-
公开(公告)号：US11694668B2
公开(公告)日：2023-07-04
申请号：US16884637
申请日：2020-05-27
Applicant: Raytheon Company
Inventor： Curtis B. Carlsten , Frederick B. Koehler , Jason E. Gaudette , Peter M. Willey
CPC classification number: G10K11/006 , H04B11/00 , B63B22/003
Abstract: 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.
-
公开(公告)号：US11530669B2
公开(公告)日：2022-12-20
申请号：US17017741
申请日：2020-09-11
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Mark J. Meisner , Jeff L. Vollin
Abstract: A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.
-
公开(公告)号：US10184762B2
公开(公告)日：2019-01-22
申请号：US14956169
申请日：2015-12-01
Applicant: RAYTHEON COMPANY
Inventor： Matthew H. Summers , Frederick B. Koehler , Jeremy C. Danforth , James K. Villarreal
Abstract: A device is provided. The device includes at least one SMM component fabricated from an SMM. The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body of the device allowing the device to change shape in an advantageous way. A method implemented by a device is also provided. The method includes changing a shape of an SMM component of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying the SMM component from a device body of the device allowing the device to change shape in an advantageous way.
-
公开(公告)号：US20170283095A1
公开(公告)日：2017-10-05
申请号：US15091008
申请日：2016-04-05
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
CPC classification number: B64G1/403 , B33Y70/00 , B33Y80/00 , B64G1/10 , B64G1/26 , F02K9/80 , F02K99/00 , F05D2210/20 , F05D2230/31
Abstract: A satellite has thrusters that are integral parts of its frame. 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.
-
公开(公告)号：US09773627B2
公开(公告)日：2017-09-26
申请号：US14255562
申请日：2014-04-17
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Ward D. Lyman , William D. Werries
CPC classification number: H01H37/323 , F03G7/065 , H01H37/46 , Y10T29/49105
Abstract: A shape memory circuit breaker includes a shape memory substrate having first and second opposed substrate ends. The shape memory substrate is configured to transition from a strained conductive configuration to a fractured non-conductive configuration. An isolation housing is coupled with the shape memory substrate. The isolation housing includes first and second anchors coupled near the first and second substrate ends. A brace extends between the first and second anchors, and the brace statically positions the first and second anchors and the respective first and second substrate ends. The shape memory substrate is configured to transition from the strained conductive configuration to the fractured non-conductive configuration at or above a specified temperature range corresponding to a specified overload current range or voltage range, and the first substrate end fractures from the second substrate end at or above the specified temperature range resulting in an open circuit.
-
Patent Agency Ranking
公开(公告)号：US20150119479A1
公开(公告)日：2015-04-30
申请号：US14066647
申请日：2013-10-29
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Terry M. Sanderson
CPC classification number: B29C61/0625 , B29C61/003 , B29C64/106 , B29C64/112 , B29C70/882 , B29K2105/0061 , B29K2105/04 , B29K2995/0005 , B33Y10/00 , C08J9/00 , C08J2300/00
Abstract: 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.
Abstract translation: 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。
-
公开(公告)号：US20150108268A1
公开(公告)日：2015-04-23
申请号：US14057876
申请日：2013-10-18
Applicant: Raytheon Company
Inventor： Ward D. Lyman , Frederick B. Koehler , Terry M. Sanderson
IPC: F42B10/64
Abstract: A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces 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 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 of the body.
Abstract translation: 用于导弹的控制系统包括可以排列在导弹体的表面上的多个控制表面，以及连接到控制表面的控制器，以选择性地将控制表面移动到空气动力学存放位置，其中控制表面符合 身体的表面和从空气动力学收起位置移除的展开的控制位置，其中控制表面从身体的表面延伸以与身体上的气流相互作用。 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身体纵轴的滚动的能力。
-
公开(公告)号：US20140306473A1
公开(公告)日：2014-10-16
申请号：US13863634
申请日：2013-04-16
Applicant: RAYTHEON COMPANY
Inventor： Frederick B. Koehler , Ward D. Lyman , Terry M. Sanderson
CPC classification number: F03G7/065 , B25J9/1085 , B25J15/12 , Y10S901/31
Abstract: A robotic finger includes a shape-memory alloy and a shape-memory polymer connected to and adjacent to the shape-memory alloy. Heating the shape-memory polymer causes it to soften, heating the shape-memory alloy causes the alloy to bend in the direction of the shape-memory polymer to press the shape-memory polymer against an object to be grasped, and cooling the shape-memory polymer causes it to stiffen and to retain its shape. An opposing member is positioned to cooperate with the finger to grasp an object positioned between the finger and the opposing member. A selectively controllable heat source is capable of applying heat to the finger.
Abstract translation: 机器人手指包括形状记忆合金和连接到形状记忆合金的形状记忆合成物。 加热形状记忆聚合物使其软化，加热形状记忆合金导致合金在形状记忆聚合物的方向上弯曲以将形状记忆聚合物压靠待被抓握的物体， 记忆聚合物使其变硬并保持其形状。 相对的构件定位成与手指配合以抓住位于手指和相对构件之间的物体。 选择性控制的热源能够对手指施加热量。
-
公开(公告)号：US20220082066A1
公开(公告)日：2022-03-17
申请号：US17017741
申请日：2020-09-11
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Mark J. Meisner , Jeff L. Vollin
Abstract: A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.
-
公开(公告)号：US11047370B1
公开(公告)日：2021-06-29
申请号：US16884755
申请日：2020-05-27
Applicant: Raytheon Company
Inventor： Frederick B. Koehler , Curtis B. Carlsten , Ward D. Lyman , Jason E. Gaudette
Abstract: 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.
-
-
-
-
-
-
-
-
-
Search Results
41
records
(took 0.022 seconds)
