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1. 发明授权

US08402895B2 Vortice amplified diffuser for buoyancy dissipater and method for selectable diffusion 有权
标题翻译：用于浮力消散器的涡流放大扩散器和可选择扩散的方法
公开(公告)号：US08402895B2
公开(公告)日：2013-03-26
申请号：US12770879
申请日：2010-04-30
申请人： James H. Dupont , Jeffrey H. Koessler
发明人： James H. Dupont , Jeffrey H. Koessler
IPC分类号： F42B12/02 , F42B15/22 , F42B19/10
CPC分类号： B63G13/00 , F15D1/001 , F41H11/00 , Y10T137/0324 , Y10T137/2098
摘要： Embodiments of a vortice-amplified diffuser section for use in a buoyancy dissipater are generally described herein. The vortice-amplified diffuser section may include a plurality of diffusion ports to diffuse an expanding gas, a reduction sleeve to adjust an amount of diffusion flow, and vortex generators within at least some of the diffusion ports to generate vortices. The reduction sleeve may be configurable to block off some of the diffusion ports. The vortex generators may generate vortices of gas bubbles in the water to reduce the water's buoyancy and to inhibit movement or disrupt the operations of an errant vessel. The reduction sleeve may be used to control the size, shape, and intensity of the expanding gas bubble or bubble plume as well as to control the lethality level of the buoyancy reduction.
摘要翻译：用于浮力耗散器的涡流扩大扩散器部分的实施例一般在此描述。涡流放大扩散器部分可以包括多个扩散扩散气体的扩散口，减少套管以调节扩散流量，以及在至少一些扩散端口内的涡流发生器以产生涡流。还原套筒可以被配置为阻挡一些扩散端口。涡流发生器可能会在水中产生气泡的漩涡，以减少水的浮力并抑制运动或扰乱错误的船只的作业。还原套筒可用于控制膨胀气泡或气泡羽流的尺寸，形状和强度，以及控制浮力降低的致死水平。

2. 发明授权

US07642492B2 Single-axis fin deployment system 有权
标题翻译：单轴翅片部署系统
公开(公告)号：US07642492B2
公开(公告)日：2010-01-05
申请号：US11043870
申请日：2005-01-26
申请人： John C. Parine , Jeffrey H. Koessler , Purnachandra R. Gogineni , Juan A. Perez , Martin A. Kebschull
发明人： John C. Parine , Jeffrey H. Koessler , Purnachandra R. Gogineni , Juan A. Perez , Martin A. Kebschull
IPC分类号： F42B10/14
CPC分类号： F42B10/14
摘要： A missile has fins that rotate about a single axis to deploy from a stowed position to a deployed position. A foil longitudinal axis of each fin is angled relative to a shaft of the fin, such that a single-axis rotation of the shaft moves the foil from the stowed position to a deployed position. A coil spring may provide both torsion and compression forces to rotate the fin into the deployed position and lock it into place. Torsion rotates the shaft until it reaches a seat on a bushing that is around the shaft. Then compression forces from the spring engage a keyed protrusion on the shaft with a corresponding keyway in the bushing, locking the shaft in place. There may be an additional lock once the fin is deployed, such as a spring-loaded pin in the missile body that engages a depression in the shaft.
摘要翻译：导弹具有围绕单个轴线旋转的翅片，以从收起位置部署到展开位置。每个翅片的箔纵向轴线相对于翅片的轴成一角度，使得轴的单轴旋转将箔从收起位置移动到展开位置。螺旋弹簧可以提供扭转和压缩力以将翅片旋转到展开位置并将其锁定到位。扭转轴旋转直到其到达位于轴周围的衬套上的座椅。然后，来自弹簧的压缩力将轴上的带键突起与衬套中的相应键槽接合，将轴锁定在适当位置。一旦翅片被部署就可能有一个附加的锁，例如导弹体中的弹簧加载的销接合轴中的凹陷。

3. 发明申请

US20140048654A1 AIRCRAFT DEVICE DEPLOYMENT SYSTEM WITH SPRING-DRIVEN MECHANICAL LINKAGE 有权
标题翻译：具有弹簧机械连接的飞机设备部署系统
公开(公告)号：US20140048654A1
公开(公告)日：2014-02-20
申请号：US13585245
申请日：2012-08-14
申请人： Zachary Williamson , Jeffrey H. Koessler , Paul A. Merems , Timothy A. Murphy , Dennis E. Rossmeier
发明人： Zachary Williamson , Jeffrey H. Koessler , Paul A. Merems , Timothy A. Murphy , Dennis E. Rossmeier
IPC分类号： B64D1/04 , B64D1/12
CPC分类号： B64D1/04 , B64D1/12
摘要： A deployment system includes a spring-driven linkage for deploying one or more kicker feet, to push a device to be deployed away from the deployment system. The kicker feet may include fore and aft kicker feet that push the deployed device to obtain a desire pitch in the launch, an example being a minimal or substantially zero pitch. The release of the kicker feet may be controlled by a pair of actuator, such as electrical solenoid actuators, both of which must be actuated to deploy the device. An electrical connection may allow positional float to account for tolerances in the positioning of the device relative to the deployment system.
摘要翻译：部署系统包括用于部署一个或多个踢脚的弹簧驱动的联动装置，以推动部署远离部署系统的设备。踢脚可以包括前部和后部踢脚，其推动所部署的装置以在发射中获得期望的间距，示例是最小或基本为零的间距。踢球脚的释放可以由一对致动器（例如电动螺线管致动器）来控制，这两个致动器必须被致动以部署该装置。电气连接可以允许位置浮动来考虑设备相对于展开系统的定位的公差。

4. 发明授权

US08869671B2 Aircraft device deployment system with spring-driven mechanical linkage 有权
标题翻译：具有弹簧机械联动的飞机装置部署系统
公开(公告)号：US08869671B2
公开(公告)日：2014-10-28
申请号：US13585245
申请日：2012-08-14
申请人： Zachary Williamson , Jeffrey H. Koessler , Paul A. Merems , Timothy A. Murphy , Dennis E. Rossmeier
发明人： Zachary Williamson , Jeffrey H. Koessler , Paul A. Merems , Timothy A. Murphy , Dennis E. Rossmeier
IPC分类号： B64D1/04
CPC分类号： B64D1/04 , B64D1/12
摘要： A deployment system includes a spring-driven linkage for deploying one or more kicker feet, to push a device to be deployed away from the deployment system. The kicker feet may include fore and aft kicker feet that push the deployed device to obtain a desire pitch in the launch, an example being a minimal or substantially zero pitch. The release of the kicker feet may be controlled by a pair of actuator, such as electrical solenoid actuators, both of which must be actuated to deploy the device. An electrical connection may allow positional float to account for tolerances in the positioning of the device relative to the deployment system.
摘要翻译：部署系统包括用于部署一个或多个踢脚的弹簧驱动的联动装置，以推动部署远离部署系统的设备。踢脚可以包括前部和后部踢脚，其推动所部署的装置以在发射中获得期望的间距，示例是最小或基本为零的间距。踢球脚的释放可以由一对致动器（例如电动螺线管致动器）来控制，这两个致动器必须被致动以部署该装置。电气连接可以允许位置浮动来考虑设备相对于展开系统的定位的公差。

5. 发明申请

US20120103424A1 VORTICE AMPLIFIED DIFFUSER FOR BUOYANCY DISSIPATER AND METHOD FOR SELECTABLE DIFFUSION 有权
标题翻译：用于浮选的扩散扩散器和选择扩散的方法
公开(公告)号：US20120103424A1
公开(公告)日：2012-05-03
申请号：US12770879
申请日：2010-04-30
申请人： James H. Dupont , Jeffrey H. Koessler
发明人： James H. Dupont , Jeffrey H. Koessler
IPC分类号： F15C1/16
CPC分类号： B63G13/00 , F15D1/001 , F41H11/00 , Y10T137/0324 , Y10T137/2098
摘要： Embodiments of a vortice-amplified diffuser section for use in a buoyancy dissipater are generally described herein. The vortice-amplified diffuser section may include a plurality of diffusion ports to diffuse an expanding gas, a reduction sleeve to adjust an amount of diffusion flow, and vortex generators within at least some of the diffusion ports to generate vortices. The reduction sleeve may be configurable to block off some of the diffusion ports. The vortex generators may generate vortices of gas bubbles in the water to reduce the water's buoyancy and to inhibit movement or disrupt the operations of an errant vessel. The reduction sleeve may be used to control the size, shape, and intensity of the expanding gas bubble or bubble plume as well as to control the lethality level of the buoyancy reduction.
摘要翻译：用于浮力耗散器的涡流扩大扩散器部分的实施例一般在此描述。涡流放大扩散器部分可以包括多个扩散扩散气体的扩散口，减少套管以调节扩散流量，以及在至少一些扩散端口内的涡流发生器以产生涡流。还原套筒可以被配置为阻挡一些扩散端口。涡流发生器可能会在水中产生气泡的漩涡，以减少水的浮力并抑制运动或扰乱错误的船只的作业。还原套筒可用于控制膨胀气泡或气泡羽流的尺寸，形状和强度，以及控制浮力降低的致死水平。

6. 发明授权

US07338010B2 Air-launchable aircraft and method of use 有权
标题翻译：空中发射飞机及使用方法
公开(公告)号：US07338010B2
公开(公告)日：2008-03-04
申请号：US10951041
申请日：2004-09-23
申请人： David A. Corder , Jeffrey H. Koessler , George R. Webb
发明人： David A. Corder , Jeffrey H. Koessler , George R. Webb
IPC分类号： B64C3/56
CPC分类号： B64C3/56 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/082 , B64C2201/102 , B64C2201/123 , B64C2201/127 , B64C2201/141 , B64C2201/145 , B64C2201/165 , B64C2201/201
摘要： An air-launched aircraft includes deployable wings, elevons, and vertical fins that deploy from a fuselage during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The aircraft may be employed at a low cost for any of a wide variety of functions, such as surveillance, or as a decoy. The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.
摘要翻译：一架空中飞机包括在飞行期间从机身部署的可部署的机翼，电梯和垂直翼片。飞机可以包括用于操作电梯的控制系统，通信系统和用于为系统供电的电池。此外，飞机可以包括与机身中的接口相配合的有效载荷模块。有效载荷模块可以包括各种有效载荷中的任何一种，包括相机，传感器和/或雷达发射器。该飞机可能是动力或无动力的，并且可能非常小，例如小于10kg（22磅）的量级。飞机可以以低成本从事各种功能，例如监视或作为诱饵。飞机的可展开的表面可以被配置成以预定的顺序部署，允许飞机在以翻滚模式发射之后自动进入受控飞行。

7. 发明授权

US08181906B2 Method and apparatus for ram deceleration in a launch system 有权
标题翻译：发射系统中压头减速的方法和装置
公开(公告)号：US08181906B2
公开(公告)日：2012-05-22
申请号：US12417418
申请日：2009-04-02
申请人： Jeffrey H. Koessler , Brian L. Cochran , Mark A. DeBake , Steven J. Elder
发明人： Jeffrey H. Koessler , Brian L. Cochran , Mark A. DeBake , Steven J. Elder
IPC分类号： B64F1/04
CPC分类号： B64F1/04 , F41F1/00 , F41F3/0413 , F41F3/08
摘要： One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior.
摘要翻译：一个实施例包括限定从底部延伸到出口的细长的线性内部的发射器。该实施例包括可滑动地设置在发射容器中的柱塞，密封到容器的柱塞。该实施例还包括一个或多个楔形件，其沿着沿着出口开口的内部联接到发射容器，每个楔形尺寸被设计成沿着从底部向出口开口延伸的出口矢量逐渐变窄内部横截面。在该实施例中，容器将容纳靠近底部的电荷，电荷沿着出口矢量推动冲头，其中一个或多个楔的尺寸被设计成在内部停止。

8. 发明申请

US20100252676A1 METHOD AND APPARATUS FOR RAM DECELERATION IN A LAUNCH SYSTEM 有权
标题翻译：推进系统中RAM衰减的方法和装置
公开(公告)号：US20100252676A1
公开(公告)日：2010-10-07
申请号：US12417418
申请日：2009-04-02
申请人： Jeffrey H. Koessler , Brian L. Cochran , Mark A. DeBake , Steven J. Elder
发明人： Jeffrey H. Koessler , Brian L. Cochran , Mark A. DeBake , Steven J. Elder
IPC分类号： B64F1/04 , F41A21/00
CPC分类号： B64F1/04 , F41F1/00 , F41F3/0413 , F41F3/08
摘要： One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior.
摘要翻译：一个实施例包括限定从底部延伸到出口的细长的线性内部的发射器。该实施例包括可滑动地设置在发射容器中的柱塞，密封到容器的柱塞。该实施例还包括一个或多个楔形件，其沿着沿着出口开口的内部联接到发射容器，每个楔形尺寸被设计成沿着从底部向出口开口延伸的出口矢量逐渐变窄内部横截面。在该实施例中，容器将容纳靠近底部的电荷，电荷沿着出口矢量推动冲头，其中一个或多个楔的尺寸被设计成在内部停止。

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