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    Fuse having self-destruct function and impact resistance
    31.
    发明授权
    Fuse having self-destruct function and impact resistance 有权
    保险丝具有自毁功能和抗冲击性

    公开(公告)号：US09103643B2

    公开(公告)日：2015-08-11

    申请号：US14357111

    申请日：2012-11-15

    Applicant: SEJU ENGINEERING CO., LTD

    Inventor： Won-Bae Lee

    IPC: F42B3/12 ,  F42C11/00 ,  F42C19/12 ,  F42C1/00 ,  F42C1/02 ,  F42C9/16

    CPC classification number: F42C11/00 ,  F42C1/00 ,  F42C1/02 ,  F42C9/16 ,  F42C19/12

    Abstract: There is provided an impact resistance self-destruct fuse installed in a shell and functioning to ignite explosion of the unexploded shell occurred in the case that a shell falls on the inclined ground or barriers but fails to be exploded by a mechanical fuse, by the configuration including a fuse slide having grooves formed on the top and the bottom at one side of the fuse slide so as to be easily breakable by absorbing the impact occurred when the shell falls and bounces, a battery displaced inside the portion of the fuse slide which is separated off by the grooves, and a battery hit needle located along the line where the battery is located in order to hit the battery, and a detonator exploded by the electric energy from the battery or exploding the impact resistance self-destruct fuse by sensing the short of the battery in circuits.

    Abstract translation: 提供了一种安装在壳体中的抗冲击自毁式保险丝，其功能是在壳体落在倾斜的地面或障碍物上而不能被机械保险丝分解的情况下发生未爆炸的壳体的爆炸， 包括具有形成在保险丝滑块的一侧的顶部和底部上的槽的保险丝滑块，以便通过吸收壳体掉落并弹跳时发生的冲击而容易地破裂，电池在保险丝滑块的部分内移位， 由凹槽分离，以及沿着电池所在的线路定位的电池击打针，以便撞击电池，并且由电池的电能分解的雷管或通过感测所述电池爆炸来防止耐冲击自毁式熔断器 短路电路中的电池。

    Guided weapon with in-flight-switchable multiple fuze modes
    32.
    发明授权
    Guided weapon with in-flight-switchable multiple fuze modes 有权
    具有飞行中可切换多重引信模式的导弹武器

    公开(公告)号：US08689692B2

    公开(公告)日：2014-04-08

    申请号：US12918327

    申请日：2009-02-12

    Applicant: Yariv Brill ,  Ohad Hanan Nuriel

    Inventor： Yariv Brill ,  Ohad Hanan Nuriel

    IPC: F42C9/14

    CPC classification number: F42B15/01 ,  F42B12/365 ,  F42C9/16 ,  F42C11/065 ,  F42C15/42

    Abstract: A method for operating a guided munition with a switchable fuze arrangement includes launching the guided munition towards a target. During flight of the guided munition, images are provided to a remote operator, who supplies a switching input. Responsive to said switching input, the fuze arrangement is switched to either of at least two of the following states: a delayed detonation state in which detonation of the explosive charge is delayed by a time delay after impact of the guided munition, an impact detonation state in which detonation of the explosive charge occurs on impact of the guided munition, a proximity detonation state in which detonation of the explosive charge is triggered by a proximity sensing arrangement, and a disabled state in which the guided munition functions as a guided kinetic shell without detonation of the explosive charge.

    Abstract translation: 用可切换的引信装置操作制导弹药的方法包括向目标发射导弹。 在飞行中的导弹弹药中，图像提供给遥控操作员，他们提供切换输入。 响应于所述切换输入，引信布置被切换到以下状态中的至少两个状态：延迟爆炸状态，其中爆炸装置的爆炸在受到导弹的冲击之后延迟时间延迟，撞击爆炸状态 其中爆炸装药的爆炸是在制导弹药的冲击下发生的，爆炸装置的爆炸引爆的邻近的爆炸状态是由接近感应装置引起的，而在这种情况下，被引导的弹药作为引导的动力弹壳起作用， 引爆炸药。

    Self-destruct fuze delay mechanism
    34.
    发明授权
    Self-destruct fuze delay mechanism 有权
    自毁引信延迟机制

    公开(公告)号：US07530313B2

    公开(公告)日：2009-05-12

    申请号：US11616625

    申请日：2006-12-27

    Applicant: William D. Chamlee ,  Jerry E. Smith ,  Berry W. Flournoy

    Inventor： William D. Chamlee ,  Jerry E. Smith ,  Berry W. Flournoy

    IPC: F42C15/34 ,  F42C15/38

    CPC classification number: F42C1/04 ,  F42C9/141 ,  F42C9/145 ,  F42C9/16 ,  F42C15/44

    Abstract: An exemplary self-destruct fuze delay for a submunition includes a container filled with an activation fluid, a spring-loaded ampoule breaker to break the container upon deployment of the munition, a spring-loaded self-destruct firing pin to initiate a secondary detonator in close proximity to a primary detonator, and an interlock ball supported by the ampoule breaker that locks the self-destruct firing pin away from the secondary detonator. The ampoule breaker includes a piston and a timing ball, which accesses the activation liquid. The action of the activation liquid on the timing ball over time causes the timing ball to erode until it is forced into the container by the spring-loaded piston. The movement of the piston frees the interlock ball, allowing the spring-loaded self-destruct firing pin to move under force and impact or initiate the secondary detonator. Initiation of the secondary detonator destroys the primary detonator and, depending upon slide location, either sterilizes the submunition, or destroys the entire submunition.

    Abstract translation: 子弹药的示例性自毁引信延迟包括填充有活化流体的容器，弹药加载的安瓿断路器，用于在部署弹药时破坏容器，弹簧加载的自毁式击发销以起动第二雷管 靠近主雷管，以及由安瓿断路器支撑的互锁球，其将自毁击发针锁定在第二雷管上。 安瓿断路器包括活塞和正时球，其接触活化液体。 激活液体对定时球的作用随着时间的推移导致定时滚珠被侵蚀，直到其被弹簧加载的活塞压入容器。 活塞的运动释放了互锁球，允许弹簧加载的自毁式撞针在力和冲击下移动或起动二次雷管。 第二雷管的启动会破坏主雷管，并根据滑轨位置对子弹药进行灭菌或者破坏整个子弹药。

    Electronic turns-counting fuze and method therefor
    35.
    发明授权
    Electronic turns-counting fuze and method therefor 失效
    电子转向计数引信及其方法

    公开(公告)号：US5705766A

    公开(公告)日：1998-01-06

    申请号：US550054

    申请日：1995-10-30

    Applicant: Louis Pasqual Farace ,  John Floyd Kaslow ,  Monty Wooson Bai

    Inventor： Louis Pasqual Farace ,  John Floyd Kaslow ,  Monty Wooson Bai

    IPC: F42C9/16 ,  F42C15/22 ,  F42C15/00 ,  F42C9/14

    CPC classification number: F42C9/16 ,  F42C15/22

    Abstract: A fuse (12) detonates a spin-stabilized projectile (10) after the fuse (12) experiences a preset number of turns. The preset number is communicated (64) to the fuse (12) prior to launch. A semiconductor piezoelectric strain gauge (26) senses stress and provides a signal which is responsive to centrifugal forces experienced by the sensor (26) as a result of projectile spin. A microcontroller (30) repetitively digitizes and translates the sensor signal to determine turn numbers, which the microcontroller (30) integrates to determine the total number of turns experienced by the fuse (12) since launch. When the accumulated turn number reaches (94) the preset number, the fuse (12) detonates the projectile (10). However, an arming duration (76) must have expired before the projectile (10) can detonate, and the projectile (10) can detonate at any time following the expiration of the arming duration when an impact is detected.

    Abstract translation: 保险丝（12）在保险丝（12）经受预设匝数之后引爆自旋稳定的射弹（10）。 在启动之前将预设号码（64）传送到保险丝（12）。 半导体压电应变仪（26）感测应力并提供响应于由于射弹旋转而由传感器（26）所经受的离心力的信号。 微控制器（30）重复地数字化和转换传感器信号以确定转向数，微控制器（30）集成以确定自启动以来熔丝（12）经历的总匝数。 当累积转弯数达到（94）预设值时，保险丝（12）引爆射弹（10）。 然而，在弹丸（10）可以引爆之前，布防时间（76）必须已经过期，并且在检测到冲击时，在弹药持续时间到期之后的任何时候，射弹（10）可以引爆。

    Settable pneumatic altitude detection equipment
    36.
    发明授权
    Settable pneumatic altitude detection equipment 失效
    可设置的气动高度检测设备

    公开(公告)号：US3827361A

    公开(公告)日：1974-08-06

    申请号：US39752673

    申请日：1973-09-17

    Applicant: US ARMY

    Inventor： BARBIERI J ,  CHANG N ,  ZECHNOWITZ A ,  XENAKIS J

    IPC: F42C5/02 ,  F42C9/16 ,  F42C5/00 ,  G01C19/30 ,  G01C21/00

    CPC classification number: F42C9/16 ,  F42C5/02 ,  Y10T74/12 ,  Y10T74/1239

    Abstract: A settable pneumatic altitude detection device provides an electrical signal to a missile or projectile for arming and destructing the missile or projectile at preset altitudes. The present invention''s main structural elements are a pair of sphere supports which hold therein a rotatable sphere assembly. The sphere support structure has two spherically shaped gas bearing pads which are separated and fixedly held to a circularly shaped collar. Two separate gas supplies are operatively positioned in the sphere support structure and in the rotatable sphere. An electrical initiating signal causes a gas release mechanism and a time delay valve, for each gas supply, to controllably release gas therefrom. Gas is forced through peripherally positioned jet nozzles on the sphere, and through operatively positioned venting ports and calibrated orifices in the sphere support structure. After the missile is fired, the sphere is pneumatically uncaged from its polar supporting structure so that it can freely spin on a nearly frictionless gas cushion. A pneumatically controlled distance meter operatively located in the sphere activates pressure operated switches on the ascent and the descent of the missile trajectory. The aforesaid switches provide an electrical signal which arms the missile on ascent and causes the missile to self-destruct on descent.

    Abstract translation: 可设置的气动高度检测装置为导弹或射弹提供电信号，用于在预设高度下布防和破坏导弹或射弹。 本发明的主要结构元件是一对球形支撑件，其中保持有可旋转的球体组件。 球体支撑结构具有两个球形的气体支承垫，它们被分离并固定地保持在圆形的套环上。 两个单独的气体供应器可操作地定位在球体支撑结构中并且在可旋转的球体中。 电启动信号使气体释放机构和每个气体供应的时间延迟阀可控制地从其中释放气体。 气体被迫通过球体上的外围定位的喷嘴，并且通过可操作地定位的排气口和球体支撑结构中的校准孔。 在导弹发射后，球体从其极性支撑结构中气动地开启，从而可以在几乎无摩擦的气垫上自由旋转。 可操作地位于球体中的气动控制距离计在导弹轨迹的上升和下降时激活压力操纵的开关。 上述开关提供一个电气信号，使导弹上升并使导弹在下降时自毁。

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