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51. 发明专利

JPS4952500A 失效
公开(公告)号：JPS4952500A
公开(公告)日：1974-05-21
申请号：JP8577073
申请日：1973-07-30
IPC分类号： F42B10/66 , F42B20060101 , F42C20060101 , F42B15/18

52. 发明申请

WO2005005911A3 ENERGETIC LINEAR TIMING ELEMENT 审中-公开
标题翻译：能量线性时序元素
公开(公告)号：WO2005005911A3
公开(公告)日：2007-12-27
申请号：PCT/US2004013340
申请日：2004-04-30
申请人： DYNO NOBEL INC , TWAROG JR JOSEPH W , CAMPBELL JOHN , PLITT TYSON , HO KIM CHI
发明人： TWAROG JR JOSEPH W , CAMPBELL JOHN , PLITT TYSON , HO KIM CHI
IPC分类号： C06C5/00 , C06B45/10 , C06C5/04 , F42B20060101
CPC分类号： C06C5/06 , C06C5/04 , C06C7/00
摘要： A timing element for an initiator is made from a reactive polymeric material such as, e.g., a glycidyl azide polymer. The reactive polymeric material may include pulverulent oxidizer additives, such as ammonium, perchlorate and/or ferric oxide. The oxidizer additives are used to increase the rate of reaction and the output spark of the polymer material. The timing element serves to delay the travel of an initiation signal between an input, such as a signal transmission input line, and an explosive output charge, for a predetermined period of time, usually about 5 to about 10,000 milliseconds, e.g., about 9 to about 9600 milliseconds.
摘要翻译：用于引发剂的定时元件由反应性聚合物材料制成，例如缩水甘油基叠氮化物聚合物。反应性聚合物材料可以包括粉末氧化剂添加剂，例如铵，高氯酸盐和/或氧化铁。氧化剂添加剂用于提高聚合物材料的反应速率和输出火花。定时元件用于延迟诸如信号传输输入线的输入和爆炸输出电荷之间的启动信号的行进预定时间段，通常为约5至约10,000毫秒，例如约9至约9600毫秒。

53. 发明申请

WO2004107065A3 PREDETERMINED MISS-DISTANCE HOMING MISSILE 审中-公开
标题翻译：预测的距离偏差
公开(公告)号：WO2004107065A3
公开(公告)日：2005-10-06
申请号：PCT/IL2004000437
申请日：2004-05-23
申请人： RAFAEL ARMAMENT DEV AUTHORITY , MAROM ITSHAK , HEXNER GYORGY
发明人： MAROM ITSHAK , HEXNER GYORGY
IPC分类号： F41G7/22 , F42B20060101 , G05B20060101 , G05D1/12
CPC分类号： G05D1/12
摘要： A method to guide a homing missile (10) having a seeker head (14) to an aim point (42) which is a miss-vector (34) away from a target. The method includes the steps of tracking the target, using the seeker head, and guiding the homing missile to the point.
摘要翻译：将具有探针头（14）的导弹（10）引导到远离目标的向量（34）的瞄准点（42）的方法。该方法包括跟踪目标的步骤，使用引导头，引导引导导弹。

54. 发明申请

US20050183616A1 Bullet with spherical nose portion 有权
标题翻译：具有球形鼻部的子弹
公开(公告)号：US20050183616A1
公开(公告)日：2005-08-25
申请号：US10871093
申请日：2004-06-18
申请人： Gerald Eberhart , Richard Hayes
发明人： Gerald Eberhart , Richard Hayes
IPC分类号： F42B20060101 , F42B12/34 , F42B12/74 , F42B10/00
CPC分类号： F42B12/74 , F42B12/34
摘要： A bullet includes a frontward facing aperture. Contained within the aperture is a relatively hard bullet frontal element that provides advantageous bullet impact performance. In one embodiment, the frontal element is a steel sphere that provides advantageous penetration and weight retention when the bullet impacts laminated glass., such as an automobile windshield.
摘要翻译：子弹包括向前的朝向孔。包含在孔内是相对较硬的子弹前部元件，其提供有利的子弹冲击性能。在一个实施例中，前部元件是钢球，当子弹撞击夹层玻璃时，例如汽车挡风玻璃，其提供有利的穿透和重量保持。

55. 发明授权

US06837165B2 Bullet with spherical nose portion 有权
标题翻译：具有球形鼻部的子弹
公开(公告)号：US06837165B2
公开(公告)日：2005-01-04
申请号：US10288889
申请日：2002-11-06
申请人： Gerald T. Eberhart , Richard A. Hayes
发明人： Gerald T. Eberhart , Richard A. Hayes
IPC分类号： F42B20060101 , F42B12/34 , F42B12/74
CPC分类号： F42B12/74 , F42B12/34
摘要： A bullet includes a frontward facing aperture. Contained within the aperture is a relatively hard bullet frontal element that provides advantageous bullet impact performance. In one embodiment, the frontal element is a steel sphere that provides advantageous penetration and weight retention when the bullet impacts laminated glass, such as an automobile windshield.

56. 发明授权

US5328130A Stabilizer for a cannon projectile 失效
标题翻译：大炮射弹的稳定器
公开(公告)号：US5328130A
公开(公告)日：1994-07-12
申请号：US32
申请日：1993-01-04
申请人： Stewart Gilman , Anthony Farina
发明人： Stewart Gilman , Anthony Farina
IPC分类号： F42B20060101 , F42B10/04 , F42B10/26
CPC分类号： F42B10/26 , F42B10/04
摘要： A cylindrical device connected to the nose of a projectile for imparting n to the projectile fired from a non-rifled bore of a cannon. The device has at least two coaxial, adjacent, and integrally connected cylindrical segments of different diameter. The segment having the larger diameter is positioned most rearwardly of the projectile, relative to the nose of the projectile, and the periphery of this segment has circumferentially spaced angled slots for catching air moving past the projectile to spin the projectile. The segment with the smaller diameter attaches the cylindrical device to the aft end of the nose of the projectile and directs the flow of air to and through the angled slots of the segment having the larger diameter.
摘要翻译：连接到射弹的鼻子的圆柱形装置，用于从炮的非膛孔射出的射弹旋转。该装置具有不同直径的至少两个同轴，相邻和一体连接的圆柱形段。具有较大直径的段相对于射弹的鼻部位于抛射体的最后面，并且该段的周边具有周向间隔开的成角度的狭槽，用于捕捉通过射弹移动的空气以旋转射弹。具有较小直径的段将圆柱形装置附接到射弹的鼻部的后端，并将空气流引导并穿过具有较大直径的段的成角度的槽。

57. 发明授权

US5129604A Lateral thrust assembly for missiles 失效
标题翻译：横向组件用于MISSILES
公开(公告)号：US5129604A
公开(公告)日：1992-07-14
申请号：US380243
申请日：1989-07-17
申请人： Cloy J. Bagley
发明人： Cloy J. Bagley
IPC分类号： B64C15/14 , B64G1/00 , F02K9/80 , F02K9/88 , F41G7/00 , F42B20060101 , F42B10/00 , F42B10/66
CPC分类号： F42B10/663
摘要： A lateral thrust assembly for missile maneuvering comprises an annular array of outwardly directed nozzles, each nozzle having a releasable plug normally blocking flow of propellant gases out of the nozzle. A plug release mechanism associated with each plug allows that plug to be released to open the respective nozzle. A combustion chamber containing propellant is connected to the inner ends of all the nozzles. The propellant is ignited when one or more selected plugs are released to allow opening of the associated nozzle or nozzles, controlling the direction of the lateral thrust applied to the vehicle.
摘要翻译：用于导弹操纵的侧向推力组件包括向外指向的喷嘴的环形阵列，每个喷嘴具有通常阻挡推进剂气体流出喷嘴的可释放塞子。与每个插头相关联的插头释放机构允许释放插头以打开相应的喷嘴。包含推进剂的燃烧室连接到所有喷嘴的内端。当一个或多个选择的塞子被释放以允许相关联的喷嘴或喷嘴的打开，控制施加到车辆的横向推力的方向时，推进剂被点燃。

58. 发明授权

US5095821A Fragmentation casing and method of making 失效
标题翻译：分割壳和制作方法
公开(公告)号：US5095821A
公开(公告)日：1992-03-17
申请号：US381747
申请日：1989-06-14
申请人： Karl Merz
发明人： Karl Merz
IPC分类号： F42B12/22 , F42B20060101 , F42B5/26 , F42B12/24 , F42B12/26
CPC分类号： F42B12/26
摘要： The fragmentation casing has a one-piece hollow body (1) that incorporates nominal break points; this hollow body (1) is divided at least in one section (4) by at least one separating cut (5) that forms a separating gap. The separating cut is so made that the hollow body remains in the form of a one-piece structure. The surfaces of the separating cut that are adjacent in the separating gap are brought into contact with each other and are so fixed in contact with each other.
摘要翻译： PCT No.PCT / CH88 / 00157 Sec。 371日期1989年6月14日第 102（e）日期1989年6月14日PCT提交1988年9月9日PCT公布。第WO89 / 03500号公报日期1989年4月20日。破碎套管具有一体式中空体（1），其包含标称断点; 该中空体（1）至少在一个部分（4）中被形成分离间隙的至少一个分离切口（5）分开。分离切割使得中空体保持为单件结构的形式。在分离间隙中相邻的分离切口的表面彼此接触并固定成彼此接触。

59. 发明授权

US4712748A Missile 失效
标题翻译：导弹
公开(公告)号：US4712748A
公开(公告)日：1987-12-15
申请号：US940520
申请日：1986-12-10
申请人： Berthold Schafer
发明人： Berthold Schafer
IPC分类号： F42B20060101 , F42B10/66 , F42B15/033
CPC分类号： F42B10/668
摘要： The missile (10) comprises at its rear end in flying direction (A) tail f (14, 16, 18) whose front edges (14F, 16F, 18F) are sharpened at both sides. Intermediate the tail fins, outflow openings (22) are arranged on the body (12) to eject therethrough fuel into the supersonic external flow forming about the body (12). Due to supersonic flow, there are generated shock wave fronts extending from the front edges (14F, 16F, 18F) and being reflected by adjacent tail fins, said shock waves of the shock wave fronts interfering with the supersonic flow passing along the body so that recirculation fields are formed between the tail fins. The said recirculation fields are formed within the range of corner flow and outlfow openings (22) so that fuel discharged from the latter is burnt down with the formation of a locally stable flame. As a result of the volume increase resulting from the combustion, a high-pressure area develops between the tail fins. The pressure produces a force directed transversely to the flying direction and causing a control of the missile (10).
摘要翻译：导弹（10）在其后端沿飞行方向（A）包括其前边缘（14F，16F，18F）在两侧被锐化的尾翼（14,16,18）。中间的尾翼，流出口（22）布置在主体（12）上，以将燃料喷射到围绕主体（12）形成的超音速外部流中。由于超音速流动，产生从前边缘（14F，16F，18F）延伸并被相邻尾翼反射的冲击波阵面，所述冲击波前面的所述冲击波干扰沿身体传递的超音速流动，使得在尾翼之间形成再循环场。所述再循环场形成在角流和外侧开口（22）的范围内，使得从后者排出的燃料燃烧形成局部稳定的火焰。由于燃烧引起的体积增加，在尾翼之间形成高压区域。压力产生横向于飞行方向的力并引起对导弹的控制（10）。

60. 发明授权

US4691880A Torsion spring powered missile wing deployment system 失效
标题翻译：扭力弹力导弹翼部署系统
公开(公告)号：US4691880A
公开(公告)日：1987-09-08
申请号：US798207
申请日：1985-11-14
申请人： Arthur M. Frank
发明人： Arthur M. Frank
IPC分类号： B64C3/56 , F42B20060101 , F42B10/14 , F42B10/16 , F42B15/00 , B64C3/38
CPC分类号： F42B10/16
摘要： A foldable missile wing is deployed by means of an overcenter linkage powered by a torsion spring assembly capable of exerting a generally linear bias on the linkage over its full range of motion. A separate lock linkage maintains the foldable wing in a deployed position until release actuation of the lock linkage occurs thereby enabling wing deployment.
摘要翻译：可折叠的导弹翼通过由能够在其全部运动范围上对联动装置施加大致线性偏压的扭转弹簧组件驱动的中心联动部署。单独的锁定联动件将可折叠机翼保持在展开位置，直到发生锁定连杆的释放致动从而使机翼展开。

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