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1. 发明授权

US06431071B1 Mems arm fire and safe and arm devices 失效
标题翻译：手臂防火，安全和手臂装置
公开(公告)号：US06431071B1
公开(公告)日：2002-08-13
申请号：US09665230
申请日：2000-09-18
申请人： Kathleen F. Hodge , David H. Lewis, Jr. , Steven D. Nelson , Victor W. Ruwe
发明人： Kathleen F. Hodge , David H. Lewis, Jr. , Steven D. Nelson , Victor W. Ruwe
IPC分类号： F42C1526
CPC分类号： F42C15/36 , F42C15/184 , F42C15/34 , F42C15/40
摘要： Miniature arm fire and safe and arm devices include an electrically operated pyrotechnic initiation device (5) to generate a detonation wave upon command and a movable pressure barrier (9) that blocks propagation of the detonation wave if the device is not intended to be fired and opens a window (12) to transfer the detonation wave externally of the device. The detonation wave may in alternate embodiments be a subsonic flame front and pressure wave or a supersonic shock wave, respectively. An electromagnet (7) may serve to move the pressure barrier. Detonation waves output from the device have application in igniting an explosive train, either directly or indirectly, the latter by operating an electrical switch. In the arm fire device, the barrier automatically prevents a detonation output when electrical power is removed from the device. In the safe and arm device, the barrier, once moved out of the way, remains out of the way, even when electrical power is removed. Various forms of miniature single operate electrical switches are described that may be operated by the foregoing devices.
摘要翻译：微型手臂式防火和安全和手臂装置包括电动式烟火引发装置（5），用于在命令时产生爆震波;以及可移动压力屏障（9），其阻止爆震波的传播，如果该装置不打算被点燃，打开窗口（12）以将设备外部的爆震波转移。在替代实施例中，爆震波分别是亚音速火焰前和压力波或超音速冲击波。电磁体（7）可用于移动压力屏障。从设备输出的爆震波可以通过操作电气开关直接或间接点燃爆炸火车。在手臂消防装置中，当从设备中取出电力时，屏障自动防止爆震输出。在安全和手臂装置中，障碍物一旦被移开，即使在电力消除的情况下仍然存在。描述了可由前述装置操作的各种形式的微型单操作电开关。

2. 发明授权

US06622629B2 Submunition fuzing and self-destruct using MEMS arm fire and safe and arm devices 有权
标题翻译：子弹弹和自毁用MEMS手臂防火和安全臂装置
公开(公告)号：US06622629B2
公开(公告)日：2003-09-23
申请号：US09982158
申请日：2001-10-17
申请人： Kathleen F. Hodge , David K. Hoffmaster , William W. Mogan , Marion E. Fines , Daniel V. Haun
发明人： Kathleen F. Hodge , David K. Hoffmaster , William W. Mogan , Marion E. Fines , Daniel V. Haun
IPC分类号： F23Q2100
CPC分类号： F42C15/40 , F42C15/34
摘要： A fuze for a submunition is miniaturized in size by forming the fuze of a micro-electromechanical systems (“MEMS”) velocity sensor (38, 32, 34 and 36), a MEMs shock detector (31), a DC power supply (30) and one of the MEMs arm-fire device (2, FIG. 1) or MEMs safe and arm device (2, FIG. 5). Multiple fuzes may be incorporated in a fuze to ensure detonation of the explosive charge, should one fuze fail. A millimeter-microwave (“MMW”) receiver-decoder may be included to permit remote detonation on command from a remote transmitter (52) and/or a microprocessor (54) may be included to time the detonation to the physical characteristics of the target.
摘要翻译：通过形成微机电系统（“MEMS”）速度传感器（38,32,34和36），MEMs冲击检测器（31），直流电源（30）的引信，子弹药的引信尺寸小型化）和其中一个MEM臂防火装置（2，图1）或MEM的安全和臂装置（图5中的2）。如果一个引信失败，则可以在引信中引入多个fuzes以确保爆炸物的爆炸。可以包括毫米波微波（“MMW”）接收器 - 解码器以允许远程引爆来自远程发射器（52）的指令和/或微处理器（54）来引爆目标的物理特性。

3. 发明授权

US06293091B1 Axisymmetrical annular plug propulsion system for integrated rocket/ramjet or rocket/scramjet 失效
标题翻译：用于集成火箭/冲压喷气或火箭/冲击喷气的轴对称环形插头推进系统
公开(公告)号：US06293091B1
公开(公告)日：2001-09-25
申请号：US09296343
申请日：1999-04-22
申请人： Nathanael F. Seymour , Kathleen F. Hodge
发明人： Nathanael F. Seymour , Kathleen F. Hodge
IPC分类号： F02K1100
CPC分类号： F02K7/18 , F02K1/008 , Y02T50/671
摘要： The invention is an airframe which includes a vehicle (12) having a solid propellant rocket engine (14) and a ramjet or scramjet engine (16); a thrust plug (18) extending from an end (20) of the vehicle which directs combustion gases (23 and 64) produced by the solid propellant rocket engine or ramjet/scramjet engine to produce forward thrust; a longitudinal passage (38) extending from the end of the vehicle to an opening (30) forward of the end which receives external air directed by forward movement of the vehicle and in which solid propellant (32) of the solid propellant rocket engine is located, and wherein during rocket operation solid propellant is combusted to produce the combustion gases in the longitudinal passage which are conveyed by the longitudinal passage into contact with the thrust plug and during ramjet/scramjet operation the longitudinal passage is open to flow of external air after operation of the solid propellant rocket engine is completed and which supports mixing and combustion of the air/fuel by the ramjet/scramjet engine to produce combustion gases which are conveyed by the longitudinal passage into contact with the thrust plug.
摘要翻译：本发明是一种机身，其包括具有固体推进剂火箭发动机（14）和冲压喷气式或冲击式喷气发动机（16）的车辆（12）。推动塞（18），其从所述车辆的端部（20）延伸，其引导由所述固体推进剂火箭发动机或冲压喷气/冲击喷气发动机产生的燃烧气体（23和64）以产生向前推力; 从车辆的端部延伸到端部前方的开口（30）的纵向通道（38），其接收由车辆的向前运动引导的外部空气，固体推进剂火箭发动机的固体推进剂（32）位于其中，并且其中在火箭操作期间，固体推进剂被燃烧以产生纵向通道中的燃烧气体，其被纵向通道输送到与推力塞接触并且在冲压喷气/冲击喷射操作期间，纵向通道对操作后的外部空气流动是开放的的固体推进剂火箭发动机完成并且支持通过冲压喷气/冲击式发动机混合和燃烧空气/燃料，以产生燃烧气体，这些气体由纵向通道输送到与推力塞接触。

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