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81. 发明授权

US6003809A Process and apparatus for discouraging countermeasures against a weapon transport device 失效
标题翻译：用于阻止对武器运输装置的对策的方法和装置
公开(公告)号：US6003809A
公开(公告)日：1999-12-21
申请号：US804635
申请日：1997-02-25
申请人： Richard F. Honigsbaum
发明人： Richard F. Honigsbaum
IPC分类号： B64D1/04 , F41G7/34 , F42B12/46 , F41G7/00 , F42B15/10 , F42B45/00
CPC分类号： B64D1/04 , F41G7/346 , F41G7/36 , F42B12/46 , Y10S376/914
摘要： A weapon transport device transports along a path toward a target in hostile territory, (1) a target-intended weapon and (2) biological, chemical and/or radioactive agents for attacking the occupants of such territory should they execute countermeasures against the weapon transport device. Separation of the biological, chemical and/or radioactive agents is initiated or, where appropriate, inhibited, by signals from either the guidance system of the transport device or from on-board Global Positioning System (GPS) receivers when the transport device strays by more than a predetermined distance from the path, the sensor is blinded, or the transport device passes beyond a predetermined point while en route to the target.
摘要翻译：武器运输装置沿着朝向敌对领土的目标的道路运输，（1）目标武器和（2）生物，化学和/或放射剂，用于攻击这些领土的居民，如果它们对武器运输采取反措施设备。生物，化学和/或放射剂的分离是通过来自运输装置的引导系统或车载全球定位系统（GPS）接收器的信号在适当时被抑制的，当运输装置偏移更多时距离路径的预定距离，传感器被盲目，或者运输装置在到达目标的途中通过超过预定点。

82. 发明授权

US5927643A Self-deploying airfoil for missile or the like 失效
标题翻译：用于导弹等的自身部署翼型
公开(公告)号：US5927643A
公开(公告)日：1999-07-27
申请号：US964856
申请日：1997-11-05
申请人： Irving E. Figge, Sr.
发明人： Irving E. Figge, Sr.
IPC分类号： F42B10/16 , F42B15/10 , F42B10/00
CPC分类号： F42B15/105 , F42B10/16
摘要： A self-deploying airfoil for a missile or the like of the type that is launched from a launch tube, the airfoil being formed of a flexible and resilient material and being movable by its own resilience from a stowed position in close proximity to the exterior surface of the missile when it is in the launch tube to a deployed position when the missile leaves the launch tube wherein it extends outwardly from the missile to provide lift and stabilize the flight of the missile. The airfoil comprises in its deployed position a first panel extending laterally outwardly from both sides of the missile and being secured at its midportion to an adjacent exterior surface of the missile, a pair of second panels secured at their outer ends to the outer end of the first panel and extending inwardly toward the missile, and a third panel secured at its midportion to an adjacent exterior surface of the missile opposite the first panel. The third panel extends laterally outwardly from both sides of the missile and is connected to the inner ends of the second panels. The third panel has end portions in engagement with the first panel to stabilize the airfoil. In the stowed position of the airfoil, the first panel is folded over the second panels which are, in turn, folded over the third panel in close proximity to the exterior surface of the missile to enable it to be positioned in the launch tube.
摘要翻译：一种用于从发射管发射的类型的导弹等的自展开翼型，翼型由柔性和弹性材料形成，并且可通过其自身的弹性从靠近外表面的收起位置移动当导弹离开发射管时，它在发射管中到达部署位置时，其中导弹从导弹向外延伸以提供升力并稳定导弹的飞行。翼型件在其展开位置包括从导弹的两侧横向向外延伸的第一面板，并且在其中部固定到导弹的相邻外表面，一对第二面板在其外端固定到该导弹的外端第一面板并朝向导弹向内延伸，并且第三面板在其中部固定到与第一面板相对的导弹的相邻外表面。第三面板从导弹的两侧横向向外延伸并连接到第二面板的内端。第三面板具有与第一面板接合的端部，以稳定翼型件。在机翼的收起位置中，第一面板折叠在第二面板上，第二面板又靠近导弹的外表面折叠在第三面板上，以使其能够定位在发射管中。

83. 发明授权

US5886289A Long range artillery shell 失效
标题翻译：远程炮兵壳
公开(公告)号：US5886289A
公开(公告)日：1999-03-23
申请号：US94996
申请日：1993-07-16
申请人： Robert J. Nixon , Martin J. Lewin , Terence L. Spellward
发明人： Robert J. Nixon , Martin J. Lewin , Terence L. Spellward
IPC分类号： F02K9/95 , F42B10/40 , F42B12/20 , F42B12/58 , F42B15/10
CPC分类号： F42B10/40 , F02K9/95
摘要： A long range artillery shell (1) comprising rocket propellant material (10), a rocket motor nozzle (14) and base bleed propellant material (12). Ignition of the rocket propellant material (10) is delayed until the base bleed propellant material (12) has substantially finished burning. The base bleed propellant material (12) may be housed in the same chamber and behind the rocket propellant material (10) in order to provide support to the rocket propellant material (10) during launch. The two propellant materials (10, 12) may be separated by a thermal ignition barrier (18) to prevent premature rocket ignition.
摘要翻译：包括火箭推进剂材料（10），火箭发动机喷嘴（14）和基部喷射推进剂材料（12）的远程炮弹（1）。火箭推进剂材料（10）的点火被延迟，直到基本排出的推进剂材料（12）基本上完成燃烧。基础排放推进剂材料（12）可以容纳在相同的室中并在火箭推进剂材料（10）的后面，以便在发射期间向火箭推进剂材料（10）提供支撑。两个推进剂材料（10,12）可以由热点火屏障（18）分开，以防止过早的火箭点火。

84. 发明授权

US5792981A Gun-launched rocket 失效
标题翻译：枪弹发射火箭
公开(公告)号：US5792981A
公开(公告)日：1998-08-11
申请号：US739469
申请日：1996-10-28
申请人： Victor Singer , Mark A. Solberg
发明人： Victor Singer , Mark A. Solberg
IPC分类号： F02K9/34 , F42B15/00 , F42B39/20 , F42B15/10 , F02K9/00
CPC分类号： F42B39/20 , F02K9/343 , F42B15/00
摘要： A rocket system employing at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at launch. The rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched rocket systems in a manner that allows for thinner case cylinder design and increased propellant volume.
摘要翻译：火箭系统采用至少一个火箭发动机闭合器，其包括低负载能力和高负载能力的保持器，其分别在发射时在喷嘴组件的存储和正锁定期间提供不敏感的弹药系统。火箭发动机还包括压力平衡系统，其适应存储期间变化的温度条件以及枪射发射火箭系统固有的气体压力变化，从而允许更薄的气缸设计和增加的推进剂体积。

85. 发明授权

US4739705A Arming and motor ignition device 失效
标题翻译：装甲和电机点火装置
公开(公告)号：US4739705A
公开(公告)日：1988-04-26
申请号：US924483
申请日：1986-10-29
申请人： James Hudson , Alan W. Holt
发明人： James Hudson , Alan W. Holt
IPC分类号： F42C15/24 , F42C15/31 , F42C15/40 , F42B15/10 , F42C15/34
CPC分类号： F42C15/40 , F42C15/24 , F42C15/31
摘要： A combined warhead arming and drive motor ignition device for a self-propelled missile having a warhead and a drive motor comprises a first acceleration responsive means (1, 2, 3, 4) to provide an output when the missile achieves a first acceleration, a timer initiated by the output from the first acceleration responsive means and providing a first output (i) after expiry of a first period and before expiry of a second period and a second output (v) after expiry of a third period, and a speed responsive means (5, 6) to provide a speed output (ii) when the missile has attained a predetermined speed and also to provide a first distance indication output (vi) when the missile has travelled a first distance but has not yet travelled a second distance and a second distance indication (vi) output when the missile has travelled a third distance. The device also includes gating means to provide an output in response to the receipt of all of the first output (i) from the timer, the speed output (ii) and the first distance indication output of the speed responsive means, ignition means to ignite the drive motor in response to the output of the gating means, and second acceleration responsive means (12, 13) which are enabled by the second output (vi) of the timing means and by the second distance indication output (vi) of the speed responsive means and which, when subjected to a predetermined acceleration consistent with successful ignition of the drive motor, enables arming and firing of the warhead.
摘要翻译：用于具有弹头和驱动马达的自推进导弹的组合弹头布防和驱动马达点火装置包括第一加速度响应装置（1,2,3,4），以在导弹达到第一加速时提供输出，定时器由第一加速度响应装置的输出启动，并且在第一周期期满之后以及在第三周期期满之后第二周期和第二输出（v）到期之前提供第一输出（i）当导弹达到预定速度时提供速度输出（ii）的装置（5,6），并且当导弹已经行进第一距离但还没有行进第二距离时提供第一距离指示输出（vi）并且当导弹已经行进了第三距离时输出第二距离指示（vi）。该装置还包括选通装置，以响应于从定时器接收到所有第一输出（i），速度输出（ii）和速度响应装置的第一距离指示输出，点火装置点火所述驱动马达响应于所述选通装置的输出;以及第二加速度响应装置（12,13），其由所述定时装置的第二输出（vi）和所述速度的所述第二距离指示输出（vi）启用并且当受到与驱动电机的成功点火一致的预定加速时，使得能够布防和发射弹头。

86. 发明授权

US4646642A Separating arrangement including an expansion chamber for a pyrotechnic charge 失效
标题翻译：分离装置包括用于烟火炸药的膨胀室
公开(公告)号：US4646642A
公开(公告)日：1987-03-03
申请号：US707643
申请日：1985-03-04
申请人： Josef Nagler , Utz-Udo Ahlers
发明人： Josef Nagler , Utz-Udo Ahlers
IPC分类号： F42B15/36 , F42B15/10
CPC分类号： F42B15/36
摘要： A separating arrangement between multipart constructional elements, including an expansion chamber for at least one pyrotechnic charge which is bounded by the piston surface of a displacement or sliding piston. The separating arrangement has at least one gas passageway which communicates with the expansion chamber, through the intermediary of which a separating piston can be subjected to pressure. The combustion gas pressure of the pyrotechnic charges acts within the expansion chamber against different piston surfaces and thereby, in a constructively predeterminable manner, effects different successive piston movements, as a result of which the sequence of the individual separating operations which can be carried out in different directions predeterminably in a definite manner and functionally-dependent.
摘要翻译：多部分结构元件之间的分离装置，包括用于至少一个烟火装料的膨胀室，其由位移或滑动活塞的活塞表面限定。分离装置具有与膨胀室连通的至少一个气体通道，通过其中间分离活塞可以承受压力。烟火充电器的燃烧气体压力作用在膨胀室内，抵抗不同的活塞表面，从而以建设性地可预先确定的方式影响不同的连续的活塞运动，结果可以将单独分离操作的顺序以确定的方式和功能依赖性可预见的不同方向。

87. 发明授权

US4574699A Extendible wafer igniter with perforations adjacent the foot portion 失效
标题翻译：具有邻近脚部的穿孔的可扩展的晶片点火器
公开(公告)号：US4574699A
公开(公告)日：1986-03-11
申请号：US552650
申请日：1983-11-17
申请人： Christopher W. Bolieau
发明人： Christopher W. Bolieau
IPC分类号： F42C19/08 , F42B15/10
CPC分类号： F42C19/0819
摘要： A closed urethane cylindrical case includes a mounting base or foot which runs parallel to the axis of the case and is bonded to the surface of the propellant grain of a full head-end-web rocket motor. Contained within the case are one or more spaced tube initiators and concentrically positioned discs or webs of high energy propellant. Flaming gases resulting from actuation of the tube initiators and consequent burning of the propellant wafers are projected over the surface of the rocket motor propellant from a plurality of nozzle ports that are provided in the cylindrical case, in the quadrants thereof adjacent the surface of the rocket motor propellant. Cylindrical case length and the number of tube initiators and propellant wafers including their spacing can be selected as required to achieve a desired mass flow rate.
摘要翻译：封闭的聚氨酯圆筒形壳体包括安装基座或脚，其平行于壳体的轴线延伸并且结合到完整的头端卷筒式火箭发动机的推进剂颗粒的表面。在这种情况下包含一个或多个间隔管引发器和高精度推进剂的同心定位的盘或腹板。火焰发动机的致动所引起的火焰气体和随之而来的推进剂晶片的燃烧，从设置在圆筒形壳体中的多个喷嘴端口突出到火箭发动机推进剂的表面上，在其邻近火箭表面的象限中机动推进剂。可以根据需要选择圆柱形壳体长度和包括它们的间距的管引发剂和推进剂晶片的数量以实现期望的质量流量。

88. 发明授权

US4542695A Contoured configured detonating cord and detonator 失效
标题翻译：轮廓配置引爆线和雷管
公开(公告)号：US4542695A
公开(公告)日：1985-09-24
申请号：US478385
申请日：1983-03-24
申请人： Robert E. Betts , John F. Crawford , Jacqueline C. Meador
发明人： Robert E. Betts , John F. Crawford , Jacqueline C. Meador
IPC分类号： F42B15/36 , F42B15/10
CPC分类号： F42B15/36
摘要： A contoured configured detonating cord and detonator is incorporated into aember during manufacture thereof. The member may be a rocket motor which is disposed to be broken into small fragments over inhabited areas subsequent to separation of the motor from the warhead. Separation permits the warhead to fly to the target without excessive drag and fragmenting the motor prevents large pieces from falling on the inhabitants. The detonating cord is contoured to the configuration of the motor to prevent stress risers from occurring and thereby weakening the motor structure.
摘要翻译：在其制造期间，将构形成形的引爆线和雷管引入到构件中。该构件可以是火箭发动机，其被设置成在马达与弹头分离之后被破坏成居住区域的小碎片。分离允许弹头飞行到目标，没有过多的拖动和分裂，马达防止大块落在居民身上。引爆线的轮廓与电动机的结构相似，以防止发生应力梯级，从而削弱电机结构。

89. 发明授权

US4522356A Multiple target seeking clustered munition and system 失效
标题翻译：多目标寻求集群弹药和系统
公开(公告)号：US4522356A
公开(公告)日：1985-06-11
申请号：US415452
申请日：1973-11-12
申请人： Clair K. Lair , Jules Jonas , Keith D. Anderson
发明人： Clair K. Lair , Jules Jonas , Keith D. Anderson
IPC分类号： F41G7/22 , F42B10/64 , F42B15/10 , F42B23/04
CPC分类号： F42B10/64 , F41G7/2233 , F42B15/105 , F42B23/04
摘要： A clustered munition in a system for low altitude aerial delivery, which releases multiple rocket powered missiles, each having the capability to cruise at a constant altitude and search for a target. Once a target is identified, the missile homes on and strikes the target. In the preferred form the target seeking means is a radiometric seeker operating in the millimeter wavelength range, in which metal or similarly reflective targets stand out against the background and provide a significant signal which is used to program the terminal action of the missile.
摘要翻译：一种用于低空空中交付系统的集群弹药，其释放多个火箭弹导弹，每个弹道导弹都能够在恒定高度巡航并搜索目标。一旦确定了一个目标，那么导弹的住房就在目标之上。在优选形式中，目标寻求装置是在毫米波长范围内工作的辐射探测器，其中金属或类似的反射目标相对于背景突出出来，并提供用于编程导弹的终端动作的重要信号。

90. 发明授权

US4502649A Gun-launched variable thrust ramjet projectile 失效
标题翻译：枪式推力可变推力冲击射弹
公开(公告)号：US4502649A
公开(公告)日：1985-03-05
申请号：US495203
申请日：1983-05-16
申请人： Leo Botwin , John A. Simpson
发明人： Leo Botwin , John A. Simpson
IPC分类号： F02C7/057 , F02K7/10 , F42B10/38 , F42B15/00 , F42B15/10
CPC分类号： F02C7/057 , F02K7/105 , F42B10/38 , F42B15/00
摘要： A gun-launched ramjet projectile follows a classical vacuum ballistic trajectory by maintaining a thrust-drag balance. The thrust of the ramjet is varied by an air door which bleeds air from the duct that leads from the supersonic diffuser at the front of the projectile to the combustion chamber. The control system for the air door includes an actuator and a pair of accelerometers, the output of which is integrated to provide an indication of velocity. The first accelerometer operates during the launching of the projectile in the gun to measure the launch velocity. A second, and more sensitive, accelerometer measures in-flight velocity changes due to atmospheric conditions. Both of the measured velocities are compared with prerecorded standards and error signals are derived representing any velocity deviations. These error signals are combined and then used to drive the air doors which varies the thrust of the ramjet so that it follows the classical vacuum ballistic trajectory.
摘要翻译：喷枪式冲压射弹遵循经典的真空弹道轨迹，通过保持推力 - 阻力平衡。冲压喷气机的推力由一个空气门变化，空气门将导管的空气从喷射器前部的超音速扩散器引导到燃烧室。用于空气门的控制系统包括致动器和一对加速度计，其输出被一体化以提供速度指示。第一个加速度计在炮弹发射时测量发射速度。第二个更敏感的加速度计测量由于大气条件的飞行中速度变化。将所测量的速度与预先记录的标准进行比较，并且导出代表任何速度偏差的误差信号。将这些误差信号组合起来，然后用于驱动改变冲压喷气机推力的气门，使其符合经典的真空弹道轨迹。

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