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    NITROGLYCERINE-FREE MULTI-PERFORATED HIGH-PERFORMING PROPELLANT SYSTEM
    1.
    发明公开
    NITROGLYCERINE-FREE MULTI-PERFORATED HIGH-PERFORMING PROPELLANT SYSTEM 审中-公开
    NITROGLYZERINFREIES，MEHRFACH PERFORIERTES，LEISTUNGSSTARKES ANTRIEBSSYSTEM

    公开(公告)号：EP2756259A2

    公开(公告)日：2014-07-23

    申请号：EP11764667.9

    申请日：2011-09-15

    申请人： Nitrochemie Wimmis AG

    发明人： SCHAEDELI, Ulrich ,  ANTENEN, Dominik ,  VAMOS, Attila

    IPC分类号： F42B5/16 ,  C06B25/34 ,  C06B25/18 ,  C06B45/00 ,  C06B45/10 ,  C06B45/12

    CPC分类号： F42B5/16 ,  B29C48/0022 ,  B29C48/11 ,  B29C2793/009 ,  B29K2001/18 ,  B29K2105/0005 ,  B29K2105/0038 ,  B29K2995/0094 ,  B29L2031/737 ,  B29L2031/777 ,  C06B25/18 ,  C06B25/34 ,  C06B45/00 ,  C06B45/105 ,  C06B45/12 ,  G06Q99/00

    摘要： The propulsion system for the acceleration of projectiles is based on a multi-perforated grain propellant and is composed from nitrocellulose, a crystalline energy carrier of a nitramine type and an inert plasticizing additive. The number of perforations is 2 to 6, preferably 4. The propellant grains can have round or polygonic profiles, depending on the number of perforations. The preferred grain geometry is cubic with a rectangular grain profile. The nitramine compound contains a structural element of the general chemical structure formula R—N—NO2, where R is a residual group. The nitramine compound is present in a concentration in the range from 0 to 35% by mass, in particular in the range from 5 to 25% by mass. The nitramine compound is preferably RDX. The inert plasticizing additive is a water-insoluble polyoxo compound, if necessary in combination with a substance containing carboxyl groups. In layers near the surface an increased concentration can be present. The inert plasticizing additive is present in a concentration of 0 to 10% by mass, preferred 0 to 5% by mass.

    摘要翻译： 用于加速抛射体的推进系统基于多孔颗粒推进剂，由硝化纤维素，硝胺型结晶能载体和惰性塑化添加剂组成。 穿孔的数量为2至6，优选4.推进剂颗粒可以具有圆形或多角形轮廓，这取决于穿孔的数量。 优选的晶粒几何形状是具有矩形晶粒轮廓的立方体。 硝胺化合物含有一般化学结构式R-N-NO 2的结构元素，其中R为残基。 硝胺化合物的浓度范围为0〜35质量％，特别是5〜25质量％。 硝胺化合物优选为RDX。 惰性塑化添加剂是必需时与含羧基的物质组合的水不溶性聚氧化合物。 在靠近表面的层中，可以存在增加的浓度。 惰性增塑添加剂的浓度为0〜10质量％，优选为0〜5质量％。

    INTEGRAL COMPOSITE ROCKET MOTOR DOME/NOZZLE STRUCTURE
    3.
    发明公开
    INTEGRAL COMPOSITE ROCKET MOTOR DOME/NOZZLE STRUCTURE 审中-公开
    整体复合材料火箭发动机穹顶/喷嘴结构

    公开(公告)号：EP2155546A1

    公开(公告)日：2010-02-24

    申请号：EP08829152.1

    申请日：2008-05-21

    申请人： Raytheon Company

    发明人： FACCIANO, Andrew B. ,  MOORE, Robert T. ,  SINNOCK, Kelly J. ,  CALDWELL, Scott T.

    IPC分类号： B63H11/00

    CPC分类号： F02K9/97 ,  B29C70/28 ,  B29K2079/08 ,  B29K2307/00 ,  B29K2309/08 ,  B29K2995/0015 ,  B29L2031/777 ,  F05D2300/2102 ,  F05D2300/211 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/614

    摘要： An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.

    摘要翻译： 整体复合火箭发动机喷嘴（100）。 所述新型喷嘴（100）包括第一增强材料（110）的第一层，第二增强材料（112）的第二层以及围绕所述第一和第二增强材料（110,112）的共同基体材料（116） ），使得加强材料（110,112）和基体材料（116）形成单个整体复合结构。 在说明性实施例中，第一增强材料（110）包括用于提供结构支撑的石墨纤维，并且第二增强材料（112）包括用于在第一层（110）的第一侧提供热绝缘的玻璃或石英纤维。 喷嘴（100）还可以包括用于在第一层（110）的第二侧上提供热绝缘的第三增强材料（114）的第三层。 在优选实施例中，第一层（110）被成形为形成一体化的圆顶和喷嘴结构。

    Fabricating large, thick wall, tubular structures
    6.
    发明公开
    Fabricating large, thick wall, tubular structures 失效
    生产大，厚壁管状结构。

    公开(公告)号：EP0087851A2

    公开(公告)日：1983-09-07

    申请号：EP83300046.6

    申请日：1983-01-05

    申请人： HERCULES INCORPORATED

    发明人： Gill, Dee Richard ,  Hikida, Edward Theodore ,  Radice, Daniel Michael

    IPC分类号： B29C53/60 ,  B29C53/84

    CPC分类号： B29C53/845 ,  B29C53/821 ,  B29L2031/7126 ,  B29L2031/777

    摘要： This invention relates to an improvement in filament winding large, hollow, tubular structures having significant axial reinforcement in their thick walls by means including (a) using a hollow, light weight mandrel adapted to expand radially at elevated temperatures and windings of alternate layers of filamentary materials positioned substantially axially and substantially circumferentially relative to the longitudinal axis of the mandrel wherein the alternate layers are preferably in a certain thermosettable resin matrix and wound in certain fashion and (b) heating the filament wound mandrel to cure the thermosettable resin wherein heat from inside and out of the mandrel controls the cure and expansion during the heating step. The thick walls preferably incorporate graphite fibers for significant strength in the reinforcement provided by the filamentary materials.

    INTEGRAL COMPOSITE ROCKET MOTOR DOME/NOZZLE STRUCTURE
    7.
    发明公开
    INTEGRAL COMPOSITE ROCKET MOTOR DOME/NOZZLE STRUCTURE 审中-公开
    整体式复合摩托车/喷嘴结构

    公开(公告)号：EP2155546A4

    公开(公告)日：2016-07-20

    申请号：EP08829152

    申请日：2008-05-21

    申请人： RAYTHEON CO

    发明人： FACCIANO ANDREW B ,  MOORE ROBERT T ,  SINNOCK KELLY J ,  CALDWELL SCOTT T

    IPC分类号： B63H11/00 ,  B29C70/28 ,  B29K79/00 ,  B29K307/00 ,  B29K309/08 ,  B29L31/00 ,  F02K9/97

    CPC分类号： F02K9/97 ,  B29C70/28 ,  B29K2079/08 ,  B29K2307/00 ,  B29K2309/08 ,  B29K2995/0015 ,  B29L2031/777 ,  F05D2300/2102 ,  F05D2300/211 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/614

    摘要： An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.

    摘要翻译： 整体复合火箭发动机喷嘴。 新型喷嘴包括第一增强材料层，第二增强材料层和围绕第一和第二增强材料的共同基体材料，使得增强材料和基体材料形成单个整体复合结构。 在说明性实施例中，第一增强材料包括用于提供结构支撑的石墨纤维，并且第二增强材料包括用于在第一层的第一侧上提供热绝缘的玻璃或石英纤维。 喷嘴还可以包括用于在第一层的第二侧上提供热绝缘的第三增强材料的第三层。 在优选实施例中，第一层被成形为形成一体的圆顶和喷嘴结构。

    STAB-RESISTANT BALLISTIC-RESISTANT MATERIAL AND PRODUCTION PROCESS THEREOF
    10.
    发明公开
    STAB-RESISTANT BALLISTIC-RESISTANT MATERIAL AND PRODUCTION PROCESS THEREOF 有权
    STICH- UND SCHUSSFESTES材料SOWIE VERFAHREN ZU SEINER HERSTELLUNG

    公开(公告)号：EP2433790A1

    公开(公告)日：2012-03-28

    申请号：EP10790338.7

    申请日：2010-05-20

    申请人： Hunan Zhongtai Special Equipment Co., Ltd.

    发明人： YANG, Nianci ,  WU, Zhiquan ,  LIN, Mingqing ,  WU, Chuanqing ,  GAO, Bo ,  ZHOU, Yunbo ,  LIN, Haijun ,  ZHANG, Yuanjun ,  ZHOU, Wanqi ,  GUO, Yong

    IPC分类号： B32B5/26 ,  B29C70/00 ,  F41H5/04

    CPC分类号： F41H5/0485 ,  B29C70/202 ,  B29K2995/0089 ,  B29L2031/4842 ,  B29L2031/777 ,  B32B5/12 ,  B32B27/36 ,  Y10T428/24058 ,  Y10T428/24074 ,  Y10T428/24124 ,  Y10T428/24306 ,  Y10T428/2495 ,  Y10T428/2913

    摘要： A stab and ballistic resistant material, comprising a stab-resistant layer and a ballistic resistant layer, wherein the stab-resistant layer comprises at least one layer, wherein each layer is constituted of two units, each of which is formed from perpendicularly combined high strength and high module unidirectional fiber prepreg strips, adjacent units are combined with rotated 45°, and the stab-resistant layer has membranes adhered to both sides; the ballistic resistant layer comprises at least one layer, wherein each layer is constituted of two units, each of which is formed from perpendicularly combined unidirectional fiber prepreg strips, adjacent units are combined with rotated 90°, and the ballistic resistant layer has membranes adhered to both sides. The invention also provides a method for preparing the above stab and ballistic resistant material. The stab and ballistic resistant material of the invention functions to defend both stabs and bullets, which makes stab and ballistic resistant vest to be lighter, more efficient in protection, and easy to produce.

    摘要翻译： 一种防刺防弹材料，其特征在于，具有防刺层和防弹层，其特征在于，所述防刺层包括至少一层，其中每层由两个单元组成，每个单元由垂直组合的高强度 和高模块单向纤维预浸料条，相邻单元结合旋转45°，防刺层具有粘附在两侧的膜; 防弹层包括至少一个层，其中每个层由两个单元组成，每个单元由垂直组合的单向纤维预浸料条形成，相邻的单元与旋转90°组合，并且防弹层具有粘附到膜 双方。 本发明还提供了制备上述防刺和防弹材料的方法。 本发明的防刺和防弹材料起到防刺和子弹的作用，使得刺和防弹背心更轻，保护效率更高，易于生产。