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11. 发明申请

US20120167794A1 REMOTE SETTING FOR ELECTRONIC SYSTEMS IN A PROJECTILE FOR CHAMBERED AMMUNITION 有权
公开(公告)号：US20120167794A1
公开(公告)日：2012-07-05
申请号：US13415306
申请日：2012-03-08
申请人： Stephan Dietrich
发明人： Stephan Dietrich
IPC分类号： F42B15/00 , F42B12/00
CPC分类号： F42C17/04 , F42C19/06
摘要： A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile.

12. 发明申请

US20120024185A1 PROJECTILE THAT INCLUDES A GIMBAL STOP 有权
标题翻译：包括一个GIMBAL停止的项目
公开(公告)号：US20120024185A1
公开(公告)日：2012-02-02
申请号：US12844493
申请日：2010-07-27
申请人： Erik T. Dale , Ryan A. Egbert
发明人： Erik T. Dale , Ryan A. Egbert
IPC分类号： F42B12/00
CPC分类号： F42B15/08 , F41G7/2213 , F41G7/2253 , F41G7/2293 , F42B15/01
摘要： Some embodiments pertain to a projectile that includes a frame and a first gimbal that is rotatably supported by the frame. The projectile further includes a second gimbal that is rotatably supported by the first gimbal. A sensor is supported by the second gimbal such that an adjustment mechanism is able to maneuver the first and second gimbals to adjust the position of the sensor. The projectile further includes a stop that is attached to the frame. The stop may be a cup that surrounds a bottom portion of the sensor. The cup provides a barrier to prevent the adjustment mechanism from maneuvering the sensor outside a designated area.
摘要翻译：一些实施例涉及一种包括框架和由框架可旋转地支撑的第一万向架的抛射体。弹丸还包括由第一万向架可旋转地支撑的第二万向架。传感器由第二万向架支撑，使得调节机构能够操纵第一和第二万向节来调节传感器的位置。射弹还包括一个附在框架上的挡块。挡块可以是围绕传感器底部的杯子。杯子提供屏障，以防止调节机构在指定区域外操纵传感器。

13. 发明申请

US20110155016A1 Synchronized Spin Multi-Component Projectile 有权
标题翻译：同步自旋多组分弹丸
公开(公告)号：US20110155016A1
公开(公告)日：2011-06-30
申请号：US12784654
申请日：2010-05-21
申请人： PJ Marx
发明人： PJ Marx
IPC分类号： F42B14/02 , F42B12/00
CPC分类号： F42B10/26 , F42B10/38 , F42B12/34 , F42B14/02
摘要： A projectile includes a leading part formed by a tip and a tip base that form a first annular shoulder where they meet. A trailing part of the projectile is formed by a base having a frusto-conical trailing end and a cylindrical leading end of truncate extent that forms a tail drive. A second annular shoulder is formed where a cylindrical rod meets the tail drive. A flat trailing end of the tip base and a flat leading end of the cylindrical rod abut one another when the projectile is assembled. A cylindrical interface has a leading extent abutting the first annular shoulder and a trailing end abutting the second annular shoulder. The tail drive and the trailing extent of the cylindrical interface are the only parts of the projectile that engage gun barrel rifling when the projectile is positioned in a gun barrel.
摘要翻译：抛射体包括由尖端和尖端基部形成的引导部分，其形成第一环形肩部，在那里它们相遇。抛射体的尾部由具有截头圆锥形后端和形成尾部驱动的截头范围的圆柱形前端的基部形成。形成第二环形肩部，其中圆柱形杆与尾部驱动器相交。当组装抛射体时，尖端基部的平坦的后端和圆柱形杆的平坦的前端彼此邻接。圆柱形接口具有与第一环形肩部相邻的引导程度和邻接第二环形肩部的后端。当弹丸放置在枪管中时，尾部驱动器和圆柱形接口的尾部范围是射弹的唯一部分，可以与枪筒枪膛接合。

14. 发明申请

US20100084505A1 MULTI-STAGE HYPER-VELOCITY KINETIC ENERGY MISSILE 有权
标题翻译：多级高速动力能量失效
公开(公告)号：US20100084505A1
公开(公告)日：2010-04-08
申请号：US12563855
申请日：2009-09-21
申请人： Richard Janik , Doron Strassman
发明人： Richard Janik , Doron Strassman
IPC分类号： F42B15/04 , F42B15/00 , F41G7/20 , F41G7/00 , F42B12/00
CPC分类号： F42B12/06 , F41G7/32 , F42B12/625 , F42B15/01 , F42B15/04
摘要： A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a ‘missile in a missile’ architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE-rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until “the last second” reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance. The missile may be configured for use with different platforms and different guidance systems but is particularly well suited for use with the existing base of TOW launch containers and platforms satisfying all of the physical, operational and CLOS guidance constraints while maintaining the performance of the KE-rod penetrator.
摘要翻译：多级高速动能导弹（HVKEM）使用“导弹”导弹，其中HVKEM包括第一级飞行导弹和第二级杀伤导弹，其中包括一个KE杆穿透器。飞行导弹以相对较低的速度（小于马赫1.5，通常小于马赫数1）巡航，以节省推进剂（重量），并允许有效的引导和机动，直到导弹靠近目标。当导弹处于KE杆穿透器的致命范围内时，杀死导弹分离并提升到更高的速度（大于Mach 3，通常大于Mach 5），并且在不到一秒钟内不引导飞行物撞击目标。等待提升KE杆直到“最后一秒”减少了将KE杆放在目标上所需的总推进剂（重量），并简化了指导。导弹可以配置为用于不同的平台和不同的导向系统，但特别适用于现有的TOW发射容器和平台的基础，满足所有的物理，操作和CLOS指导约束，同时保持KE- 杆穿透器。

15. 发明申请

US20100064926A1 APPARATUS AND METHOD FOR INHIBITING INADVERTENT INITIATION OF A MUNITION 失效
标题翻译：抑制无效启动的装置和方法
公开(公告)号：US20100064926A1
公开(公告)日：2010-03-18
申请号：US11123292
申请日：2005-05-06
申请人： Roger W. Melin , John S. Buchan , Joseph M. Wright , Chris E. Williams , Daren C. Davis
发明人： Roger W. Melin , John S. Buchan , Joseph M. Wright , Chris E. Williams , Daren C. Davis
IPC分类号： F42B12/00
CPC分类号： F42B39/14 , F42B39/18
摘要： A device for inhibiting inadvertent initiation of a munition includes a sorbing refrigeration device adapted to at least partially surround an energetic material of the munition. A container includes an energetic material and a sorbing refrigeration device at least partially surrounding the energetic material. A method for inhibiting an inadvertent initiation of a munition includes cooling an energetic material of the munition by sorption refrigeration.
摘要翻译：用于抑制无意中启动弹药的装置包括适于至少部分地围绕弹药的能量材料的吸附制冷装置。容器包括能量材料和至少部分地围绕高能材料的吸附制冷装置。用于抑制无意中启动弹药的方法包括通过吸附制冷来冷却弹药的高能材料。

16. 发明申请

US20090288572A1 HUNTING BULLET COMPRISING AN EXPANSION RING 有权
标题翻译：包围膨胀圈的打包带
公开(公告)号：US20090288572A1
公开(公告)日：2009-11-26
申请号：US12534639
申请日：2009-08-03
申请人： Jean-Claude SAUVESTRE
发明人： Jean-Claude SAUVESTRE
IPC分类号： F42B12/00
CPC分类号： F42B12/34 , F42B5/045 , F42B7/10 , F42B30/02
摘要： The invention relates to the field of ammunition for hunting guns.The ammunition consists of a full-caliber or subcaliber bullet (2), of the type comprising a substantially rigid bullet body (6) and a deformable part, the deformable part consisting of an approximately cylindrical expansion ring (7), the rear part of which is fitted onto the front part of the bullet body (6).Application to small, medium or large caliber ammunition.
摘要翻译：本发明涉及狩猎枪弹药领域。该弹药包括全口径或亚型子弹（2），其类型包括基本上刚性的子弹体（6）和可变形部分，该可变形部分由大致圆柱形的膨胀环（7）组成，后部其安装在子弹体（6）的前部上。适用于小，中，大口径弹药。

17. 发明申请

US20090101038A1 Frangible non-lethal projectile 审中-公开
标题翻译：易碎非致死弹丸
公开(公告)号：US20090101038A1
公开(公告)日：2009-04-23
申请号：US12315761
申请日：2008-12-05
申请人： John A. Kapeles , Joseph P. Kolnik
发明人： John A. Kapeles , Joseph P. Kolnik
IPC分类号： F42B12/00 , F42B12/36 , F42B12/40 , F42B12/46
CPC分类号： F42B12/40 , F42B12/50 , F42B12/745
摘要： A non-lethal impact projectile having a nose composed of a frangible, rigid, polymer foam material such that the nose crushes upon impact with a target to disperse energy, thereby reducing the kinetic energy transferred to the target. Most preferably, the munition or projectile is provided with a cavity to retain a payload, such as marker agents, lacrimators, irritants, inflammatory agents, odorants or inert powders, such that the payload is laterally dispersed upon impact to further dissipate energy transferred to the target.
摘要翻译：具有由易碎，刚性的聚合物泡沫材料构成的鼻子的非致命冲击弹丸，使得鼻子与目标物撞击以分散能量，由此减少传递到靶的动能。最优选地，弹药或抛射体具有空腔以保留有效载荷，例如标记剂，流动剂，刺激剂，炎症剂，气味剂或惰性粉末，使得有效载荷在冲击时横向分散，以进一步消散转移到目标。

18. 发明申请

US20090050010A1 Soft projectile 有权
标题翻译：软弹丸
公开(公告)号：US20090050010A1
公开(公告)日：2009-02-26
申请号：US11983384
申请日：2007-11-07
申请人： Kwok-Wah Tsang
发明人： Kwok-Wah Tsang
IPC分类号： F42B12/00
CPC分类号： F42B6/003 , F42B6/10
摘要： A projectile for a toy shooting device includes a tubular body, a head moulded of soft material, an anchor partially embedded in the head and comprising a fixing stem extending into and adhered to the tubular body.
摘要翻译：用于玩具射击装置的抛射体包括管状体，由软材料模制的头部，部分地嵌入头部中的锚固件，并且包括延伸到并粘附到管状体上的固定杆。

19. 发明申请

US20080314234A1 DISTRIBUTED GROUND-BASED THREAT DETECTION SYSTEM 有权
标题翻译：分布式地基威胁检测系统
公开(公告)号：US20080314234A1
公开(公告)日：2008-12-25
申请号：US11879524
申请日：2007-06-25
申请人： Mallory John Boyd , Jason R. Allen , William Rodney Ditzler , Richard James Busse , Michael Dennis Barrett
发明人： Mallory John Boyd , Jason R. Allen , William Rodney Ditzler , Richard James Busse , Michael Dennis Barrett
IPC分类号： G06K9/28 , F42B12/00
CPC分类号： F41H11/02 , G01S3/784 , G01S5/16 , G06T7/254 , G06T7/292 , G06T2207/10016 , G06T2207/30212
摘要： A distributed ground sensor threat detection system, which is an automated missile warning system designed to provide reliable, timely and accurate missile location information of shoulder-launched SAMs within the volume under surveillance by a network of sensors. Remote sensor nodes position in proximity to an airport runway monitor the area between the nodes to locate threat missiles. Detection information from each remote sensor node is sent to a central processing node which processes the information to determine if a threat missile is launched against a commercial aircraft.
摘要翻译：一种分布式地面传感器威胁检测系统，是一种自动导弹预警系统，旨在通过传感器网络在受监控的体积内提供肩部发射的SAM的可靠，及时和准确的导弹位置信息。远程传感器节点靠近机场跑道，监视节点之间的区域以定位威胁导弹。来自每个远程传感器节点的检测信息被发送到中央处理节点，处理该信息以确定是否向商用飞机发射威胁导弹。

20. 发明授权

US07467761B2 Method and system for adjusting the flight path of an unguided projectile, with compensation for jittering deviation 有权
标题翻译：用于调整非导弹弹道的飞行路径的方法和系统，并补偿抖动偏差
公开(公告)号：US07467761B2
公开(公告)日：2008-12-23
申请号：US11128654
申请日：2005-05-13
申请人： Oded Yehezkeli , Irad Kunreich
发明人： Oded Yehezkeli , Irad Kunreich
IPC分类号： F41G7/00 , F41F3/04 , F42B15/01 , F42B12/00 , F42B15/00 , F42B30/00
CPC分类号： F41G3/12 , F41G3/10 , F41G7/306
摘要： A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction substantially equal to that of the compensating impulse vector.
摘要翻译：一种用于调整非导弹弹道的飞行路径的方法，其包括以下步骤：（a）在射弹从发射管的射出时间处测量射弹发射管的抖动的大小和方向; （b）测量射弹与标称速度的速度偏差; （c）测量发射管视线的角度偏差，等于与重力方向重合的线与通过发射管中心的线和瞄准中心之间的角度偏差; （d）基于抖动，速度偏差和角度偏差的大小和方向，确定在其初始飞行路径期间施加到射弹的补偿脉冲矢量; 和（e）通过激活飞行校正单元将补偿冲击矢量施加到射弹，由飞行校正单元产生的推力适于调整射弹飞行路径的幅度和方向与补偿脉冲矢量的大小相等。

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