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1. 发明申请

WO2016053445A1 METHODS AND APPARATUS FOR UNDERWATER ELECTRICAL NEAR-FIELD SIGNAL SYSTEM 审中-公开
标题翻译：水下电场信号系统的方法与装置
公开(公告)号：WO2016053445A1
公开(公告)日：2016-04-07
申请号：PCT/US2015/040677
申请日：2015-07-16
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , MCCREERY, Thomas, P. , RINKER, Robert , ROGERS, Darrell, R. , ROSENWALD, Ross, D. , SANDERSON, Terry, M. , SAR, David, R. , FASSE, Ernest, D.
IPC分类号： H04B13/02 , G01S1/72 , G01S13/02 , G01S13/04
CPC分类号： H04B5/0031 , G01N25/00 , G01N27/06 , G01S1/72 , G06F1/163 , G06F1/1698 , H04B13/02 , H04B2001/3894 , H04W4/80
摘要： Methods and apparatus for a near-field signal system to generate signals underwater for navigation and/or communication. In one embodiment, a system includes a signal processing module coupled to a first antenna to transmit near-field signals underwater and a second antenna to receive near-field signals underwater transmitted by the first antenna. In one embodiment, a wetsuit includes an integrated near-field signal system.
摘要翻译：近场信号系统在水下生成用于导航和/或通信的信号的方法和装置。在一个实施例中，系统包括耦合到第一天线以在水下发射近场信号的信号处理模块和用于接收由第一天线发射的近场信号的第二天线。在一个实施例中，潜水衣包括集成的近场信号系统。

2. 发明申请

WO2021242436A2 SONOBUOY VOLUMETRIC ARRAY DEPLOYMENT MODULE 审中-公开
公开(公告)号：WO2021242436A2
公开(公告)日：2021-12-02
申请号：PCT/US2021/027595
申请日：2021-04-16
申请人： RAYTHEON COMPANY
发明人： CARLSTEN, Curtis, B. , KOEHLER, Frederick, B. , GAUDETTE, Jason, E. , WILLEY, Peter, M.
IPC分类号： G10K11/00 , F03G7/06 , G01V1/20 , G01V1/38 , G01S7/521 , B63B22/00
摘要： A deployment module according to the present application enables both compact stowage of a sensor array and expansion of the sensor array into a three-dimensional volumetric array shape that enables improved directionality of the sensors during operation. The deployment module includes a support shell that is configured to retain a cable of the sensor array separately from sensors of the sensor array and an expandable deployment body formed of a superelastic shape memory alloy that uses superelasticity and stored energy for deployment of the sensor array. During deployment, the deployment body is removed from the support shell and the sensors are subsequently pulled out of the support shell. The deployment body then expands and holds the cable to retain the three-dimensional volumetric shape of the deployed array.

3. 发明申请

WO2021242310A2 SELF ERECTING SUB-SURFACE ARRAY DEPLOYMENT MECHANISM WITH SHAPE MEMORY ALLOY 审中-公开
公开(公告)号：WO2021242310A2
公开(公告)日：2021-12-02
申请号：PCT/US2020/065222
申请日：2020-12-16
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , CARLSTEN, Curtis, B. , LYMAN, Ward, D. , GAUDETTE, Jason, E.
IPC分类号： G01V1/20 , G10K11/00 , B63B22/00 , H01Q1/08 , F03G7/06 , G01V1/38 , B63B22/003 , F03G7/06145 , F03G7/0636 , F03G7/064 , F03G7/065 , G01V1/201 , G01V1/3843 , G10K11/008
摘要： A deployment body for a sensor array includes at least one superelastic spring formed of a shape memory alloy (SMA) material that enables activation of the deployment body. The SMA spring is configured to expand from a stowed position in which the SMA spring is wound around a central hub of the deployment body to a deployed position in which the SMA spring is extended in a radially outward direction relative to the central hub. A stiffness of the SMA spring enables the SMA spring to hold cables of the sensor array and maintain a deployed shape of the sensor array, which may be a volumetric array. Using the SMA material is advantageous in that the material is tuned to maintain superelasticity based on at least one of an intended operating temperature and a desired expansion ratio of stowed to deployed diameter of the deployment body.

4. 发明申请

WO2017069816A1 SPACECRAFT WITH SHAPE MEMORY POLYMER DEPLOYMENT MECHANISM 审中-公开
标题翻译：具有形状记忆聚合物展开机制的航天器
公开(公告)号：WO2017069816A1
公开(公告)日：2017-04-27
申请号：PCT/US2016/040419
申请日：2016-06-30
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , LYMAN, Ward, D. , SUMMERS, Matt, H. , DANFORTH, Jeremy, C.
IPC分类号： B64G1/22 , F03G7/06
CPC分类号： B64G1/222 , B64G1/10 , F03G7/065
摘要： A spacecraft (10), such as a satellite, uses a shape memory polymer actuator (18) to deploy one or more deployable parts (14). The shape memory polymer actuator may be formed integrally with a deployable part and/or with a fuselage (12) or other structure of the spacecraft, with the shape memory polymer actuator being for example a relatively thin portion of the shape memory polymer material of the integral structure. The shape memory actuator allows deployment of the deployable part(s) upon heating of the shape memory polymer material of the actuator, such as after the satellite has been launched into space. The heating may be caused by a heat source that is part of the spacecraft itself, or may be merely the result of exposing the spacecraft to solar heating after launch. The deployable part of the spacecraft may include any of a wide variety of parts that are used after launch.
摘要翻译：诸如卫星之类的航天器（10）使用形状记忆聚合物致动器（18）来展开一个或多个可展开部件（14）。形状记忆聚合物致动器可以与可展开部件和/或与航天器的机身（12）或其他结构一体形成，其中形状记忆聚合物致动器例如是形状记忆聚合物材料的相对较薄的部分整体结构。形状记忆致动器允许在加热致动器的形状记忆聚合物材料时，例如在卫星已经发射到太空之后，展开可展开部件。加热可能由作为航天器本身一部分的热源引起，或者可能仅仅是航天器在发射后暴露于太阳能加热的结果。航天器的可展开部分可能包括发射后使用的各种部件中的任何一种。

5. 发明申请

WO2015065527A1 SHAPE-MEMORY POLYMER WITH INTEGRAL RESISTIVE HEATING ELEMENT 审中-公开
标题翻译：具有整体电阻加热元件的形状记忆聚合物
公开(公告)号：WO2015065527A1
公开(公告)日：2015-05-07
申请号：PCT/US2014/040232
申请日：2014-05-30
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , SANDERSON, Terry, M.
IPC分类号： B29C70/88 , B29C67/00 , B29C61/06
CPC分类号： B29C61/0625 , B29C61/003 , B29C64/106 , B29C64/112 , B29C67/0059 , B29C70/882 , B29K2105/0061 , B29K2105/04 , B29K2995/0005 , B33Y10/00 , C08J9/00 , C08J2300/00
摘要： A method of making a reconfigurable three-dimensional shape includes the following steps: (i) moving multiple print heads in three dimensions relative to a printing surface, where the print heads include a conductor print head and a polymer print head; (ii) depositing a conductive material from the conductor print head; and (iii) depositing a shape-memory polymer from the polymer print head. The depositing steps form a volumetric shape of a shape-memory polymer, capable of changing shape, with a conductive material capable of acting as a heating element integrally formed in the volumetric shape. The method can further include the steps of heating the shape-memory polymer above a transition temperature, changing the shape of the volumetric shape following the heating step, and then allowing the shape-memory polymer to cool below the transition temperature to fix the new volumetric shape.
摘要翻译：制造可重构三维形状的方法包括以下步骤：（i）相对于打印表面三维地移动多个打印头，其中打印头包括导体打印头和聚合物打印头; （ii）从导体印刷头沉积导电材料; 和（iii）从聚合物打印头沉积形状记忆聚合物。沉积步骤形成能够改变形状的形状记忆聚合物的体积形状，其中导电材料能够用作体积形状一体形成的加热元件。该方法还可以包括以下步骤：将形状记忆聚合物加热到转变温度之上，改变加热步骤之后的体积形状的形状，然后使形状记忆聚合物冷却到低于转变温度以固定新体积形状。

6. 发明申请

WO2014062232A1 HEAT-ACTUATED RELEASE MECHANISM 审中-公开
标题翻译：热启动机构
公开(公告)号：WO2014062232A1
公开(公告)日：2014-04-24
申请号：PCT/US2013/034908
申请日：2013-04-02
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , LYMAN, Ward, D. , BEARD, Douglas, M. , LEE, Anthony, O.
IPC分类号： F03G7/06 , F16B1/00
CPC分类号： F03G7/065 , F16B1/0014
摘要： A release mechanism passively releases a mechanically coupling as a result of a temperature rise. The release mechanism includes a breakable element, such as a shape memory alloy (SMA) element, that is configured to break when the element is heated to a predetermined temperature. The breakage of the breakable element releases a mechanical coupling, such as a coupling holding a lid onto a container. The release mechanism may be part of a handle or other device to close the container. The release mechanism may have a mechanical load on it prior to release, a load that in part passes through the breakable element. Most of the load may pass through one or more other members of the release mechanism, providing the force for separation after the release mechanism is triggered. The release mechanism may be used to provide a passive way of releasing a mechanical coupling in response to heating.
摘要翻译：释放机构由于温度上升而被动地释放机械耦合。释放机构包括诸如形状记忆合金（SMA）元件的可破坏元件，其被配置为当元件被加热到预定温度时断裂。可破坏元件的断裂释放机械联接，例如将盖子保持在容器上的联接器。释放机构可以是用于关闭容器的手柄或其他装置的一部分。释放机构在释放之前可能具有机械负载，其部分地穿过可破坏元件的负载。大部分负荷可以通过释放机构的一个或多个其他构件，在释放机构被触发之后提供用于分离的力。释放机构可以用于提供响应于加热释放机械联接的被动方式。

7. 发明申请

WO2022115124A1 MULTI-PULSE SOLID ROCKET MOTOR AND IGNITION METHOD 审中-公开
公开(公告)号：WO2022115124A1
公开(公告)日：2022-06-02
申请号：PCT/US2021/027596
申请日：2021-04-16
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , PINELLO-BENAVIDES, Jacob, A. , COPELAND, Curtis, S. , MCNEIL, Isaiah, M. , KADLEC, Paul , BRUNACINI, Lauren, E. , LANGHENRY, Mark, T.
IPC分类号： F02K9/95 , F02K9/28 , F02K9/94
摘要： A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.

8. 发明申请

WO2018038868A1 GAS GENERATION SYSTEM AND METHOD OF IGNITION OF ELECTRICALLY OPERATED PROPELLANT 审中-公开
标题翻译：燃气发电系统和电动推进器点火方法
公开(公告)号：WO2018038868A1
公开(公告)日：2018-03-01
申请号：PCT/US2017/044654
申请日：2017-07-31
申请人： RAYTHEON COMPANY
发明人： VILLARREAL, James, K. , VILLARREAL, Thomas, W. , KOEHLER, Frederick, B. , LANGHENRY, Mark, T. , SUMMERS, Matt, H.
IPC分类号： F02K9/95
CPC分类号： F02K9/26 , F02K9/94 , F02K9/95
摘要： An actuator produces a displacement that maintains positive contact between an electrically operated propellant and a pair of electrodes to ignite and sustain combustion of an ignition surface. The electrodes are suitably configured such that current lines between the electrodes follow equipotential surfaces through the propellant. The displacement drives a contour of the ignition surface to substantially match an equipotential surface corresponding to a maximum and uniform current density J at a minimum gap between the electrodes to ignite and combust the entire ignition surface. The flat, angled or curved contact areas of the electrodes are suitably symmetric about a plane.
摘要翻译：致动器产生位移，该位移保持电动推进剂与一对电极之间的正接触以点燃并维持点火表面的燃烧。电极适当地配置为使得电极之间的电流线通过推进剂跟随等势表面。该位移驱动点火表面的轮廓以基本匹配等于对应于在电极之间的最小间隙处的最大均匀电流密度J的等电位表面以点燃并燃烧整个点火表面。电极的平坦，成角度或弯曲的接触区域关于平面适当对称。

9. 发明申请

WO2017176310A1 SATELLITE WITH INTEGRAL THRUSTERS 审中-公开
标题翻译：带有整体推力器的卫星
公开(公告)号：WO2017176310A1
公开(公告)日：2017-10-12
申请号：PCT/US2016/056382
申请日：2016-10-11
申请人： RAYTHEON COMPANY
发明人： KOEHLER, Frederick, B. , DANFORTH, Jeremy, C. , LYMAN, Ward, D. , LANGHENRY, Mark, T. , SUMMERS, Matt, H. , PONTIUS, Paul, E. , PAPE, Brian, M. , STALLINGS, Jared, D. , VILLARREAL, James, K. , VILLARREAL, Thomas
IPC分类号： B64G1/10 , B64G1/40
摘要： A satellite (10) has thrusters (18) that are integral parts of its frame (12). The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
摘要翻译：卫星（10）具有作为其框架（12）的组成部分的推进器（18）。框架限定推进器所在的空腔。推进器可以包括电驱动推进剂和电极以激活电驱动推进剂中的燃烧。框架可以加成制造，并且推进剂和/或电极也可以附加地制造，其中框架和推进剂和/或电极也可以在单个工艺中制造。另外，推进器可具有喷嘴部分，燃烧气体通过喷嘴部分离开推进器。推进器可以位于框架的角落和/或沿着框架的边缘，并且可以用于完成卫星的各种操纵中的任何一种。卫星可以是小卫星，例如CubeSat卫星，例如具有约1升的体积和不大于约1.33kg的质量。

10. 发明申请

WO2015057274A1 AERO CONTROL SURFACES AND METHOD OF USE 审中-公开
公开(公告)号：WO2015057274A1
公开(公告)日：2015-04-23
申请号：PCT/US2014/040208
申请日：2014-05-30
申请人： RAYTHEON COMPANY
发明人： LYMAN, Ward, D. , KOEHLER, Frederick, B. , SANDERSON, Terry, M.
IPC分类号： F42B10/62
CPC分类号： F42B10/64 , B64C9/36 , F42B10/62
摘要： A control system (10) for a missile (12) includes a plurality of control surfaces (14) that can be arrayed across a surface (16) of the missile body (18), and a controller (30) connected to the control surfaces (14) to selectively move the control surfaces (14) between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow (20) over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape- memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis (22) of the body (18).
摘要翻译：用于导弹（12）的控制系统（10）包括可以跨过导弹体（18）的表面（16）排列的多个控制表面（14）和连接到控制表面的控制器（30）（14），用于选择性地将所述控制表面（14）移动到所述控制表面符合所述主体表面的空气动力学收起位置和从所述空气动力学收起位置移除的展开控制位置，其中所述控制表面从所述控制表面身体与身体上的气流（20）相互作用。控制表面由包括形状记忆合金的材料制成。加热控制表面使得形状记忆合金将控制表面从空气动力学存放位置移动到展开的控制位置。通过选择性地延伸和缩回控制表面，控制系统提供控制导弹的行进方向或减少围绕主体（18）的纵向轴线（22）的滚动的能力。

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