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公开(公告)号：US10927987B2
公开(公告)日：2021-02-23
申请号：US14861043
申请日：2015-09-22
申请人： Raytheon Company
摘要： Ducting and/or duct couplings can be formed from shape memory polymer material, with the material for example being additively manufactured. The use of shape memory polymer material for one or more of the duct portions may allow for easier installation of the ducting, for example allowing the ducting to be warped and/or bent to fit into or through places that are hard to reach or hard to maneuver through, with the ducting then heated to cause it to return to a predetermined memory shape. The coupling of duct portions together may be accomplished by the duct portions including a shape memory polymer material, with for example ends of the duct portions fitted together, and then heated to use a shape memory property of the material to effect coupling. Heating of the shape memory polymer material also softens the material, allowing it to move to a previously set shape.
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公开(公告)号：US10518908B2
公开(公告)日：2019-12-31
申请号：US14921545
申请日：2015-10-23
申请人： Raytheon Company
摘要： A spacecraft, such as a satellite, uses a shape memory polymer actuator to deploy one or more deployable parts. The shape memory polymer actuator may be formed integrally with a deployable part and/or with a fuselage 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.
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公开(公告)号：US10220966B2
公开(公告)日：2019-03-05
申请号：US15091008
申请日：2016-04-05
申请人： Raytheon Company
发明人： 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
摘要： 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.
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公开(公告)号：US20160305754A1
公开(公告)日：2016-10-20
申请号：US14687693
申请日：2015-04-15
申请人： Raytheon Company
IPC分类号： F42B39/14
摘要： A release mechanism includes a frame with an interior. The release mechanism also includes a prestrained element coupled to the interior of the frame. The prestrained element creates a seal with the frame. The prestrained element is notched in one or more regions. The prestrained element is configured to fracture when heated to a predetermined temperature allowing the interior to open. The fracture is based on the notched regions of the prestrained element such that separation initiates within the notched regions. The remaining regions of the prestrained element unfractured. The shape memory alloy element can include one or more of a nickel-titanium alloy, a titanium-nickel alloy, a copper-zinc-aluminum alloy, a copper aluminum nickel alloy, and a nickel titanium hafnium alloy. Heating of the shape memory alloy element causes a stress in the shape memory alloy that causes fracturing of the prestrained alloy when sufficient heating has been achieved.
摘要翻译： 释放机构包括具有内部的框架。 释放机构还包括耦合到框架内部的预应力元件。 预制元件与框架形成密封。 预制元素在一个或多个区域中被切口。 预应力元件被配置为当加热到允许内部打开的预定温度时断裂。 断裂基于预应力元件的缺口区域，使得在缺口区域内开始分离。 预应力元素的剩余区域不合格。 形状记忆合金元素可以包括镍 - 钛合金，钛 - 镍合金，铜 - 锌 - 铝合金，铜铝镍合金和镍铪合金中的一种或多种。 形状记忆合金元件的加热导致形状记忆合金中的应力，当达到足够的加热时，会导致预应变合金的断裂。
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公开(公告)号：US20170283095A1
公开(公告)日：2017-10-05
申请号：US15091008
申请日：2016-04-05
申请人： Raytheon Company
发明人： 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分类号： B64G1/403 , B33Y70/00 , B33Y80/00 , B64G1/10 , B64G1/26 , F02K9/80 , F02K99/00 , F05D2210/20 , F05D2230/31
摘要： 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.
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公开(公告)号：US09773627B2
公开(公告)日：2017-09-26
申请号：US14255562
申请日：2014-04-17
申请人： Raytheon Company
CPC分类号： H01H37/323 , F03G7/065 , H01H37/46 , Y10T29/49105
摘要： 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.
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公开(公告)号：US20150108268A1
公开(公告)日：2015-04-23
申请号：US14057876
申请日：2013-10-18
申请人： Raytheon Company
IPC分类号： F42B10/64
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US20140306473A1
公开(公告)日：2014-10-16
申请号：US13863634
申请日：2013-04-16
申请人： RAYTHEON COMPANY
CPC分类号： F03G7/065 , B25J9/1085 , B25J15/12 , Y10S901/31
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US11174048B2
公开(公告)日：2021-11-16
申请号：US16266520
申请日：2019-02-04
申请人： Raytheon Company
发明人： 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
IPC分类号： B64G1/40 , F02K9/24 , F02K9/95 , B33Y80/00 , B64G1/26 , F02K9/80 , B64G1/10 , F02K99/00 , F02K9/94 , B33Y70/00
摘要： 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.
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公开(公告)号：US10948274B1
公开(公告)日：2021-03-16
申请号：US16585931
申请日：2019-09-27
申请人： Raytheon Company
摘要： A heat-activated triggering device, such as for a missile or munition, includes a bi-metal trigger element, with a breakable pin of a first metal surrounded by a sleeve made of a second metal that is different than the first metal. The sleeve may be made of a shape memory alloy, such as a single-crystal shape memory alloy, that is pre-compresses around part of the pin. The sleeve may be configured to put a tension force on the pin as the sleeve passes a predetermined temperature, for instance a temperature at which the shape memory feature of the sleeve is activated. The pin may have a weakened portion, such as a notched portion, at which the pin breaks. The breaking of the pin may be used to drive a firing pin into a primer, to initiate a detonation and/or combustion reaction.
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