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公开(公告)号：US07895948B2
公开(公告)日：2011-03-01
申请号：US12698611
申请日：2010-02-02
摘要： Embodiments of a buoyancy dissipater and method for deterring an errant vessel are generally described herein. In some embodiments, a volume of gas is generated from a propellant and diffused below a waterline of a vessel. The resulting gas bubble dissipates the buoyancy of the vessel providing a non-lethal deterring effect. The buoyancy dissipater includes a diffuser having radially-positioned diffusion ports to radially diffuse the gas generated by a gas generator below the waterline. In some embodiments, the radially-positioned diffusion ports comprise holes positioned radially around the diffuser to diffuse the gas around the buoyancy dissipater.
摘要翻译： 浮力消散器的实施例和用于阻止错误的容器的方法一般在此描述。 在一些实施方案中，从推进剂产生一定体积的气体并在容器的水线下方扩散。 所产生的气泡消散了船舶的浮力，提供了非致命的阻止作用。 浮力消散器包括具有放射状位置的扩散口的扩散器，用于使由水线下方的气体发生器产生的气体径向扩散。 在一些实施例中，径向定位的扩散端口包括围绕漫射器径向设置的孔，以使气体围绕浮力耗散器扩散。
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公开(公告)号：US20120091253A1
公开(公告)日：2012-04-19
申请号：US12198146
申请日：2008-08-26
申请人： William N. Patterson , James H. Dupont , Richard D. Loehr , Henri Y. Kim , Garrett L. Hall , James M. Cook
发明人： William N. Patterson , James H. Dupont , Richard D. Loehr , Henri Y. Kim , Garrett L. Hall , James M. Cook
IPC分类号： F42B15/01
CPC分类号： F41H11/02 , F41F3/073 , F42B10/661 , F42B15/01 , F42B15/10
摘要： A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.
摘要翻译： 一种击败诸如火箭推进手榴弹的进入导弹的方法包括软启动拦截导弹，然后使用拦截导弹发动机的俯仰角来将导弹的过程改变到所需的拦截方向。 通过以相对较慢的速度（例如小于或等于40米/秒（130英尺/秒）的速度）发射，拦截导弹可以在发射的250毫秒内达到所需的拦截方向。 拦截导弹可以能够围绕发射位置覆盖半球或更大程度上的所有拦截方向。 例如，拦截导弹可以从地面车辆垂直发射，并且能够在250毫秒内改变任何地面上的轨迹。
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公开(公告)号：US20100192798A1
公开(公告)日：2010-08-05
申请号：US12698611
申请日：2010-02-02
摘要： Embodiments of a buoyancy dissipater and method for deterring an errant vessel are generally described herein. In some embodiments, a volume of gas is generated from a propellant and diffused below a waterline of a vessel. The resulting gas bubble dissipates the buoyancy of the vessel providing a non-lethal deterring effect. The buoyancy dissipater includes a diffuser having radially-positioned diffusion ports to radially diffuse the gas generated by a gas generator below the waterline. In some embodiments, the radially-positioned diffusion ports comprise holes positioned radially around the diffuser to diffuse the gas around the buoyancy dissipater.
摘要翻译： 浮力消散器的实施例和用于阻止错误的容器的方法一般在此描述。 在一些实施方案中，从推进剂产生一定体积的气体并在容器的水线下方扩散。 所产生的气泡消散了船舶的浮力，提供了非致命的阻止作用。 浮力消散器包括具有放射状位置的扩散口的扩散器，用于使由水线下方的气体发生器产生的气体径向扩散。 在一些实施例中，径向定位的扩散端口包括围绕漫射器径向设置的孔，以使气体围绕浮力耗散器扩散。
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公开(公告)号：US07730838B1
公开(公告)日：2010-06-08
申请号：US12362547
申请日：2009-01-30
摘要： Embodiments of a buoyancy dissipater and method for deterring a vessel are generally described herein. In some embodiments, a volume of gas is generated from a propellant and diffused below a waterline of a vessel. The resulting gas bubble dissipates the buoyancy of the vessel providing a non-lethal deterring effect.
摘要翻译： 在此通常描述用于阻止容器的浮力消散器和方法的实施例。 在一些实施方案中，从推进剂产生一定体积的气体并在容器的水线下方扩散。 所产生的气泡消散了船舶的浮力，提供了非致命的阻止作用。
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公开(公告)号：US08173946B1
公开(公告)日：2012-05-08
申请号：US12198146
申请日：2008-08-26
申请人： William N. Patterson , James H. Dupont , Richard D. Loehr , Henri Y. Kim , Garrett L. Hall , James M. Cook
发明人： William N. Patterson , James H. Dupont , Richard D. Loehr , Henri Y. Kim , Garrett L. Hall , James M. Cook
CPC分类号： F41H11/02 , F41F3/073 , F42B10/661 , F42B15/01 , F42B15/10
摘要： A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.
摘要翻译： 一种击败诸如火箭推进手榴弹的进入导弹的方法包括软启动拦截导弹，然后使用拦截导弹发动机的俯仰角来将导弹的过程改变为所需的拦截方向。 通过以相对较慢的速度（例如小于或等于40米/秒（130英尺/秒）的速度）发射，拦截导弹可以在发射的250毫秒内达到所需的拦截方向。 拦截导弹可以能够围绕发射位置覆盖半球或更大程度上的所有拦截方向。 例如，拦截导弹可以从地面车辆垂直发射，并且能够在250毫秒内改变任何地面上的轨迹。
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公开(公告)号：US08181444B2
公开(公告)日：2012-05-22
申请号：US12240223
申请日：2008-09-29
IPC分类号： F02K9/00
CPC分类号： F02K9/18
摘要： A motor includes an annular solid fuel between an inside diameter and an outside diameter. The solid fuel has a series of radial notches that define segments of fuel between them. The notches allow for faster burning of the fuel, while still allowing structural integrity of the fuel segments to be retained during the burning process.
摘要翻译： 马达包括在内径和外径之间的环形固体燃料。 固体燃料具有在它们之间限定燃料段的一系列径向凹口。 切口允许更快地燃烧燃料，同时仍然允许在燃烧过程中保持燃料段的结构完整性。
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公开(公告)号：US20100077723A1
公开(公告)日：2010-04-01
申请号：US12240223
申请日：2008-09-29
IPC分类号： C06B45/00
CPC分类号： F02K9/18
摘要： A motor includes an annular solid fuel between an inside diameter and an outside diameter. The solid fuel has a series of radial notches that define segments of fuel between them. The notches allow for faster burning of the fuel, while still allowing structural integrity of the fuel segments to be retained during the burning process.
摘要翻译： 马达包括在内径和外径之间的环形固体燃料。 固体燃料具有在它们之间限定燃料段的一系列径向凹口。 切口允许更快地燃烧燃料，同时仍然允许在燃烧过程中保持燃料段的结构完整性。
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公开(公告)号：US20120269633A1
公开(公告)日：2012-10-25
申请号：US13089441
申请日：2011-04-19
CPC分类号： F02K9/00 , B64C2201/042 , F02K9/42 , F02K9/425 , F02K9/50 , F02K9/52 , F02K9/68 , H02J7/00 , H02K7/1823
摘要： A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
摘要翻译： 气体发生器组件包括容纳胺基推进剂的推进剂室。 反应室与推进剂室结合。 反应室包括反应室壳体和反应室壳体内的多孔反应基质。 反应基质包括催化剂，并且催化剂被配置为不可燃地将胺基推进剂催化成一种或多种加压气体。 喷射器与推进剂室连通。 喷射器构造成将胺基推进剂输送到多孔反应基质。 排放喷嘴与反应室联接并且构造成加速和排出一个或多个加压气体。 在一个示例中，气体发生器与脉冲涡轮机组件和发电机中的一个或多个耦合以形成微动力单元。
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公开(公告)号：US07966805B2
公开(公告)日：2011-06-28
申请号：US11748843
申请日：2007-05-15
申请人： Richard D. Loehr
发明人： Richard D. Loehr
IPC分类号： C06D5/04
CPC分类号： F02K9/72
摘要： A new rocket motor assembly configuration is disclosed. Amine based oxidizer is decomposed in the presence of a metallic catalyst to generate an oxygen rich hot gas stream. The hot gas stream is used to trigger a Magnesium based solid fuel in the combustion chamber. The thrust of the rocket motor may be regulated at multiple points. This design thus offers an IM compliant, thrust-adjustable rocket motor that is of a low hazard classification without compromising its performance.
摘要翻译： 公开了一种新的火箭发动机组件结构。 胺类氧化剂在金属催化剂的存在下分解，产生富氧的热气流。 热气流用于在燃烧室中触发镁基固体燃料。 火箭发动机的推力可以在多个点进行调节。 因此，该设计提供了IM兼容的推力可调式火箭发动机，其危险性低，不会影响其性能。
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公开(公告)号：US08636247B2
公开(公告)日：2014-01-28
申请号：US13089441
申请日：2011-04-19
IPC分类号： B64C15/00
CPC分类号： F02K9/00 , B64C2201/042 , F02K9/42 , F02K9/425 , F02K9/50 , F02K9/52 , F02K9/68 , H02J7/00 , H02K7/1823
摘要： A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
摘要翻译： 气体发生器组件包括容纳胺基推进剂的推进剂室。 反应室与推进剂室结合。 反应室包括反应室壳体和反应室壳体内的多孔反应基质。 反应基质包括催化剂，并且催化剂被配置为不可燃地将胺基推进剂催化成一种或多种加压气体。 喷射器与推进剂室连通。 喷射器构造成将胺基推进剂输送到多孔反应基质。 排放喷嘴与反应室联接并且构造成加速和排出一个或多个加压气体。 在一个示例中，气体发生器与脉冲涡轮机组件和发电机中的一个或多个耦合以形成微动力单元。
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