公开(公告)号：WO2022265787A1

公开(公告)日：2022-12-22

申请号：PCT/US2022/029632

申请日：2022-05-17

Applicant: RAYTHEON COMPANY

Inventor： GALD, Matthew ,  FORGACS, Stephen J. ,  RELLER, Dan L. ,  CORNELIUS, Dean J.

IPC: F16C11/04 ,  F42B15/34 ,  B64C7/00

Abstract: A hinge includes internal on-axis stopping mechanisms that cause the hinge to shear and break at an on-axis weakened region of the hinge when rotation of the hinge reaches a predetermined angle with a specified torsional load. The on-axis configuration is compact, has minimal impact on the outer mold line (OML) of the object to which it is mounted both pre and post detachment and allows for accurate tailoring of the torsional load that will detach the hinge.

公开(公告)号：WO2021112934A1

公开(公告)日：2021-06-10

申请号：PCT/US2020/048226

申请日：2020-08-27

Applicant: STOKE SPACE TECHNOLOGIES, INC.

Inventor： LAPSA, Andrew ,  FELDMAN, Thomas

IPC: F42B15/34

Abstract: An actively-cooled heat shield system includes a heat shield, a tank, a pump, a heat exchanger, and a turbine. The heat shield defines a windward side of a vehicle. The tank stores a coolant. The pump receives the coolant from the tank and outputs a pressurized coolant. The heat exchanger is integrally connected with the heat shield. The heat exchanger receives the pressurized coolant from the pump, transfers heat from the heat shield to the pressurized coolant to generate a heated fluid, and outputs the heated fluid. The turbine includes an inlet, a shaft, and an outlet. The inlet receives the heated fluid output from the heat exchanger. The shaft is coupled to the pump and includes turbine blades. The shaft rotates and powers the pump when the heated fluid received from the heat exchanger acts on the turbine blades. The outlet outputs the heated fluid.

公开(公告)号：WO2008045032A3

公开(公告)日：2008-10-02

申请号：PCT/US2006038848

申请日：2006-10-04

Applicant: HARDING DAVID K

Inventor： HARDING DAVID K

IPC: F42B12/02 ,  F42B15/34 ,  G06F15/18

CPC classification number: F42B12/60

Abstract: A multi-hydrogen bomb warhead (5) preferably having a plurality of bombs (3) located behind a door (2) of a nose cone (1) of the warhead (5). A plurality of decoys (4) may be used in conjunction with the bombs (3). The bombs (3) and decoys (4) are spring-ejected from the nose cone (1) through the doors (2). However, the bomb (3) may be transported via missile or via alternative transportation systems, such as the back of a pick-up truck (6).

Abstract translation: 多氢弹弹头（5）优选地具有位于弹头（5）的鼻锥（1）的门（2）后面的多个炸弹（3）。 多个诱饵（4）可以与炸弹（3）结合使用。 炸弹（3）和诱饵（4）通过门（2）从鼻锥（1）弹簧弹出。 然而，炸弹（3）可以通过导弹或通过替代运输系统（例如拾取卡车（6））的后部运输。

公开(公告)号：WO02055954A3

公开(公告)日：2003-01-23

申请号：PCT/US0141895

申请日：2001-08-27

Applicant: HRL LAB LLC ,  RAYTHEON CO ,  KIRBY KEVIN W ,  VAJO JOHN J ,  JANKIEWICZ ANTHONY ,  HEROLD JOHN ,  VALENZUELA CARLOS ,  JUDNICH FRANK ,  ANDERSON WAYNE

Inventor： KIRBY KEVIN W ,  VAJO JOHN J ,  JANKIEWICZ ANTHONY ,  HEROLD JOHN ,  VALENZUELA CARLOS ,  JUDNICH FRANK ,  ANDERSON WAYNE

IPC: B05D3/02 ,  B05D5/00 ,  B05D7/00 ,  F42B15/34 ,  B64G1/58 ,  C08J7/04

CPC classification number: B05D7/58 ,  B05D3/0254 ,  B05D5/00 ,  F42B15/34 ,  Y10T428/216 ,  Y10T428/31663 ,  Y10T428/31667

Abstract: A method for improving the thermal barrier properties of silicone resin/glass fibercomposites. Composites comprising a layer of polysiloxane (silicone resin) matrixwith a glass or quartz fiber reinforcement embedded in such matrix and an organic polymeric layer were subjected to multi-cycle heat treatment, preferably with quartzlamps. The polysiloxane layer was pre-coated with graphite dispersion in order to ensure acceptable optical receptivity of the polysiloxane layer. As a result, the silicone resin was converted into a thick porous layer of silicone dioxide, the latterhaving the improved thermal barrier properties.

Abstract translation: 一种提高硅树脂/玻璃纤维复合材料的热阻性能的方法。 将包含嵌入该基质中的玻璃或石英纤维增强剂的聚硅氧烷（硅树脂）基质层和有机聚合物层的复合材料进行多循环热处理，优选采用石英灯。 为了确保聚硅氧烷层的可接受的光学接受性，将聚硅氧烷层预先涂覆有石墨分散体。 结果，将有机硅树脂转变成二氧化硅的厚多孔层，后者具有改善的热阻特性。

公开(公告)号：WO2021194718A1

公开(公告)日：2021-09-30

申请号：PCT/US2021/020885

申请日：2021-03-04

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： GOLDBERG, Mark Russell ,  HUNSBERGER, Harold Kregg ,  MILLS, Helen J.

IPC: H01Q1/28 ,  H01Q11/10 ,  H01Q21/20 ,  H01R24/40 ,  F42B15/34 ,  H01Q1/02 ,  B64G1/58 ,  H01Q1/281 ,  H01Q11/105 ,  H01Q13/085 ,  H01Q21/064 ,  H01Q21/205

Abstract: An aerial vehicle includes a body and an antenna assembly mounted to the body. The antenna assembly includes a fairing component comprising a hollow body, a conductive coating formed on at least an inner surface of the fairing component, a plurality of antenna elements formed in the conductive coating, each antenna element including a first slot line defining a first transmission line and a second slot line defining a second transmission line, an insulator sleeve disposed within the fairing component, wherein an outer surface of the insulator sleeve at least substantially matches an inner surface of the fairing component, and a plurality of cable assemblies operably coupled to the plurality of antenna elements, wherein each cable assembly is coupled to a respective antenna element.

公开(公告)号：WO2014039122A3

公开(公告)日：2014-07-03

申请号：PCT/US2013043425

申请日：2013-05-30

Applicant: RAYTHEON CO

Inventor： SUNNE WAYNE L ,  PENTLAND CHRISTOPHER E ,  MARR CHRISTOPHER D

IPC: F42B10/46 ,  F42B15/34

CPC classification number: F42B15/01 ,  F42B10/46 ,  F42B15/34 ,  Y10T403/479 ,  Y10T428/131

Abstract: A vehicle (10), such as a missile, is disclosed. The vehicle (10)includes an optically transparent dome (20,120,220,320), a vehicle body (30,130,230,330), and a brazed joint (40,140) directly coupling the dome (20,120,220,320) to the vehicle body (30,130,230,330). The dome (20,120,220,320) is formed of a Nanocomposite Optical Ceramic (NCOC) material comprising two or more different types of nanograins dispersed in one another. Each nanograin type has a coefficient of thermal expansion (CTE), and an aggregate CTE of the NCOC material is based on the CTE of each nanograin type.

Abstract translation: 披露诸如导弹的车辆（10）。 车辆（10）包括光学透明的圆顶（20,120,220,320），车身（30,130,230,330）和将圆顶（20,120,220,320）直接联接到车身（30,130,230,330）的钎焊接头（40,140）。 圆顶（20,120,220,320）由纳米复合光学陶瓷（NCOC）材料形成，其包括彼此分散的两种或更多种不同类型的纳米晶粒。 每种纳米晶型均具有热膨胀系数（CTE），而NCOC材料的总CTE基于每种纳米晶型的CTE。

公开(公告)号：WO2013150241A1

公开(公告)日：2013-10-10

申请号：PCT/FR2013/050732

申请日：2013-04-03

Applicant: HERAKLES

Inventor： SOULIGNAC, Thierry ,  BOMBLED, Florine ,  ISSAC, François. M. ,  SIERRA, Guillaume ,  DESVERGNES, Philippe, P. ,  CAILLER, Aurélien

IPC: B64D45/02 ,  B64G1/58 ,  F42B15/34

CPC classification number: H02G13/80 ,  B64D45/02 ,  B64G1/58 ,  F42B3/18 ,  F42C19/04

Abstract: L'invention concerne un dispositif de protection contre la foudre (200) destiné à être posé sur une structure (100) à protéger et comprenant : un revêtement de surface comprenant au moins une couche de peinture conductrice (202), une pluralité d'éléments électriquement conducteurs (204) disposés de manière espacée sur la structure, lesdits éléments étant en contact avec la couche de peinture conductrice (202), un revêtement de protection (205) disposé sur le revêtement de surface et comprenant un matériau thermiquement isolant et électriquement conducteur, le revêtement de protection (205) recouvrant partiellement les éléments électriquement conducteurs (204).

Abstract translation: 本发明涉及一种提供防雷击的装置（200），并且旨在放置在待保护的结构（100）上，并且包括：表面涂层，其包括至少一层导电涂料（202），多个 导电元件（204）以间隔开的方式定位在结构上，所述元件与导电涂料（202）的涂层接触，施加到表面涂层上的保护涂层（205）包括隔热和 导电材料，保护涂层（205）部分地覆盖导电元件（204）。

公开(公告)号：WO2010053607A2

公开(公告)日：2010-05-14

申请号：PCT/US2009/052176

申请日：2009-07-30

Applicant: RAYTHEON COMPANY ,  GESWENDER, Chris E. ,  BENNETT, Stephen E. ,  ZAMORA, Matthew A. ,  SANCHEZ, Cesar

Inventor： GESWENDER, Chris E. ,  BENNETT, Stephen E. ,  ZAMORA, Matthew A. ,  SANCHEZ, Cesar

IPC: F42B10/46 ,  F42B15/34 ,  F42C11/00 ,  F42C19/02

CPC classification number: F42C19/02 ,  F42B10/46

Abstract: A smart fuze system (12) includes a radome (60) used to hold a replaceable smart fuze module (24) in place. An internally-threaded collar (66) screws onto threads on the main body (42) of the smart fuze system. Pressure from the radome presses the smart fuze module against electrical connections (48) in the main body. The smart fuze module may thereby be held in place without potting material, allowing different types of fuzes to be swapped into place. The different types of fuzes may include a type that communicates height of burst (HOB) information a type that communicates telemetry, and a type that communicates both HOB and telemetry information.

Abstract translation: 智能引信系统（12）包括用于将替换的智能引信模块（24）保持在适当位置的天线罩（60）。 螺纹套环（66）拧入智能引信系统的主体（42）上的螺纹上。 天线罩的压力将智能引信模块按压到主体中的电气连接（48）。 因此，智能引信模块可以在没有灌封材料的情况下保持就位，从而允许将不同类型的支架交换到位。 不同类型的fuzes可以包括传达突发（HOB）信息的高度的类型，通信遥测的类型，以及传达HOB和遥测信息的类型。

公开(公告)号：WO01017326A1

公开(公告)日：2001-03-08

申请号：PCT/US2000/023388

申请日：2000-08-25

IPC: F42B15/08 ,  F42B15/34 ,  H05K7/14 ,  H05K7/20

CPC classification number: H05K7/20445 ,  F42B15/08 ,  F42B15/34 ,  H05K7/1434

Abstract: A heat conducting device for providing a thermal path between a circuit board and a missile airframe includes a thermal plane that is adapted to receive a circuit board and a collar that encompasses at least a portion of the thermal plane. The collar has a first position that disengages the heat conducting device from at least a portion of the airframe and a second position that engages the heat conducting device with at least a portion of the airframe to provide a thermal path between the circuit board and the airframe.

Abstract translation: 用于在电路板和导弹机体之间提供热路径的导热装置包括适于接收电路板的热平面和包围热平面的至少一部分的套环。 套环具有使导热装置与机身的至少一部分脱离的第一位置，以及与导热装置与机体的至少一部分接合以在电路板和机身之间提供热路径的第二位置 。

公开(公告)号：WO99010237A2

公开(公告)日：1999-03-04

申请号：PCT/US1998/017072

申请日：1998-08-17

IPC: F42B15/34 ,  B64G1/36 ,  B64G1/00

CPC classification number: F42B10/46 ,  B64G1/36

Abstract: A dome assembly (50) adapted for use with a missile (32) having a longitudinal axis (42) parallel to a thrust vector thereof. The inventive dome (50) includes a sapphire crystal (30) having a crystallographic structure that includes positive n-planes (12), positive r-planes (14) and a c-plane (16). A surface around a missile sensor provides a place for mounting the crystal (30, 50) such that one of said positive r-planes faces leeward with respect to wind flow (36) that impinges on said missile (32) during missile flight. The projection of one of the positive r-plane normals onto the wind flow vector (36) points aft. By design at nominal conditions, an r-plane (14) is approximately bisected by a plane formed by the normal of the c-plane (16) and a wind flow vector (36). In the illustrative embodiment, the dome assembly (50) includes an x-ray device for locating the r-planes within the sensor dome (50). A turntable (not shown) orients the sensor dome (50) so that a first r-plane (14) faces leeward of impinging air flow (36). An r-plane normal (38) of a second r-plane forms an angle of approximately 60 degrees with respect to impinging airflow (36). The turntable includes a motor (not shown) for strategically orienting the lattice planes (12, 14, 16) of the dome (50) so as to maximize the strength of the dome (50) with respect to applied stresses.

Abstract translation: 适于与具有平行于其推力向量的纵向轴线（42）的导弹（32）一起使用的圆顶组件（50）。 本发明的圆顶（50）包括具有包括正n面（12），正r面（14）和c平面（16）的结晶结构的蓝宝石晶体（30）。 导弹传感器周围的表面提供了用于安装晶体（30,50）的位置，使得所述正r面中的一个相对于在导弹飞行期间撞击所述导弹（32）的风流（36）面向背风。 正面r平面法线中的一个投影到风向量（36）上。 通过在标称条件下的设计，r平面（14）由由c平面（16）的法线和风向量（36）形成的平面近似地平分。 在说明性实施例中，圆顶组件（50）包括用于将传感器圆顶（50）内的r平面定位的X射线装置。 转台（未示出）定向传感器圆顶（50），使得第一r平面（14）面向冲击气流（36）的背风。 第二r平面的r平面法线（38）相对于撞击气流形成大约60度的角度（36）。 转盘包括用于对拱顶（50）的格子平面（12,14,16）进行策略性定向以使拱顶（50）相对于所施加的应力的强度最大化的马达（未示出）。