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61. 发明申请

WO2017011066A1 ARMORED RADOME 审中-公开
标题翻译：装甲雷达
公开(公告)号：WO2017011066A1
公开(公告)日：2017-01-19
申请号：PCT/US2016/031737
申请日：2016-05-11
申请人： RAYTHEON COMPANY
发明人： CROUCH, David D.
IPC分类号： F41H5/04 , F41H13/00 , F42B10/46 , H01Q1/42
CPC分类号： F41H13/0068 , F41H5/0457 , F42B10/46 , H01Q1/273 , H01Q1/425
摘要： An armored radome (10) is provided and includes a metallic plate (20) formed to define an array of through-holes (21). Each through-hole (21) has a respective longitudinal axis (22) substantially aligned with electromagnetic radiation passing locally through the metallic plate (20).
摘要翻译：提供了一种装甲天线罩（10）并且包括形成为限定通孔阵列（21）的金属板（20）。每个通孔（21）具有基本上与通过金属板（20）局部通过的电磁辐射基本对准的相应的纵向轴线（22）。

62. 发明申请

WO2016032370A3 BULLET FOR SMALL ARMS WEAPON 审中-公开
标题翻译：小武器武器的弹丸
公开(公告)号：WO2016032370A3
公开(公告)日：2016-04-07
申请号：PCT/RU2015000539
申请日：2015-08-26
申请人： POLOVNEV ANDREY ALBERTOVICH
发明人： POLOVNEV ANDREY ALBERTOVICH
IPC分类号： F42B30/02 , F42B5/067 , F42B10/00
CPC分类号： F42B10/44 , F42B10/46 , F42B14/02
摘要： The invention relates to the field of small arms ammunition and can be used in the fabrication of bullets intended for high precision firing at supersonic and subsonic initial bullet velocities. A bullet for a small arms weapon comprises a head portion with a blunt nose surface, a leading portion, and a tail portion, which tapers towards the base end, wherein the largest diameter of the cross-section of the leading portion is equal to D. The length of the head portion is equal to 1.9-2.9 D, and the diameter at the interface between the nose surface and the lateral surface of the head portion is equal to 0.15-0.3 D. The lateral surface of the head portion is delimited by the surface of two adjoining truncated cones, namely a front cone and a rear cone with opening angles equal to 22°-30° and 8°-16° respectively, wherein the smaller base of the front truncated cone abuts the nose surface, and the larger base of the rear truncated cone abuts the surface of the leading portion. Between the leading portion and the tail portion there is a step transition so that the largest diameter of the cross-section of the tail portion is equal to 0.94-0.97 D and is less than the diameter of the barrel bore, measured at the rifling lands. The invention provides an increase in the ballistic characteristics of bullets on a trajectory and a decrease in bullet dispersion.
摘要翻译：本发明涉及小型武器弹药领域，并且可用于制造旨在以超音速和亚音速初始子弹速度进行高精度发射的子弹。一种用于小型武器的子弹包括具有钝的鼻子表面，头部和尾部的头部，该头部朝基端逐渐变细，其中，头部横截面的最大直径等于D ，头部的长度等于1.9-2.9D，头部表面与头部侧面之间的界面处的直径等于0.15-0.3D。头部的侧表面被限定通过两个相邻的截头锥体的表面，即分别具有等于22°-30°和8°-16°的开口角的前锥体和后锥体，其中前截锥体的较小基部邻接鼻面，并且后截头圆锥体的较大基部邻接前导部分的表面。在引导部分和尾部之间存在阶梯过渡部分，使得尾部横截面的最大直径等于0.94-0.97D并小于在膛线处测量的筒孔直径。本发明提供了弹道上的子弹的弹道特性的增加和子弹分散的减少。

63. 发明申请

WO2012160271A1 ELÉMENT DE JONCTION POUR UN CORPS EN MATÉRIAU COMPOSITE D'UN PROJECTILE MILITAIRE DE PERFORATION 审中-公开
标题翻译：连接军用复合材料物体的元素
公开(公告)号：WO2012160271A1
公开(公告)日：2012-11-29
申请号：PCT/FR2012/000196
申请日：2012-05-15
申请人： MBDA FRANCE , BLIN Michel , CHEVALIER Germain
发明人： BLIN Michel , CHEVALIER Germain
IPC分类号： F42B10/46 , F42B10/52 , F42B12/08 , F42B12/76
CPC分类号： F42B12/745 , F42B10/46 , F42B10/52 , F42B12/08 , F42B12/76
摘要： Selon l'invention, la partie arrière de l'élément de jonction (1), destinée à être reliée à un corps (4) en matériau composite, comporte au moins une butée (13) de forme annulaire, centrée par rapport à un axe longitudinal (10) et destinée à venir au contact du bord avant (14) dudit corps (4), ainsi qu'un prolongement longitudinal (15) vers l'arrière, qui est défini à partir de ladite butée (13), qui comprend une face de contact (16), et qui présente une forme et un diamètre adaptés audit corps (4) de manière à pouvoir venir, avec sa face de contact (16), latéralement au contact d'une surface périphérique (17) de ce dernier.
摘要翻译：根据本发明，连接元件（1）的后部部分意图连接到由复合材料制成的主体（4）上，包括至少一个环形形状的邻接（13），该基座相对于纵向轴线（10）并且旨在与所述主体（4）的前边缘（14）接触，以及从所述邻接件（13）向前限定的纵向后延伸部（15），并且包括接触面（16），并且具有适于所述主体（4）的形状和直径，使得其接触面（16）可以侧向地与其外周表面（17）接触。

64. 发明申请

WO2012136239A1 AEROHEATING PROTECTION FOR A MISSILE ELECTRO - OPTICAL SEEKER 审中-公开
标题翻译：用于电光学眼镜的电磁干扰保护
公开(公告)号：WO2012136239A1
公开(公告)日：2012-10-11
申请号：PCT/EP2011/055179
申请日：2011-04-04
申请人： SENER GRUPO DE INGENIERIA, S.A. , SANCHO PONCE, Jorge , HERRAIZ ALIJAS, Pedro, Jose , REBOLO GOMEZ, Rafael , MIRAVET FUSTER, Carlos , ARCE AGUINAGA, Aitor , FERNANDEZ IBARZ, Jose, Maria , RIBAS NIETO, Daniel
发明人： SANCHO PONCE, Jorge , HERRAIZ ALIJAS, Pedro, Jose , REBOLO GOMEZ, Rafael , MIRAVET FUSTER, Carlos , ARCE AGUINAGA, Aitor , FERNANDEZ IBARZ, Jose, Maria , RIBAS NIETO, Daniel
IPC分类号： F41G7/22
CPC分类号： G01J1/0271 , F41G7/2253 , F41G7/2293 , F42B10/46 , F42B15/01 , G02B27/0006 , G02B27/0018
摘要： This invention advances the related state-of-the-art by eliminating the physical EO window used by electro-optical imaging infrared seekers for tactical missiles and high-altitude endo-atmospheric interceptors, widely employed in integrated defense systems. This invention increases the probability of intercepting exo-atmospheric ballistic warheads by exo-atmospheric interceptors, and eliminates the existing altitude "gap" of interception, as well as the geographical limitations posed by the mesospheric Noctilucent Clouds. The problem of protecting an imaging EO sensor from aeroheating is solved in this invention by a special purpose device which is enabled immediately after the nose cone ejection event. The role of said device is to augment the sensor fixed sunshade and cavity lengths in the forward direction, and by doing so, the resulting new cavity enables the optimal injection of an optically inert gas into the new extended cavity in front of the sensor, thus effectively blocking the entry of the compressed hot air into the sensor cavity, while simultaneously avoiding any adverse effects of inducing flow instabilities in the flow as well as the disturbance of the injected gas flow on sensor structures. Having a greater length for the hot gas to penetrate, eliminates also the penetration of suspended particles in oncoming air stream.
摘要翻译：本发明通过消除广泛应用于综合防御系统中的用于战术导弹和高空大气拦截器的电光成像红外寻道者所使用的物理EO窗口，来改进现有技术。本发明增加了外太空拦截器截获外部大气弹道弹头的可能性，消除了现有高度“拦截间隙”以及中层夜光引起的地理局限性。保护成像EO传感器免受气候加热的问题在本发明中由专门的设备解决，该专用设备在鼻锥喷射事件之后立即启用。所述装置的作用是增加传感器固定的遮阳罩和空腔长度在向前的方向，并且通过这样做，所得到的新腔体能够将光学惰性气体最佳地注入到传感器前面的新的延伸空腔中有效地阻止压缩的热空气进入传感器腔，同时避免在流动中引起流动不稳定性以及传感器结构上注入的气体流动的干扰的任何不利影响。具有较长的热气穿透长度，也消除悬浮颗粒在迎面而来的气流中的穿透。

65. 发明申请

WO2011058359A1 GUIDANCE DEVICE 审中-公开
标题翻译：指导装置
公开(公告)号：WO2011058359A1
公开(公告)日：2011-05-19
申请号：PCT/GB2010/051879
申请日：2010-11-11
申请人： BAE SYSTEMS PLC , AXFORD, Richard, Desmond Joseph , BEGGS, Kevin,William
发明人： AXFORD, Richard, Desmond Joseph , BEGGS, Kevin,William
IPC分类号： F42B10/14 , F42B10/12 , F42B10/64
CPC分类号： F42B10/14 , F42B10/12 , F42B10/46 , F42B10/64
摘要： There is disclosed a collar (100) which may be attached to a munition in order to control the trajectory of the munition. The collar (100) has a collar body (10); a surface (12) for capturing the projectile as it leaves the barrel; a sill (14) for supporting the surface (12) at the muzzle of the barrel; and a guidance means (20a, 20b, 21a, 21b) for altering the flow of air around the collar (100). The collar (100) supports itself at the muzzle and may attach to the projectile at the surface (12) to integrate with the projectile as the projectile is fired. The collar (100) is particularly suited for attachment to mortar rounds. Such a collar (100) gives a weapon operator the option of increasing the precision of a munition without having to carry a plurality of munition types.
摘要翻译：公开了一种衣领（100），其可附接到弹药以控制弹药的轨迹。衣领（100）具有衣领（10）; 用于当抛射体离开桶时捕获射弹的表面（12）; 用于在所述枪管的枪口处支撑所述表面（12）的基台（14）; 以及用于改变所述轴环（100）周围的空气流的引导装置（20a，20b，21a，21b）。衣领（100）在枪口处支撑自身，并且可以在射弹被射击时附着在表面（12）处的射弹与射弹结合。套环（100）特别适合于附着在迫击炮弹的周围。这样的衣领（100）使武器操作者能够提高弹药的精度，而不必携带多种弹药。

66. 发明申请

WO2011045792A1 MISSILE NOSE FAIRING SYSTEM 审中-公开
标题翻译： MISSILE NOSE公寓系统
公开(公告)号：WO2011045792A1
公开(公告)日：2011-04-21
申请号：PCT/IL2010/000840
申请日：2010-10-14
申请人： RAFAEL ADVANCED DEFENSE SYSTEMS LTD. , YACOBOVITCH, Yacov
发明人： YACOBOVITCH, Yacov
IPC分类号： B64D7/00
CPC分类号： F42B10/46
摘要： The present invention is a missile nose fairing system. The system of the invention comprises a plurality of sections attached at an aft end thereof to a missile body, restraining means for normally preventing aftward displacement of the plurality of sections, and a drive unit for releasing the restraining means in response to a received signal. Each of the sections has an outer surface that converges to a common forward pointed tip for enclosing and protecting a guidance head when in an extended position and is retractable into a corresponding recessed region formed within a missile nose when the drive unit is activated releasing the restraining means.
摘要翻译：本发明是一种导弹整流罩系统。本发明的系统包括在其后端附接到导弹体的多个部分，用于正常防止多个部分的向后移动的限制装置，以及用于响应于接收到的信号释放限制装置的驱动单元。每个部分具有会聚到共同的前尖尖的外表面，用于在延伸位置包围和保护引导头，并且当驱动单元被激活释放限制时可伸缩到形成在导弹鼻内的相应凹陷区域内手段。

67. 发明申请

WO2009095910A3 APPARATUS FOR SPLITTING AND REMOVING A SHROUD FROM AN AIRBORNE VEHICLE 审中-公开
标题翻译：从AIRBORNE VEHICLE分离和拆卸SHROUD的装置
公开(公告)号：WO2009095910A3
公开(公告)日：2010-03-11
申请号：PCT/IL2009000106
申请日：2009-01-28
申请人： RAFAEL ADVANCED DEFENSE SYS , KRISHER EHUD
发明人： KRISHER EHUD
IPC分类号： F42B15/10
CPC分类号： F42B10/46 , F42B15/36
摘要： The present invention relates to an apparatus for splitting and removing a shroud from an airborne vehicle, that comprises a shroud that includes two components, linkable one to another along their lengths, and wherein upon being fastened one to the other, they form a shroud with a lengthwise axis and an inner space, and having a base sector around the circumference of the bottom part of said shroud, and wherein said base is connectable to said airborne body and a fastening assembly for fastening said two components of said shroud one to the other, and wherein said fastening assembly is given to be torn on stretching upon detonation of a pyrotechnic charge and a piston assembly that disassembled at the completion of the piston's stroke, and is operable by said pyrotechnic charge, and wherein said piston assembly serves for timed tearing of said fastening assembly.
摘要翻译：本发明涉及一种用于从机载车上分离和去除护罩的装置，其包括一个护罩，该护罩包括两个沿其长度可彼此连接的部件，并且其中，一旦彼此紧固，它们形成护罩，纵向轴线和内部空间，并且具有围绕所述护罩的底部的圆周的基部部分，并且其中所述基座可连接到所述空中主体和紧固组件，用于将所述护罩的所述两个部件一个紧固到另一个，并且其中所述紧固组件在引爆烟火充电时被拉伸撕裂，以及在活塞行程完成时拆卸的活塞组件，并且可由所述烟火充电器操作，并且其中所述活塞组件用于定时撕裂的所述紧固组件。

68. 发明申请

WO2009095910A2 APPARATUS AND METHOD FOR SPLITTING AND REMOVING A SHROUD FROM AN AIRBORNE VEHICLE 审中-公开
标题翻译：从AIRBORNE车辆分离和拆卸SHROUD的装置和方法
公开(公告)号：WO2009095910A2
公开(公告)日：2009-08-06
申请号：PCT/IL2009/000106
申请日：2009-01-28
申请人： RAFAEL ADVANCED DEFENSE SYSTEMS LTD. , KRISHER, Ehud
发明人： KRISHER, Ehud
IPC分类号： B64C7/02
CPC分类号： F42B10/46 , F42B15/36
摘要： The present invention relates to an apparatus for splitting and removing a shroud from an airborne vehicle, that comprises a shroud that includes two components, linkable one to another along their lengths, and wherein upon being fastened one to the other, they form a shroud with a lengthwise axis and an inner space, and having a base sector around the circumference of the bottom part of said shroud, and wherein said base is connectable to said airborne body and a fastening assembly for fastening said two components of said shroud one to the other, and wherein said fastening assembly is given to be torn on stretching upon detonation of a pyrotechnic charge and a piston assembly that disassembled at the completion of the piston's stroke, and is operable by said pyrotechnic charge, and wherein said piston assembly serves for timed tearing of said fastening assembly and to "active" removal of said two components of said shroud one from the other, in an essentially revolving motion and while tearing and moving farther apart said shroud's base from the airborne vehicle body and wherein said apparatus is characterized by the positioning of said fastening assembly that is given to be torn on stretching upon detonation of said pyrotechnic charge, at a distance and separated from said piston assembly; and by the axes of operation of the two assemblies - the operating axis of said fastening assembly that is torn on stretching, and the operating axis of said piston assembly that is disassembled on the termination of the piston's stroke - are axes that are essentially parallel one to the other, while essentially orthogonal and radial in their direction of operation relatively to said shroud's lengthwise axis.
摘要翻译：本发明涉及一种用于从机载车上分离和去除护罩的装置，其包括一个护罩，该护罩包括两个沿其长度可彼此连接的部件，并且其中，一旦彼此紧固，它们形成护罩，纵向轴线和内部空间，并且具有围绕所述护罩的底部的圆周的基部部分，并且其中所述基座可连接到所述空中主体和紧固组件，用于将所述护罩的所述两个部件一个紧固到另一个，并且其中所述紧固组件在引爆烟火充电时被拉伸撕裂，以及在活塞行程完成时拆卸的活塞组件，并且可由所述烟火充电器操作，并且其中所述活塞组件用于定时撕裂并且以基本上旋转的运动和“主动”地将所述护罩的所述两个部件彼此“移除” 使得护罩的基座从机载车体分离并移动得更远，并且其中所述装置的特征在于所述紧固组件的定位在远离所述火药装置的爆炸时被拉伸，并与所述活塞分离部件; 并且通过两个组件的操作轴线 - 所述紧固组件的在拉伸时撕裂的操作轴线以及在活塞行程终止时拆卸的所述活塞组件的操作轴线是基本上平行的轴线而在其相对于所述护罩的纵向轴线的操作方向上基本上是正交的和径向的。

69. 发明申请

WO2005103600A3 MISSILE WITH MULTIPLE NOSECONES 审中-公开
标题翻译：与多个NOSECONES的MISSILE
公开(公告)号：WO2005103600A3
公开(公告)日：2005-12-08
申请号：PCT/US2004034567
申请日：2004-10-19
申请人： RAYTHEON CO , FACCIANO ANDREW B , MOORE ROBERT T , PARRY JAMES E , WHITE JOHN T
发明人： FACCIANO ANDREW B , MOORE ROBERT T , PARRY JAMES E , WHITE JOHN T
IPC分类号： F41G7/00 , F42B10/00 , F42B10/02 , F42B10/46
CPC分类号： F42B10/46
摘要： A missile (10) includes a payload assembly (16) that has a pair of nosecones (18, 20). The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separation mechanisms. The first (outer) nosecone (18) may have a more streamlined shape, be made of more thermally-protective material, and may meet less stringent sealing requirements, than the second (inner) nosecone (20). Separation of the outer nosecone from the payload assembly may cause backward movement of a center of pressure of the payload assembly, bringing the center of pressure of the assembly closer to a center of gravity of the assembly. This may make the payload assembly easier to maneuver, for example, reducing or eliminating the need for intervention by an attitude control system, to maintain the payload assembly on a desired course.
摘要翻译：导弹（10）包括有效载荷组件（16），所述有效载荷组件（16）具有一对旋转体（18,20）。对于不同的环境和/或飞行阶段，例如具有不同形状，不同的外壳材料，不同类型的密封件和/或不同的分离机构，可以优化鼻锥体。第一（外）鼻锥（18）可以具有更加流线型的形状，由更多的热保护材料制成，并且可以满足比第二（内）鼻锥（20）更不严格的密封要求。外部鼻锥与有效载荷组件的分离可能导致有效载荷组件的压力中心向后移动，使组件的压力中心更接近组件的重心。这可以使得有效负载组件更容易操纵，例如，减少或消除对姿态控制系统的干预的需要，以将有效负载组件保持在期望的过程上。

70. 发明申请

WO2005103600A2 MISSILE WITH MULTIPLE NOSECONES 审中-公开
标题翻译：具有多个NOSECONES的导弹
公开(公告)号：WO2005103600A2
公开(公告)日：2005-11-03
申请号：PCT/US2004/034567
申请日：2004-10-19
申请人： RAYTHEON COMPANY , FACCIANO, Andrew, B. , MOORE, Robert, T. , PARRY, James, E. , WHITE, John, T.
发明人： FACCIANO, Andrew, B. , MOORE, Robert, T. , PARRY, James, E. , WHITE, John, T.
IPC分类号： F41G7/00
CPC分类号： F42B10/46
摘要： A missile (10) includes a payload assembly (16) that has a pair of nosecones (18, 20). The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separation mechanisms. The first (outer) nosecone (18) may have a more streamlined shape, be made of more thermally-protective material, and may meet less stringent sealing requirements, than the second (inner) nosecone (20). Separation of the outer nosecone from the payload assembly may cause backward movement of a center of pressure of the payload assembly, bringing the center of pressure of the assembly closer to a center of gravity of the assembly. This may make the payload assembly easier to maneuver, for example, reducing or eliminating the need for intervention by an attitude control system, to maintain the payload assembly on a desired course.
摘要翻译：导弹（10）包括具有一对鼻孔（18,20）的有效负载组件（16）。例如，具有不同的形状，不同的壳体材料，不同类型的密封件和/或不同的分离机构，可以针对不同的环境和/或飞行阶段对鼻锥进行优化。与第二（内）鼻锥20相比，第一（外）鼻锥18可以具有更流线型的形状，由更耐热的材料制成，并且可以满足不太严格的密封要求。将外锥头与有效负载组件分离可导致有效负载组件的压力中心向后移动，使组件的压力中心更靠近组件的重心。这可以使得有效载荷组件更容易操纵，例如，减少或消除姿态控制系统干预的需要，以将有效载荷组件维持在期望的路线上。

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