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公开(公告)号：US08074516B2
公开(公告)日：2011-12-13
申请号：US12394250
申请日：2009-02-27
申请人： Andrew B. Facciano , Brian J. Gowler , James L. Kinzie , Quenten E. Duden , Blake R. Tennison , Adam P. Cherrill
发明人： Andrew B. Facciano , Brian J. Gowler , James L. Kinzie , Quenten E. Duden , Blake R. Tennison , Adam P. Cherrill
IPC分类号： G01D11/24
CPC分类号： F42B10/46
摘要： Methods and apparatus for non-axisymmetric radome according to various aspects of the present invention include a non-symmetric housing for a forward portion of a projectile. Multiple sensors may be positioned in an off-axis configuration within the non-symmetric housing reducing the possibility of one sensor interfering with the operation of another sensor. The non-symmetric housing may also be configured with a strengthening member suitably adapted to provide additional resistance to bending moments caused by external loading along a surface of the non-symmetric housing.
摘要翻译： 根据本发明的各个方面的用于非轴对称雷达罩的方法和装置包括用于射弹前部的非对称壳体。 多个传感器可以位于非对称壳体内的偏轴构造中，减少了一个传感器干扰另一个传感器的操作的可能性。 非对称壳体还可以被配置有加强构件，该加强构件适合于提供对沿着非对称壳体的表面的外部载荷引起的弯曲力矩的附加阻力。
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2.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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公开(公告)号：US06343954B1
公开(公告)日：2002-02-05
申请号：US09593204
申请日：2000-06-14
IPC分类号： H01R1358
CPC分类号： H01R13/533
摘要： The present invention relates to an improved electrical interconnection assembly adaptable for creating electrical connections between spaced-apart sections of a high performance missile assembly. Because the electrical connection must extend outside the missile, a plurality of electrical interconnections are integrally formed within a protective housing that is, itself of aerodynamic configuration. The cables may take the form of flat wires, or printed wire assemblies integral with the housing. Pre-stressed foam is formed in the housing to insulate the electrical interconnections. Wire mesh is preferably mounted in the housing between the interconnections and the outside of the housing to protect the interconnections from Electro-magnetic Interference (EMI).
摘要翻译： 本发明涉及一种改进的电互连组件，其适于在高性能导弹组件的间隔开的部分之间产生电连接。 因为电气连接必须在导弹之外延伸，所以在保护壳体内整体地形成多个电气互连，其本身是空气动力学构型。 电缆可能采取扁平电线或与外壳一体的印刷电线组件的形式。 在壳体中形成预应力泡沫以使电互连绝缘。 电线网优选地安装在外壳之间的互连和外壳之间的壳体中，以保护互连免受电磁干扰（EMI）。
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6.发明授权Mitigation of drift effects in secondary inertial measurements of an isolated detector assembly 有权减轻孤立探测器组件二次惯性测量中的漂移效应公开(公告)号：US08552350B2
公开(公告)日：2013-10-08
申请号：US13350787
申请日：2012-01-15
申请人： Michael S. Bielas , Edward C. Schlatter , Andrew B. Facciano , Philip C. Theriault , James A. Ebel , Robert J. LaPorte
发明人： Michael S. Bielas , Edward C. Schlatter , Andrew B. Facciano , Philip C. Theriault , James A. Ebel , Robert J. LaPorte
CPC分类号： G01C21/16 , G01C25/005
摘要： The 6-axis position and attitude of an imaging vehicle's detector assembly is measured by mounting the detector assembly on a compliant isolator and separating the main 6-axis IMU on the vehicle from a secondary IMU comprising at least inertial rate sensors for pitch and yaw on the detector assembly. The compliant isolator couples low-frequency rigid body motion of the vehicle below a resonant frequency to the isolated detector assembly while isolating the detector assembly from high-frequency attitude noise above the resonant frequency. A computer processes measurements of the 6-axis rigid body motion and the angular rate of change in yaw and pitch of the isolated detector assembly to mitigate the drift and noise error effects of the secondary inertial rate sensors and estimate the 6-axis position and attitude of the detector assembly.
摘要翻译： 成像车辆检测器组件的6轴位置和姿态通过将检测器组件安装在顺应性隔离器上并将车辆上的主6轴IMU与第二IMU分离，其中至少包括用于俯仰和偏航的惯性速率传感器 检测器组件。 兼容隔离器将低于谐振频率的车辆的低频刚体运动耦合到隔离的检测器组件，同时将检测器组件与高于谐振频率的高频姿态噪声隔离。 计算机处理六轴刚体运动的测量和隔离检测器组件的偏航和俯仰角变化速率，以减轻二次惯性速率传感器的漂移和噪声误差影响，并估计6轴位置和姿态 的检测器组件。
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公开(公告)号：US07819048B2
公开(公告)日：2010-10-26
申请号：US12274660
申请日：2008-11-20
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：US07767944B2
公开(公告)日：2010-08-03
申请号：US11715034
申请日：2007-03-07
摘要： A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the 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： 振动控制的外壳。 新颖的壳体包括壳体结构和用于接收控制信号并根据其电子调谐结构的结构响应的机构。 在说明性实施例中，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：US07681834B2
公开(公告)日：2010-03-23
申请号：US11395794
申请日：2006-03-31
IPC分类号： B64C1/00
CPC分类号： F42B10/46 , H01Q1/281 , H01Q1/42 , H01Q21/065
摘要： A missile includes a radome-seeker airframe assembly that has a single-piece composite material forebody. The forebody is made of a high-temperature composite material that can withstand heat with little or no ablation. The forebody has a front part with an ogive shape and an aft part that has a cylindrical shape. The front part acts as a radome for a seeker located within the forebody. Patch antennas are attached to an inside surface of the cylindrical aft part. The aft part acts as a radome for the patch antennas, allowing signals to be sent and received by the patch antennas without a need for cutouts. A single seal may be used to seal the guidance system and seeker within the forebody, allowing the equipment to be hermetically sealed within the forebody.
摘要翻译： 导弹包括具有单件复合材料前身的天线探头机身机身组件。 前体由高温复合材料制成，能够耐受很少或无消融的热量。 前身具有具有圆柱形状的前部，其具有凹凸形状和后部。 前部作为位于前体内的寻求者的天线罩。 贴片天线连接到圆筒形后部的内表面。 尾部作为贴片天线的天线罩，允许由贴片天线发送和接收信号，而不需要切口。 可以使用单个密封件来密封前体内的引导系统和探测器，从而允许设备在前体内气密密封。
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公开(公告)号：US20080217465A1
公开(公告)日：2008-09-11
申请号：US11715034
申请日：2007-03-07
摘要： A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the 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： 振动控制的外壳。 新颖的壳体包括壳体结构和用于接收控制信号并根据其电子调谐结构的结构响应的机构。 在说明性实施例中，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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