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11.发明申请MISSILE AIRFRAME AND STRUCTURE COMPRISING PIEZOELECTRIC FIBERS AND METHOD FOR ACTIVE STRUCTURAL RESPONSE CONTROL 有权包含压电纤维的空气弹性体结构和主动结构响应控制方法公开(公告)号：US20100264251A1
公开(公告)日：2010-10-21
申请号：US12823683
申请日：2010-06-25
IPC分类号： F42B15/01 , F42B15/00 , H01L41/053 , H01L41/09
摘要： Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.
摘要翻译： 导弹，机身和包括压电纤维的结构的实施例和用于主动结构响应控制的方法一般在本文中描述。 在一些实施例中，壳体结构包括复合材料，其包含多个压电纤维，其适于响应于结构中的变形而产生电信号，并且响应于施加到其上的电信号使结构变形。 控制电路从光纤接收感测到的信号，并产生施加到光纤的激励信号，以增加光纤在预定频率下的刚度或顺应性。 在说明性实施例中，控制信号适于提供低频刚度和强度性能，同时衰减高频振动以保护容纳在结构内的电子元件。
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公开(公告)号：US20090194632A1
公开(公告)日：2009-08-06
申请号：US12024532
申请日：2008-02-01
CPC分类号： F42B15/01
摘要： Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.
摘要翻译： 具有外部系统的导弹的方法和装置与机身和流体传输系统一起操作。 机身包括限定基本封闭的内部腔室的内表面。 流体传输系统选择性地将内部室连接到外部系统，例如以向外部系统提供加压或冷却剂。
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公开(公告)号：US20090071320A1
公开(公告)日：2009-03-19
申请号：US12274660
申请日：2008-11-20
IPC分类号： F42D3/00
CPC分类号： F42B15/38 , Y10T428/15
摘要： A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.
摘要翻译： 可分离结构包括由反应性烟火材料分离或切断的复合材料。 根据一个实施例，该结构包括一对复合层压结构部分，每个复合层压结构部分包括多层复合材料。 这些部分各自延伸到重叠区域中，两个结构部分的复合层可以交替放置在该重叠区域内，彼此重叠。 反应性材料也被放置在该重叠区域内，例如在复合材料层对之间的层中。 可以点燃反应性材料以引起烟火材料的破坏，并且重叠区域中的复合材料层的基质或树脂材料层。 这导致结构沿着重叠区域内的分离线断开或分离。 可能发生分离而不需要切断复合材料的纤维。
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公开(公告)号：US07800032B1
公开(公告)日：2010-09-21
申请号：US11606763
申请日：2006-11-30
IPC分类号： F42B15/01
CPC分类号： F42B10/143 , F42B10/64
摘要： Provided is a detachable aerodynamic missile stabilizing system for a missile flying at low flight speeds. The system includes a housing adapted to couple to couple to the missile. Extending outward from the housing is at least one grid fin. Specifically the grid fin extends from the housing such that it is transverse to a longitudinal axis of the housing and the missile. The grid fin provides a plurality of apertures. The apertures are parallel to the longitudinal axis of the housing and the missile. A coupler is adapted to detachably couple the housing to the missile. A method of use is also provided.
摘要翻译： 提供了一种用于以低飞行速度飞行的导弹的可拆卸气动导弹稳定系统。 该系统包括适于耦合到导弹的壳体的壳体。 从房屋向外延伸至少有一个格栅。 具体地，网格翅片从壳体延伸，使得其横向于壳体和导弹的纵向轴线。 网格翅片提供多个孔。 这些孔平行于壳体和导弹的纵向轴线。 耦合器适于将壳体可拆卸地耦合到导弹。 还提供了一种使用方法。
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公开(公告)号：US20100219285A1
公开(公告)日：2010-09-02
申请号：US11606763
申请日：2006-11-30
IPC分类号： F42B10/14
CPC分类号： F42B10/143 , F42B10/64
摘要： Provided is a detachable aerodynamic missile stabilizing system for a missile flying at low flight speeds. The system includes a housing adapted to couple to couple to the missile. Extending outward from the housing is at least one grid fin. Specifically the grid fin extends from the housing such that it is transverse to a longitudinal axis of the housing and the missile. The grid fin provides a plurality of apertures. The apertures are parallel to the longitudinal axis of the housing and the missile. A coupler is adapted to detachably couple the housing to the missile. A method of use is also provided.
摘要翻译： 提供了一种用于以低飞行速度飞行的导弹的可拆卸气动导弹稳定系统。 该系统包括适于耦合到导弹的壳体的壳体。 从房屋向外延伸至少有一个格栅。 具体地，网格翅片从壳体延伸，使得其横向于壳体和导弹的纵向轴线。 网格翅片提供多个孔。 这些孔平行于壳体和导弹的纵向轴线。 耦合器适于将壳体可拆卸地耦合到导弹。 还提供了一种使用方法。
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公开(公告)号：US4569918A
公开(公告)日：1986-02-11
申请号：US345002
申请日：1982-02-02
CPC分类号： G01N27/06 , G01N31/12 , Y10T436/186 , Y10T436/25125 , Y10T436/255
摘要： A sulfur dioxide-containing analysis stream, such as formed by the oxidative pyrolysis of a sulfur-containing liquid, is passed through a trapping medium comprising metal or metal oxide, preferably nickel oxide, wherein the sulfur dioxide is retained while the remainder of the gas flows through. Thereafter, the flow of analysis gas is discontinued and the trap zone is heated to release the sulfur dioxide, which is passed in an inert carrier gas stream through a sulfur dioxide detector such as a conductivity cell. Halides in the analysis stream are removed prior to trapping by being dissolved in an aqueous liquid in a scrubbing chamber. Such chamber is regenerated by vaporizing the halide-containing aqueous solution and venting it. Also, a system of the foregoing type including two traps and a single detector whereby two samples are alternately analyzed and trapped to reduce the overall analysis time.
摘要翻译： 通过含硫液体的氧化热解形成的含二氧化硫的分析流通过包含金属或金属氧化物（优选氧化镍）的捕集介质，其中保留二氧化硫，而剩余的气体 流过。 此后，中断分析气体的流动并加热捕集区以释放二氧化硫，二氧化硫通过惰性载气流通过诸如电导池的二氧化硫检测器。 在分析流中的卤化物通过溶解在洗涤室中的水性液体中而在捕获之前被除去。 通过使含卤化物的水溶液蒸发并使其排气来再生这样的室。 另外，上述类型的系统包括两个陷阱和单个检测器，由此交替地分析和捕获两个样本以减少总体分析时间。
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公开(公告)号：US4227887A
公开(公告)日：1980-10-14
申请号：US937652
申请日：1978-08-28
CPC分类号： G01N31/12 , G01N33/1826
摘要： A three phase process for determining total organic halides in water. The first phase is a sorptive process including passing a liquid through a packed bed of sorptive material thereby removing quantitatively, purgeable and non-purgeable, organic halides and thereafter passing an inorganic halide displacement wash solution through the bed to displace inorganic halides. The second and third phases are a combination combustion and titration whereby organic bromides and other organic halides entering the combustion phase are quantitatively titrated coulometrically. The second and third phases include in a first heating zone heating a sample, such as the sorptive material following the first phase, in the presence of a mild oxidant to a temperature sufficient to vaporize water; in a second heating zone heating any remaining sample from the first heating zone and gases therefrom in the presence of an oxidant to a temperature sufficient to complete combustion of the sample and gases; and concurrently titrating coulometrically the gases from the second heating zone.
摘要翻译： 用于测定水中总有机卤化物的三相方法。 第一阶段是吸附过程，包括使液体通过吸附材料的填充床，从而除去定量，可清洗和不可吹扫的有机卤化物，然后使无机卤化物置换的洗涤溶液通过床以置换无机卤化物。 第二和第三相是组合燃烧和滴定，其中进入燃烧阶段的有机溴化物和其它有机卤化物被库仑法定量滴定。 第二和第三相包括在温和氧化剂存在下将样品（例如第一相后的吸附材料）加热至足以蒸发水的温度的第一加热区; 在第二加热区中，在氧化剂存在下将来自第一加热区的任何剩余样品和其中的气体加热到足以完全燃烧样品和气体的温度; 并同时对来自第二加热区的气体进行库仑滴定。
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18.发明授权Missile airframe and structure comprising piezoelectric fibers and method for active structural response control 有权导弹机体和包括压电纤维的结构和主动结构响应控制方法公开(公告)号：US08049148B2
公开(公告)日：2011-11-01
申请号：US12823683
申请日：2010-06-25
摘要： Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure to provide low frequency stiffness and strength performance while attenuating high frequency vibrations.
摘要翻译： 导弹，机身和包括压电纤维的结构的实施例和用于主动结构响应控制的方法一般在本文中描述。 在一些实施例中，壳体结构包括复合材料，其包含多个压电纤维，其适于响应于结构中的变形而产生电信号，并且使结构变形以提供低频刚度和强度性能，同时衰减高频振动。
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公开(公告)号：US07509903B2
公开(公告)日：2009-03-31
申请号：US11190297
申请日：2005-07-27
IPC分类号： B64G1/64
CPC分类号： F42B15/38 , Y10T428/15
摘要： A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.
摘要翻译： 可分离结构包括由反应性烟火材料分离或切断的复合材料。 根据一个实施例，该结构包括一对复合层压结构部分，每个复合层压结构部分包括多层复合材料。 这些部分各自延伸到重叠区域中，两个结构部分的复合层可以交替放置在该重叠区域内，彼此重叠。 反应性材料也被放置在该重叠区域内，例如在复合材料层对之间的层中。 可以点燃反应性材料以引起烟火材料的破坏，并且重叠区域中的复合材料层的基质或树脂材料层。 这导致结构沿着重叠区域内的分离线断开或分离。 可能发生分离而不需要切断复合材料的纤维。
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公开(公告)号：US20080290191A1
公开(公告)日：2008-11-27
申请号：US11986954
申请日：2007-11-27
CPC分类号： F02K9/97 , B29C70/28 , B29K2079/08 , B29K2307/00 , B29K2309/08 , B29K2995/0015 , B29L2031/777 , F05D2300/2102 , F05D2300/211 , F05D2300/224 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/614
摘要： An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.
摘要翻译： 整体复合火箭发动机喷嘴。 新型喷嘴包括第一增强材料层，第二增强材料层和围绕第一和第二增强材料的共同基体材料，使得增强材料和基体材料形成单个整体复合结构。 在说明性实施例中，第一增强材料包括用于提供结构支撑的石墨纤维，并且第二增强材料包括用于在第一层的第一侧上提供热绝缘的玻璃或石英纤维。 喷嘴还可以包括用于在第一层的第二侧上提供热绝缘的第三增强材料的第三层。 在优选实施例中，第一层被成形为形成一体的圆顶和喷嘴结构。
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