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81. 发明授权

US07530314B2 Thermally initiated venting system and method of using same 有权
标题翻译：热启动排气系统及其使用方法
公开(公告)号：US07530314B2
公开(公告)日：2009-05-12
申请号：US11128578
申请日：2005-05-13
申请人： Anthony T. Skinner , Michael L. Fortner , Marcus J. Dill , David N. Zichichi , Lamar R. Lunsford
发明人： Anthony T. Skinner , Michael L. Fortner , Marcus J. Dill , David N. Zichichi , Lamar R. Lunsford
IPC分类号： F42B15/36 , F02K9/38
CPC分类号： F42B39/20
摘要： An apparatus includes a thermally-activated, deflagration initiation device, a deflagration-to-detonation transition manifold, a first transfer line connecting the deflagration initiation device and the deflagration-to-detonation transition manifold, and a linear shaped charge coupled with the first transfer line. An apparatus includes a heat-to-detonation transition manifold, a heat pipe connected to the transition manifold, a linear shaped charge, and a transfer line connecting the heat-to-detonation transition manifold and the linear shaped charge. An apparatus includes a thermally-activated pyrotechnic train and a linear shaped charge coupled with the pyrotechnic train. A method includes initiating a deflagrating material at a predetermined temperature or within a predetermined range of temperatures, initiating a detonating material with the deflagrating material, and initiating a linear shaped charge with the detonated material.
摘要翻译：一种装置包括热活化的爆燃启动装置，爆燃至爆震过渡歧管，连接爆燃启动装置和爆燃至爆震过渡歧管的第一传输线以及与第一转移耦合的线性电荷线。一种装置包括热至爆震过渡歧管，连接到过渡歧管的热管，线性形状的电荷和连接热至爆震过渡歧管和线性电荷的传输线。一种装置包括热活化烟火列车和与烟火列车相连的线性电荷装置。一种方法包括在预定温度或预定温度范围内引发爆燃材料，起爆具有爆燃材料的引爆材料，以及引爆引爆材料的线性电荷。

82. 发明授权

US07478526B2 Speed control apparatus for a rotary sprinkler 有权
公开(公告)号：US07478526B2
公开(公告)日：2009-01-20
申请号：US11182379
申请日：2005-07-15
申请人： Michael A. McAfee , Cesar A. Gomez
发明人： Michael A. McAfee , Cesar A. Gomez
IPC分类号： F02K9/38 , B05B15/10
CPC分类号： B05B3/0422 , B05B15/70 , B05B15/74
摘要： A turbine for a sprinkler is disclosed for self-governing its rotational velocity. As a rate of fluid through the sprinkler increases, particularly when air is used to flush the sprinkler system, a portion of the turbine shifts outwardly so as to decrease alignment of vanes located thereon with directed water streams for controlling the rotation of the turbine.

83. 发明授权

US07373885B2 Device for venting a container housing an energetic material and method of using same 有权
标题翻译：用于排放容纳高能材料的容器的装置及其使用方法
公开(公告)号：US07373885B2
公开(公告)日：2008-05-20
申请号：US11261184
申请日：2005-10-28
申请人： Anthony T. Skinner
发明人： Anthony T. Skinner
IPC分类号： F41A17/16 , F02K9/38
CPC分类号： F42B39/20 , F42B39/14
摘要： A device for venting a container housing an energetic material includes an insulating portion, a charge holder disposed in the insulating portion, and an explosive cutting charge disposed in the charge holder. The device further includes a thermally activated initiation device, and a transfer line coupling the thermally activated initiation device and the explosive cutting charge. An apparatus includes a container, an energetic material disposed within the container, and a device, disposed within the container, for venting the container. The device for venting the container includes an insulating portion, a charge holder disposed in the insulating portion, and an explosive cutting charge disposed in the charge holder. The device for venting the container further includes a thermally activated initiation device, and a transfer line coupling the thermally activated initiation device and the explosive cutting charge.
摘要翻译：用于排放容纳高能材料的容器的装置包括绝缘部分，设置在绝缘部分中的电荷保持器，以及设置在电荷保持器中的爆炸性切割电荷。该装置还包括热激活起始装置和连接热激活起始装置和爆炸切割装料的传输线。一种装置包括容器，设置在容器内的能量材料，以及设置在容器内用于排出容器的装置。用于排出容器的装置包括绝缘部分，设置在绝缘部分中的电荷保持器和设置在电荷保持器中的爆炸性切割电荷。用于排出容器的装置还包括热激活的引发装置和连接热活化的引发装置和爆炸性切割装药的传输线。

84. 发明授权

US06873945B2 Rocket motor propellant temperature simulator 失效
标题翻译：火箭发动机推进剂温度模拟器
公开(公告)号：US06873945B2
公开(公告)日：2005-03-29
申请号：US09853076
申请日：2000-12-18
申请人： Jonathan R. Ross , Conan R. Schultz , Michael K Oetjen
发明人： Jonathan R. Ross , Conan R. Schultz , Michael K Oetjen
IPC分类号： F02K9/26 , F02K9/32 , F02K9/38 , F42B35/00 , G06G7/48 , F02K9/00 , F02K9/08 , F02K9/70 , F42B8/00
CPC分类号： F02K9/38 , F02K9/26 , F02K9/32 , F42B35/00
摘要： The present invention comprises a device which is inert and “thermally-equivalent” to actual ordnance. The device can travel with live ordnance and track the propellant temperatures in order to get a more precise propellant temperature for the ordnance. The device comprises a thermally equivalent inert grain instrumented with thermocouples, connected to a data recorder, and packaged in scaled-down ordnance hardware. The hardware is scaled down to enable the device to more easily travel with live munitions.
摘要翻译：本发明包括与实际弹药惰性和“热等效”的装置。该装置可以用活体运动并跟踪推进剂温度，以获得更精确的弹药推进剂温度。该装置包括装有热电偶的热等效惰性颗粒，连接到数据记录器，并包装在按比例缩小的弹药硬件中。硬件按比例缩小，使设备能够更容易地使用实时弹药旅行。

85. 发明授权

US5936188A Missile with a safe rocket ignition system 失效
标题翻译：导弹与安全的火箭点火系统
公开(公告)号：US5936188A
公开(公告)日：1999-08-10
申请号：US982655
申请日：1997-12-02
申请人： Bobby G. Atkinson
发明人： Bobby G. Atkinson
IPC分类号： F02K9/38 , F02K9/95 , F41A19/58 , F41G7/00 , F42B5/10 , F42B15/00 , F42C15/40 , F42B15/10 , F41F3/04
CPC分类号： F02K9/38 , F41A19/58 , F41G7/007 , F42B15/00 , F42B5/105 , F42C15/40
摘要： A rocket ignition system adapted for use with a missile having a rocket motor is provided. The rocket ignition system comprises (a) a first circuit for detecting an optical impulse and providing a first signal in response thereto; (b) a second circuit for detecting a pressure wave and providing a second signal in response thereto; and (c) a third circuit for launching the missile in response to the first and second signals. The rocket ignition system, which is easily adapted to existing missiles and rocket propelled devices, can reliably distinguish between the firing of a primer and other acoustic events occurring in noisy environments, such as a battlefield.
摘要翻译：提供适用于具有火箭发动机的导弹的火箭点火系统。火箭点火系统包括：（a）用于检测光脉冲并响应于此提供第一信号的第一电路; （b）用于检测压力波并响应于此提供第二信号的第二电路; 和（c）用于响应于第一和第二信号发射导弹的第三电路。容易适应现有导弹和火箭推进装置的火箭点火系统可以可靠地区分底漆的燃烧和在诸如战场的嘈杂环境中发生的其它声学事件。

86. 发明授权

US5735114A Thermostatic bimetallic retaining ring for use in rocket motor assembly 失效
标题翻译：用于火箭发动机总成的恒温双金属保持环
公开(公告)号：US5735114A
公开(公告)日：1998-04-07
申请号：US745531
申请日：1991-08-15
申请人： Warren W. Ellingsen
发明人： Warren W. Ellingsen
IPC分类号： F02K9/34 , F02K9/38 , F42B39/20 , F02K1/00
CPC分类号： F02K9/343 , F02K9/38 , F42B39/20 , F05D2300/50212
摘要： A device for safely attaching sections of a rocket motor is disclosed. The device is constructed such that if the temperature of the rocket motor is elevated to the point where ignition of the propellant within the rocket motor becomes a significant danger, the device allows the sections of the motor to disengage. The device comprises a bimetallic retaining ring which either contracts or expands in diameter upon heating. The retaining ring is positioned in such a manner as to lockingly engage two sections of the rocket motor at normal temperatures. At elevated temperatures, however, the expansion or contraction of the bimetallic retaining ring causes the sections of the motor to unlock from one another, such that if the propellant ignites the sections will disengage and the rocket will be rendered non-propulsive.
摘要翻译：公开了用于安全地安装火箭发动机部分的装置。该装置被构造成使得如果火箭发动机的温度升高到火箭发动机内的推进剂的点火成为显着的危险，则该装置允许电动机的部分脱离。该装置包括双金属保持环，其在加热时直径收缩或膨胀。保持环的定位方式是在常温下与火箭发动机的两部分锁定接合。然而，在升高的温度下，双金属保持环的膨胀或收缩导致马达的各部分彼此解锁，使得如果推进剂点燃该部分将分离，并且火箭将被非推进。

87. 发明授权

US5507231A Solid fuel launch vehicle destruction system and method 失效
标题翻译：固体燃料运载火箭破坏系统及方法
公开(公告)号：US5507231A
公开(公告)日：1996-04-16
申请号：US322917
申请日：1994-10-13
申请人： Steven E. Moore , F. Lynn Duce
发明人： Steven E. Moore , F. Lynn Duce
IPC分类号： F42B15/12 , B64G1/00 , B64G1/40 , B64G1/52 , B64G1/66 , F02K9/38 , F42B15/01 , F42B15/36 , F02K9/00
CPC分类号： F02K9/38 , B64G1/002 , B64G1/403 , B64G1/52 , F42B15/36
摘要： A system and method for shattering a launch vehicle into relatively small pieces are described. The launch vehicle includes at least one solid fuel rocket motor having a propellant disposed about a combustion chamber within a rocket motor case. Each rocket motor also includes at least one motor igniter to ignite the propellant and at least one explosive charge adjacent the rocket motor case. A firing unit is capable of generating a motor ignition signal and a charge explosion signal. A first propagator carries the motor ignition signal to the motor igniter so the signal arrives after a propagation time T.sub.ignition and causes ignition of the previously unignited rocket motor. A second propagator carries the charge explosion signal to the explosive charge so the signal arrives after a propagation time T.sub.explosion and causes an explosion against the rocket motor case. The time T.sub.explosion is greater than the time T.sub.ignition by a pressurization time T.sub.pressurization that is sufficient to allow pressurization of the combustion chamber before actuation of the explosive charge. Pressurization of the combustion chamber exerts forces on the rocket motor case which act in combination with the subsequent force from the explosion to shatter both the case and the propellant much more effectively than conventional destruction systems.
摘要翻译：描述了将运载火车撞击成相对小的部件的系统和方法。运载火箭包括至少一个固体燃料火箭发动机，其具有围绕火箭发动机壳体内的燃烧室设置的推进剂。每个火箭发动机还包括至少一个电动机点火器以点燃推进剂和在火箭发动机壳体附近的至少一个爆炸物。点火单元能够产生电动机点火信号和充电爆炸信号。第一传播器将电动机点火信号传送到电动机点火器，使得信号在传播时间Tignition之后到达，并引起先前未被标记的火箭发动机点火。第二个传播者将充电爆炸信号传送到爆炸装置，使信号在传播时间T爆炸后到达，并对火箭发动机壳体造成爆炸。时间T爆炸大于时间Tignition通过加压时间T加压，足以允许在致动爆炸炸药之前对燃烧室进行加压。燃烧室的加压对火箭发动机壳体施加力，其结合来自爆炸的随后的力与传统的破坏系统相比更有效地破坏壳体和推进剂。

88. 发明授权

US5228285A Solid propellant rocket motor case for insensitive munitions requirements 失效
标题翻译：固体推进剂火箭发动机用于不灵敏弹药的要求
公开(公告)号：US5228285A
公开(公告)日：1993-07-20
申请号：US843068
申请日：1992-03-02
申请人： Frederick W. Van Name , Michael A. Gerace , Robert G. Gleeson
发明人： Frederick W. Van Name , Michael A. Gerace , Robert G. Gleeson
IPC分类号： F02K9/38 , F42B39/20
CPC分类号： F02K9/38 , F42B39/20
摘要： The invention is a propellant rocket motor case designed to meet insensitive munitions requirements comprising a propellant surrounded by a case having slots therein, and a wrapping around the case, the wrapping comprising a load bearing material which can withstand the hoop load on the case during normal firing of said rocket, the material also having the characteristic of losing strength or melting at undesired temperatures above normal storage temperatures, but below the autoignition temperature of said propellant, so that during undesired high storage temperatures the propellant will exhaust any subsequently generated gases, due to any subsequent propellant burning, by venting through said slots thereby avoiding any explosion or undesired operative one-way thrust.

89. 发明授权

US5170007A Tailorable roll-bonded insensitive munitions case 失效
标题翻译：卷边不灵敏弹药案
公开(公告)号：US5170007A
公开(公告)日：1992-12-08
申请号：US775526
申请日：1991-10-15
申请人： Irving E. Figge, Sr.
发明人： Irving E. Figge, Sr.
IPC分类号： F02K9/34 , F02K9/38 , F42B39/14 , F42B39/20
CPC分类号： F02K9/34 , F02K9/38 , F42B39/20
摘要： A tailorable, roll-bonded, insensitive munitions motor case and method of production. The motor case comprises a sheet of fiber reinforced thermoplastic, thermoset or other suitable material rolled to form a case with a tubular configuration having at least one layer of material, and a coating of adhesive on at least part of said sheet for bonding the sheet to itself for maintaining the tubular configuration. The adhesive has a bond-strength breakdown temperature which is below the autoignition temperature of the housed propellant, thereby enabling the case to separate and un-roll when the breakdown temperature is reached to preclude dangerous propellant pressurization within the case. The method of production includes the steps of applying an adhesive to the sheet, rolling the sheet around a cylindrical tool to form a tubular case having at least one layer, and curing the case. Preferably the case is cured while on a tool which has a coefficient of thermal expansion which is greater than that of the sheet. Also, the sheet may be rolled such that there is a longitudinal section of the case which has one less layer of material than the remainder of the case, thereby to cause the case to fail along the longitudinal section if over-pressurization should occur.
摘要翻译：一个可裁剪，滚动，不敏感的弹药马达案例和生产方法。电动机壳体包括一片纤维增强热塑性塑料，热固性材料或其它合适的材料，其被轧制以形成具有至少一层材料的管状构造的壳体，以及在所述片材的至少一部分上的粘合剂涂层，用于将片材粘合到本身用于维持管状构造。粘合剂具有低于所容纳的推进剂的自燃温度的粘结强度击穿温度，从而能够在达到击穿温度时使外壳分离和脱开，以防止外壳内的危险推进剂加压。生产方法包括以下步骤：将粘合剂施加到片材上，将片材卷绕在圆柱形工具上以形成具有至少一层的管状壳体，并固化壳体。优选地，在具有大于片材的热膨胀系数的工具上固化的情况。此外，片材可以卷起，使得壳体的纵向部分具有比壳体的其余部分少一层的材料，从而如果发生过度加压，则使壳体沿纵向部分失效。

90. 发明授权

US5060470A Gas generator ventable at a high temperature for hazard reduction 失效
标题翻译：气体发生器在高温下通风，可减少危害
公开(公告)号：US5060470A
公开(公告)日：1991-10-29
申请号：US526884
申请日：1990-05-22
申请人： Frederick W. VanName
发明人： Frederick W. VanName
IPC分类号： F02K9/34 , F02K9/38 , F42B39/20
CPC分类号： F42B39/20 , F02K9/34 , F02K9/38 , Y10S428/902 , Y10T428/24995
摘要： A rocket motor or other gas generator the case of which is ventable at a predetermined temperature substantially greater than the ambient temperature range for storage and operation thereof and substantially less than the auto-ignition temperature of gas generant material contained therein so as to prevent catastrophic propulsion or burst in case of fire. The venting is provided by memory metal members which are interleaved between plies of matrix-impregnated fibrous material in the case and which have a transformation temperature which is substantially higher than the ambient temperature range and substantially lower than the auto-ignition temperature and characterized by a change in shape when heated to a temperature above the transformation temperature.
摘要翻译：一种火箭发动机或其他气体发生器，其情况是在明显高于用于储存和运行的环境温度范围的预定温度下通风并且基本上小于其中包含的气体发生剂材料的自燃温度，以便防止灾难性推进或在发生火灾时爆裂。通气由存储金属构件提供，该存储金属构件在壳体中基体浸渍的纤维材料层之间交错并且具有显着高于环境温度范围并且显着低于自燃温度的相变温度，并且其特征在于：当加热到高于转化温度的温度时，形状发生变化。

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