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1. 发明授权

US08294072B2 Projectile that includes as needed pressure-relieving wrap-around tail fins 有权
标题翻译：弹丸包括需要的减压缠绕尾翼
公开(公告)号：US08294072B2
公开(公告)日：2012-10-23
申请号：US12789068
申请日：2010-05-27
申请人： Chris E. Geswender , Mark E. Elkanick , Craig O. Shott
发明人： Chris E. Geswender , Mark E. Elkanick , Craig O. Shott
IPC分类号： F42B15/00
CPC分类号： F42B10/16 , F42B10/20 , F42B10/38
摘要： Some embodiments pertain to a projectile that includes a casing and a plurality of fins which are secured to the casing. Each of the fins is movable between a stowed position and a deployed position. The fins are typically in the stowed position during storage and launch, and move to the deployed position as soon as possible after launch. Each fin includes a first foil that has a first set of openings and a second foil that includes a second set of openings. The first sets of openings in the first foils are aligned with the second sets of openings in the second foils when each of the fins is in the stowed position. The first sets of openings in the first foils are not aligned with the second sets of openings in the second foils when each of the fins is in the deployed position.
摘要翻译：一些实施例涉及一种弹射器，其包括壳体和固定到壳体的多个翅片。每个翅片可在收起位置和展开位置之间移动。散热片通常在储存和发射期间处于收起位置，并且在发射后尽快移动到展开位置。每个翅片包括具有第一组开口的第一箔片和包括第二组开口的第二箔片。当每个翅片处于收起位置时，第一箔中的第一组开口与第二箔中的第二组开口对准。当每个翅片处于展开位置时，第一箔中的第一组开口不与第二箔中的第二组开口对齐。

2. 发明申请

US20120199691A1 PROJECTILE THAT INCLUDES AS NEEDED PRESSURE-RELIEVING WRAP-AROUND TAIL FINS 有权
标题翻译：包括需要压力消除缠绕尾灯的项目
公开(公告)号：US20120199691A1
公开(公告)日：2012-08-09
申请号：US12789068
申请日：2010-05-27
申请人： Chris E. Geswender , Mark E. Elkanick , Craig O. Shott
发明人： Chris E. Geswender , Mark E. Elkanick , Craig O. Shott
IPC分类号： F42B15/01
CPC分类号： F42B10/16 , F42B10/20 , F42B10/38
摘要： Some embodiments pertain to a projectile that includes a casing and a plurality of fins which are secured to the casing. Each of the fins is movable between a stowed position and a deployed position. The fins are typically in the stowed position during storage and launch, and move to the deployed position as soon as possible after launch. Each fin includes a first foil that has a first set of openings and a second foil that includes a second set of openings. The first sets of openings in the first foils are aligned with the second sets of openings in the second foils when each of the fins is in the stowed position. The first sets of openings in the first foils are not aligned with the second sets of openings in the second foils when each of the fins is in the deployed position.
摘要翻译：一些实施例涉及一种弹射器，其包括壳体和固定到壳体的多个翅片。每个翅片可在收起位置和展开位置之间移动。散热片通常在储存和发射期间处于收起位置，并且在发射后尽快移动到展开位置。每个翅片包括具有第一组开口的第一箔片和包括第二组开口的第二箔片。当每个翅片处于收起位置时，第一箔中的第一组开口与第二箔中的第二组开口对准。当每个翅片处于展开位置时，第一箔中的第一组开口不与第二箔中的第二组开口对齐。

3. 发明申请

US20100236511A1 Method and Apparatus for improved internal combustion of fuel/oxidizer mixtures by nanostructure injection and electromagnetic pulse ignition 有权
标题翻译：用于通过纳米结构注入和电磁脉冲点火来改善燃料/氧化剂混合物的内部燃烧的方法和装置
公开(公告)号：US20100236511A1
公开(公告)日：2010-09-23
申请号：US12692492
申请日：2010-01-22
申请人： Mark E. Elkanick , Delmar L. Barker
发明人： Mark E. Elkanick , Delmar L. Barker
IPC分类号： F02B43/00 , F02B19/00
CPC分类号： F02B47/00 , F02B5/00 , F02B9/00 , Y02T10/12 , Y02T10/121
摘要： A system and method to inject nanostructures into the fuel/oxidizer mixture, typically lean mixtures, to increase efficiency of internal combustion and/or decrease pollution. An electromagnetic pulse (suitably 1 to 100 GHz) couples energy to the nanostructures to produce a volumetric combustion of the fuel oxidizer mixture. The fuel/oxidizer mixture is substantially transparent to the band of the electromagnetic pulse. The nanostructures couple to the electromagnetic radiation, absorb the energy and heat rapidly producing many local ignitions that in turn produce volume combustion. The nanostructures may be filled or partially filled with energetic material.
摘要翻译：将纳米结构注入燃料/氧化剂混合物（通常为稀混合物）以提高内燃效率和/或减少污染的系统和方法。电磁脉冲（合适地1至100GHz）将能量耦合到纳米结构以产生燃料氧化剂混合物的体积燃烧。燃料/氧化剂混合物对电磁脉冲的波段基本上是透明的。纳米结构耦合到电磁辐射，吸收能量和热量迅速产生许多局部点火，这又产生体积燃烧。纳米结构可以用能量材料填充或部分填充。

4. 发明申请

US20140061364A1 INTEGRATED PROPULSION AND ATTITUDE CONTROL SYSTEM FROM A COMMON PRESSURE VESSEL FOR AN INTERCEPTOR 有权
标题翻译：来自普通压力容器的综合推进和姿态控制系统
公开(公告)号：US20140061364A1
公开(公告)日：2014-03-06
申请号：US13551221
申请日：2012-07-17
申请人： Doron Strassman , Mark E. Elkanick
发明人： Doron Strassman , Mark E. Elkanick
IPC分类号： F42B10/66 , F42B15/01
CPC分类号： F42B10/663 , F42B15/01
摘要： An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.
摘要翻译：拦截器配有集成的推进和姿态控制系统（ACS），其中推进剂燃烧形成用于高压气体的常用压力容器。火箭发动机中的后端口将气体引导通过一个或多个在大致轴向方向排出高速气体的主喷嘴，以推动拦截器。前进端口将气体引导通过一个或多个姿态控制喷嘴，其在大致径向方向上排出高速气体，以控制拦截器的姿态。主喷嘴和稳定翅片固定，对主喷嘴或翅片无伺服控制，影响姿态控制。使用通用的压力容器使得能够紧凑，重量轻且廉价的集成推进和ACS。

5. 发明授权

US08276570B2 Method and apparatus for improved internal combustion of fuel/oxidizer mixtures by nanostructure injection and electromagnetic pulse ignition 有权
标题翻译：通过纳米结构注射和电磁脉冲点火改善燃料/氧化剂混合物内燃的方法和装置
公开(公告)号：US08276570B2
公开(公告)日：2012-10-02
申请号：US12692492
申请日：2010-01-22
申请人： Mark E. Elkanick , Delmar L. Barker
发明人： Mark E. Elkanick , Delmar L. Barker
IPC分类号： F02B51/00
CPC分类号： F02B47/00 , F02B5/00 , F02B9/00 , Y02T10/12 , Y02T10/121
摘要： A system and method to inject nanostructures into the fuel/oxidizer mixture, typically lean mixtures, to increase efficiency of internal combustion and/or decrease pollution. An electromagnetic pulse (suitably 1 to 100 GHz) couples energy to the nanostructures to produce a volumetric combustion of the fuel oxidizer mixture. The fuel/oxidizer mixture is substantially transparent to the band of the electromagnetic pulse. The nanostructures couple to the electromagnetic radiation, absorb the energy and heat rapidly producing many local ignitions that in turn produce volume combustion. The nanostructures may be filled or partially filled with energetic material.
摘要翻译：将纳米结构注入燃料/氧化剂混合物（通常为稀混合物）以提高内燃效率和/或减少污染的系统和方法。电磁脉冲（合适地1至100GHz）将能量耦合到纳米结构以产生燃料氧化剂混合物的体积燃烧。燃料/氧化剂混合物对电磁脉冲的波段基本上是透明的。纳米结构耦合到电磁辐射，吸收能量和热量迅速产生许多局部点火，这又产生体积燃烧。纳米结构可以用能量材料填充或部分填充。

6. 发明授权

US08975565B2 Integrated propulsion and attitude control system from a common pressure vessel for an interceptor 有权
标题翻译：用于拦截器的通用压力容器的综合推进和姿态控制系统
公开(公告)号：US08975565B2
公开(公告)日：2015-03-10
申请号：US13551221
申请日：2012-07-17
申请人： Doron Strassman , Mark E. Elkanick
发明人： Doron Strassman , Mark E. Elkanick
IPC分类号： F42B10/66 , F42B15/01 , F42B10/00 , F42B15/00
CPC分类号： F42B10/663 , F42B15/01
摘要： An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.
摘要翻译：拦截器配有集成的推进和姿态控制系统（ACS），其中推进剂燃烧形成用于高压气体的常用压力容器。火箭发动机中的后端口将气体引导通过一个或多个在大致轴向方向排出高速气体的主喷嘴，以推动拦截器。前进端口将气体引导通过一个或多个姿态控制喷嘴，其在大致径向方向上排出高速气体，以控制拦截器的姿态。主喷嘴和稳定翅片固定，对主喷嘴或翅片无伺服控制，影响姿态控制。使用通用的压力容器使得能够紧凑，重量轻且廉价的集成推进和ACS。

7. 发明授权

US5975460A Nonlinear guidance gain factor for guided missiles 失效
标题翻译：导弹非线性引导增益系数
公开(公告)号：US5975460A
公开(公告)日：1999-11-02
申请号：US967158
申请日：1997-11-10
申请人： Mark E. Elkanick , James A. Bacon
发明人： Mark E. Elkanick , James A. Bacon
IPC分类号： F41G7/22 , F41G7/00
CPC分类号： F41G7/22
摘要： A system (10') for generating a missile guidance gain factor adapted for use with guided missiles. The inventive system includes a guidance control system (52) for obtaining current guidance parameters(55, 57) including ideal navigation gain, closing rate, line of sight rate, missile maneuverability, and missile velocity parameters. Software (56) running on a guidance control processor (54) computes a current guidance gain factor reflective of the current maneuverability of the missile from the guidance parameters (55, 57). In the illustrative embodiment, the system 10' further includes a nonlinear notch circuit (56) that generates an acceleration command (59) from the guidance parameters (55, 57) that varies in response to varying missile maneuverability parameters (57). The guidance control system (10') includes a conventional guidance law computation circuit (54, 55) and electromagnetic sensing equipment (52). An autopilot circuit (58) included in the system (10') provides the missile maneuverability parameters (57). In a specific embodiment, the nonlinear notch circuit (56) is implemented via software running on a guidance processor (54) which performs the following computation for generating the acceleration command (59): A.sub.new =G.sub.nl .times.A, where A.sub.new is the acceleration command (59), A is a pre-existing acceleration command (53), and G.sub.nl is the missile guidance gain factor of the present invention. The guidance gain factor is a function of the ratio of the measured line of sight rate with respect to the ideal line of sight rate maximum, and is tailored to existing missile characteristics and performance requirements.
摘要翻译：一种用于产生适于与导弹一起使用的导弹引导增益因子的系统（10'）。本发明的系统包括用于获得包括理想的导航增益，关闭速率，视线速度，导弹机动性和导弹速度参数的当前引导参数（55,57）的引导控制系统（52）。在引导控制处理器（54）上运行的软件（56）根据引导参数（55,57）计算反映导弹当前可操作性的当前引导增益因子。在说明性实施例中，系统10'还包括非线性陷波电路（56），该非线性陷波电路根据导弹参数（55,57）产生加速度指令（59），所述引导参数响应于变化的导弹机动性参数而变化。引导控制系统（10'）包括常规的引导律计算电路（54,55）和电磁感测设备（52）。包括在系统（10'）中的自动驾驶仪电路（58）提供导弹机动性参数（57）。在特定实施例中，非线性陷波电路（56）通过在引导处理器（54）上运行的软件来实现，所述引导处理器执行以下用于生成加速命令（59）的计算：Anew = GnlxA，其中Anew是加速命令（59 ），A是预先存在的加速指令（53），Gnl是本发明的导弹引导增益因子。引导增益因子是测量视线比相对于理想视线速度最大值的比率的函数，并且是针对现有导弹特性和性能要求而定制的。

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