layer of a mixture of amine silane, a trialkoxypropylsilylamino prepolymer, and diglycidylether of polypropylene glycol, an epoxy applied to the grain surface and allowed to cure to a polysiloxane layer, and a flame inhibitor layer applied over the barrier layer consisting of a mixture of hydroxyl terminated polybutadiene and dimeryl diisocyanate with flake aluminum which is applied over the barrier layer and allowed to cure. The barrier layer prevents migration of nitrate esters from the solid propellant grain to the flame inhibitor layer thus preventing peeling and reduction of flame inhibiting properties. The polysiloxane barrier layer is also useful in itself as a flame inhibitor and can also be employed between the insulator/liner of the rocket motor and the solid propellant grain.

摘要翻译： 用于火箭发动机的固体推进剂颗粒的那些表面的阻燃剂涂层，其中不需要燃烧，例如穿孔推进剂颗粒的后端，其包括胺硅烷，三烷氧基丙基甲硅烷基氨基预聚物和三烷氧基丙基甲硅烷基氨基预聚物的混合物的阻挡层和 聚丙二醇的二缩水甘油醚，施加到晶粒表面并使其固化成聚硅氧烷层的环氧树脂，以及施加在由羟基封端的聚丁二烯和二聚二异氰酸酯的混合物组成的阻挡层上的阻燃层， 阻挡层并允许固化。 阻挡层防止硝酸酯从固体推进剂颗粒向阻燃剂层迁移，从而防止阻燃性能的剥离和降低。 聚硅氧烷阻挡层本身也可用作阻燃剂，也可用于火箭发动机的绝缘体/内衬与固体推进剂颗粒之间。