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1. 发明专利

IL173697D0 MINIATURE MISSILE 未知
公开(公告)号：IL173697D0
公开(公告)日：2006-12-31
申请号：IL17369706
申请日：2006-02-13
申请人： ODED YEHEZKELI , RAFAEL ADVANCED DEFENSE SYS , YARIV BRIL , YAKOV HETZ

2. 发明申请

US20100320312A1 MINIATURE MISSILE 有权
标题翻译：微型MISSILE
公开(公告)号：US20100320312A1
公开(公告)日：2010-12-23
申请号：US12377604
申请日：2007-08-16
申请人： Yariv Bril , Yakov Hetz , Oded Yehezkeli , Ehud Chishinsky
发明人： Yariv Bril , Yakov Hetz , Oded Yehezkeli , Ehud Chishinsky
IPC分类号： F42B15/01 , F41G7/00 , F42B10/00 , G06F19/00 , F41F3/04 , F41F3/045 , F41F3/06
CPC分类号： F42B15/00 , F41G7/008 , F41G7/2206 , F41G7/2213 , F41G7/2253 , F41G7/2293
摘要： A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.
摘要翻译：微型轻型高机动导弹（10）具有导弹体（12），具有三组至少两个气动控制表面（14,16,18），用于独立控制导弹的滚动，俯仰和偏航。每组控制表面（14,16,18）由部署在导弹体（12）内的对应致动器（20）独立地控制。其他优选特征包括选择目标处的高度入射角，以及在爆炸和动力学操作模式之间切换。

3. 发明专利

IL177527D0 MINIATURE MISSILE 未知
公开(公告)号：IL177527D0
公开(公告)日：2007-05-15
申请号：IL17752706
申请日：2006-08-16
申请人： RAFAEL ADVANCED DEFENSE SYS , ODED YEHEZKELI , YARIV BRIL , YAKOV HETZ , EHUD CHISHINSKY
IPC分类号： F41G20100101
摘要： A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.

4. 发明申请

US20060060692A1 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：US20060060692A1
公开(公告)日：2006-03-23
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： F42B15/01
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的飞行路径的幅度和方向与补偿脉冲矢量的大小相等。

5. 发明授权

US5301986A Clamp 失效
标题翻译：钳
公开(公告)号：US5301986A
公开(公告)日：1994-04-12
申请号：US959319
申请日：1992-10-09
申请人： Oded Yehezkeli
发明人： Oded Yehezkeli
IPC分类号： F16L23/10 , F16L23/036
CPC分类号： F16L23/10 , Y10T24/1441
摘要： A clamp for joining a pair of elements having generally circular flanges, the clamp including an inner flange engaging portion arranged to provide generally axially extending forces to said flanges for retaining them against one another when substantially radial forces are applied to the inner flange, an outer circumferential strap element and at least one bolt. The clamp also includes a coupler engaging the strap element adapted to provide substantially circumferential tension thereto, whereby substantially radial forces are applied to the inner flange without urging non-circumferential bending of the strap element.
摘要翻译：一种用于连接一对具有大致圆形凸缘的元件的夹具，所述夹具包括内部凸缘接合部分，所述内部凸缘接合部分被布置成向所述凸缘提供大致轴向延伸的力，以在基本上径向的力施加到所述内部凸缘时将它们保持在彼此上，周向带元件和至少一个螺栓。夹具还包括接合带元件的联接件，其适于向其提供基本上周向的张力，由此基本上径向的力被施加到内凸缘，而不施加带元件的非圆周弯曲。

6. 发明授权

US08664575B2 Miniature missile 有权
标题翻译：微型导弹
公开(公告)号：US08664575B2
公开(公告)日：2014-03-04
申请号：US12377604
申请日：2007-08-16
申请人： Yariv Bril , Yakov Hetz , Oded Yehezkeli , Ehud Chishinsky
发明人： Yariv Bril , Yakov Hetz , Oded Yehezkeli , Ehud Chishinsky
IPC分类号： F41G7/22 , F42B10/62 , F41G7/00 , F42B10/00
CPC分类号： F42B15/00 , F41G7/008 , F41G7/2206 , F41G7/2213 , F41G7/2253 , F41G7/2293
摘要： A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.
摘要翻译：微型轻型高机动导弹（10）具有导弹体（12），具有三组至少两个气动控制表面（14,16,18），用于独立控制导弹的滚动，俯仰和偏航。每组控制表面（14,16,18）由部署在导弹体（12）内的对应致动器（20）独立地控制。其他优选特征包括选择目标处的高度入射角，以及在爆炸和动力学操作模式之间切换。

7. 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。

8. 发明授权

US06582381B1 Mechanical positioner for MRI guided ultrasound therapy system 有权
标题翻译： MRI引导超声治疗系统的机械定位器
公开(公告)号：US06582381B1
公开(公告)日：2003-06-24
申请号：US09628964
申请日：2000-07-31
申请人： Oded Yehezkeli , David Freundlich , Nitzan Magen , Carlos Marantz , Yoav Medan , Skuki Vitek , Avi Weinreb
发明人： Oded Yehezkeli , David Freundlich , Nitzan Magen , Carlos Marantz , Yoav Medan , Skuki Vitek , Avi Weinreb
IPC分类号： A61B5055
CPC分类号： A61N7/00 , A61B90/50 , A61B2090/374 , Y10S128/916 , Y10S977/725 , Y10S977/929
摘要： An ultrasound therapy system utilizes a mechanical positioning assembly to locate and aim an ultrasonic transducer. The positioner provides for roll and pitch control as well as control in the lateral and longitudinal directions. The positioner uses piezo-electric vibrational motors that can effectively operate within the field of an MRI system without interfering with its operation. The motors are capable of providing a breaking force to the drive shafts while de-energized and thus aid in preventing motor slippage or backlash. Since the motors do not affect the operation of an MRI system, the ultrasonic therapy system can be made more compact. Two sets of position encoders are used to align the positioner. Course absolute encoders and fine relative encoders are both coupled to the positioning motors and allow for precise control over the position and orientation of the ultrasonic transducer.
摘要翻译：超声治疗系统利用机械定位组件来定位和瞄准超声波换能器。定位器提供滚动和俯仰控制以及横向和纵向控制。定位器使用压电振动电动机，可以在MRI系统的领域内有效地操作，而不会干扰其操作。电动机能够在断电的同时向驱动轴提供断裂力，从而有助于防止电机滑动或反向间隙。由于电动机不影响MRI系统的操作，所以可以使超声波治疗系统更加紧凑。两组位置编码器用于对准定位器。课程绝对编码器和精细的相对编码器都耦合到定位电机，并允许精确控制超声波换能器的位置和方向。

9. 发明授权

US5326049A Device including a body having folded appendage to be deployed upon acceleration 失效
标题翻译：装置包括具有折叠附件的主体，以在加速时部署
公开(公告)号：US5326049A
公开(公告)日：1994-07-05
申请号：US3045
申请日：1993-01-11
申请人： Hanan Rom , Oded Yehezkeli
发明人： Hanan Rom , Oded Yehezkeli
IPC分类号： F42B10/14
CPC分类号： F42B10/14 , Y10S343/02
摘要： A device, particularly a missile, includes a body having an appendage, e.g., a wing, normally folded in an inoperative position and to be unfolded to an operative position when the body is accelerated in the direction of the longitudinal axis of the body. The appendage is pivotally mounted about a first pivot axis extending perpendicularly to the longitudinal axis of the body, and also about a second pivot axis extending parallel to the longitudinal axis of the body. The center of gravity of the appendage is outwardly of the first pivot axis in the folded condition of the appendage such that the acceleration of the body produces a moment pivotting the appendage about the first pivot axis.
摘要翻译：一种装置，特别是导弹，包括具有附件的主体，例如机翼，其通常折叠在不工作的位置，并且当主体沿着身体的纵向轴线的方向被加速时展开到操作位置。附件围绕垂直于主体的纵向轴线延伸的第一枢转轴线枢转地安装，并且还围绕平行于主体的纵向轴线延伸的第二枢转轴线枢转地安装。在附件的折叠状态下，附件的重心在第一枢转轴线的外侧，使得身体的加速度产生使附件围绕第一枢转轴线枢转的力矩。

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