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1. 发明申请

US20180037342A1 MULTI-FUNCTIONAL COMPOSITE STRUCTURE FOR EXTREME ENVIRONMENTS 审中-公开
公开(公告)号：US20180037342A1
公开(公告)日：2018-02-08
申请号：US15226219
申请日：2016-08-02
申请人： The Boeing Company
发明人： Jian Dong , Naveed Moayyed Hussain
IPC分类号： B64G1/54 , E04C2/36 , B64G1/56 , E04C2/284 , E04B1/92 , E04C2/34 , E04C2/52
CPC分类号： B64G1/54 , B32B1/08 , B32B3/08 , B32B3/12 , B32B5/02 , B32B7/12 , B32B9/007 , B32B15/02 , B32B27/065 , B32B27/12 , B32B27/32 , B32B2250/05 , B32B2250/40 , B32B2262/0253 , B32B2262/0269 , B32B2262/105 , B32B2262/106 , B32B2262/14 , B32B2266/0278 , B32B2307/202 , B32B2307/212 , B32B2307/304 , B32B2307/558 , B32B2307/56 , B32B2307/71 , B32B2307/7246 , B32B2571/02 , B32B2605/00 , B32B2605/18 , B64C1/064 , B64C1/12 , B64C1/406 , B64C2001/0072 , B64D2221/00 , B64G1/56 , E04B1/92 , E04B2001/925 , E04C2/284 , E04C2/3405 , E04C2/365 , E04C2/521 , E04C2/526 , E04C2002/345
摘要： A multi-functional composite structure has a modular design that can be altered depending on an extreme environment in which the structure will be exposed such as hazardous radiation, micro-meteoroid and orbital debris impacts, extreme temperature changes, etc. The material combinations employed in the multi-functional composite structure provide a supporting structure with low weight and maximum protection from radiation, debris impacts and temperature variations.

2. 发明授权

US09527608B1 ELF and VLF antenna and related methods 有权
标题翻译： ELF和VLF天线及相关方法
公开(公告)号：US09527608B1
公开(公告)日：2016-12-27
申请号：US14954031
申请日：2015-11-30
申请人： The United States of America as represented by the Secretary of the Air Force
发明人： Vladimir Sotnikov , Tony Kim
IPC分类号： B64G1/54 , H01Q1/28 , H01Q7/00 , H01Q21/29
CPC分类号： B64G1/54 , H01Q1/288 , H01Q7/00 , H01Q21/29
摘要： A method of reducing densities of harmful charged radiation belt particles is includes providing a space-based antenna having a first antenna portion and second antenna portion. The first antenna portion and the second antenna portion are oriented such that their loop planes are perpendicular with respect to the magnetic field of the Earth. The first antenna portion and the second antenna portion are energized with a first frequency and a second frequency, respectively, wherein the first frequency and the second frequency satisfy the relationship that the ratio of the first frequency to the second frequency is equal to the ratio of the second radius to the first radius. The trajectory of energetic particles in the radiation belt, such that the trajectories of energetic particles are shifted into a loss cone.
摘要翻译：降低有害带电辐射带粒子的密度的方法包括提供具有第一天线部分和第二天线部分的基于天线的天线。第一天线部分和第二天线部分被定向成使得它们的环面相对于地球的磁场垂直。第一天线部分和第二天线部分分别以第一频率和第二频率被激励，其中第一频率和第二频率满足第一频率与第二频率之比等于第二个半径到第一个半径。辐射带中能量粒子的轨迹，使得能量粒子的轨迹移入损耗锥体。

3. 发明授权

US08809824B1 Cryogenically cooled radiation shield device and associated method 有权
标题翻译：低温辐射屏蔽装置及相关方法
公开(公告)号：US08809824B1
公开(公告)日：2014-08-19
申请号：US12966350
申请日：2010-12-13
申请人： Gary A. Kinstler
发明人： Gary A. Kinstler
IPC分类号： G21F5/00
CPC分类号： B64G1/58 , B64G1/50 , B64G1/54 , G21F1/00 , G21F3/00
摘要： A cryogenically cooled radiation shield device and method are provided to shield an area, such as the capsule of a space vehicle, from radiation. A cryogenically cooled radiation shield device may include at least one first coil comprised of a superconducting material extending about the area to be shielded. The cryogenically cooled radiation shield device also includes a first inner conduit extending about the area to be shielded from radiation. The at least one first coil is disposed within the first inner conduit. The cryogenically cooled radiation shield device also includes a first outer conduit extending about the area to be shielded from radiation. The first inner conduit is disposed within the first outer conduit. The cryogenically cooled radiation shield device also includes a first cryogen liquid disposed within the first inner conduit and a second cryogen liquid, different than the first cryogen liquid, disposed within the first outer conduit.
摘要翻译：提供了一种低温冷却的辐射屏蔽装置和方法来屏蔽诸如太空车辆的胶囊的区域不受辐射。低温冷却的辐射屏蔽装置可以包括至少一个由围绕待屏蔽区域延伸的超导材料构成的第一线圈。低温冷却的辐射屏蔽装置还包括围绕要被屏蔽的区域延伸的第一内导管。所述至少一个第一线圈设置在所述第一内导管内。低温冷却的辐射屏蔽装置还包括围绕要被屏蔽的区域延伸的第一外导管。第一内导管设置在第一外导管内。低温冷却的辐射屏蔽装置还包括布置在第一内部管道内的第一冷冻剂液体和设置在第一外部管道内的与第一冷冻剂液体不同的第二冷冻剂液体。

4. 发明授权

US08770521B2 Device for protecting an optical instrument of a satellite 有权
标题翻译：用于保护卫星光学仪器的装置
公开(公告)号：US08770521B2
公开(公告)日：2014-07-08
申请号：US13451419
申请日：2012-04-19
申请人： Yannick Baudasse , Stéphane Vezain
发明人： Yannick Baudasse , Stéphane Vezain
IPC分类号： B64G1/54 , B64G1/00 , B64G1/22 , B64G1/66
CPC分类号： B64G1/222 , B64G1/54 , B64G1/66
摘要： A device for protecting an optical instrument of a satellite comprises a body on which the optical instrument is mounted, said protection device having a folded-down position and a deployed position, and further comprising a plurality of rigid panels in the deployed position, the device forming a tube, the section of which is a polygon, arranged so as to protect the optical instrument, the longitudinal axis of the tube being substantially parallel with the focal axis of the optical instrument, the faces of the tube of polygonal section being formed by panels, in the folded-down position, said panels being held against the body of the satellite.
摘要翻译：用于保护卫星的光学仪器的装置包括其上安装有光学仪器的主体，所述保护装置具有折叠位置和展开位置，并且还包括处于展开位置的多个刚性面板，所述装置形成管，其部分是多边形，布置成保护光学仪器，管的纵向轴线基本上与光学仪器的焦点轴线平行，多边形部分的管的表面由在折叠位置，所述面板被保持抵靠卫星的主体。

5. 发明授权

US08679582B2 Tunable variable emissivity materials and methods for controlling the temperature of spacecraft using tunable variable emissivity materials 有权
标题翻译：可调谐的可变辐射率材料和使用可调谐的可变辐射材料来控制航天器的温度的方法
公开(公告)号：US08679582B2
公开(公告)日：2014-03-25
申请号：US12705782
申请日：2010-02-15
申请人： Robert Cumberland , William B. Barvose-Carter , Adam F. Gross
发明人： Robert Cumberland , William B. Barvose-Carter , Adam F. Gross
IPC分类号： B05D3/02
CPC分类号： B64G1/54 , C01G45/1264 , C01P2002/34 , C01P2002/77 , C01P2006/32 , C01P2006/42
摘要： Tunable variable emissivity materials, methods for fabricating tunable variable emissivity materials, and methods for controlling the temperature of a spacecraft using tunable variable emissivity materials have been provided. In an exemplary embodiment, a variable emissivity material has the formula M1(1−(x+y))M2xM3yMnO3, wherein M1 comprises lanthanum, praseodymium, scandium, yttrium, neodymium or samarium, M2 comprises an alkali earth metal, M3 comprises an alkali earth metal that is not M2, and x, y, and (x+y) are less than 1. The material has a critical temperature (Tc) in the range of about 270 to about 320K and a transition width is less than about 30K.
摘要翻译：已经提供了可调谐的可变发射材料，用于制造可调谐的发射率材料的方法以及使用可调谐的发射率材料来控制航天器的温度的方法。在示例性实施例中，可变发射率材料具有式M1（1-（x + y））M2xM3yMnO3，其中M1包括镧，镨，钪，钇，钕或钐，M2包括碱土金属，M3包含碱不属于M2的地球金属，x，y和（x + y）小于1.该材料的临界温度（Tc）在约270至约320K的范围内，并且转变宽度小于约30K 。

6. 发明授权

US08665175B2 Thermal control film for spacecraft 有权
标题翻译：航天器热控薄膜
公开(公告)号：US08665175B2
公开(公告)日：2014-03-04
申请号：US10584407
申请日：2006-05-17
申请人： Paul Joseph Brooks
发明人： Paul Joseph Brooks
IPC分类号： H01Q15/14 , H01Q15/08 , G02B5/20 , G02B1/04 , B32B7/02
CPC分类号： B32B17/10018 , B32B27/36 , B64G1/54 , B64G1/58 , B64G1/66 , G02B5/281 , G02B5/282 , H01Q1/002 , H01Q1/28 , H01Q1/422 , Y10T428/261
摘要： A thermal control film for use in spacecraft having a multi-layer interference filter adapted to exhibit high reflectivity to solar radiation, low absorptivity across the microwave spectrum and high emissivity in the far infra-red. The film is free from metal and extends over the active face of an antenna carried by the spacecraft. Such a film exhibits the desired thermo-optical properties for a thermal control radiator surface and can be used over the active face of a communications or radar antenna without disrupting the RF signal.
摘要翻译：一种用于航天器的热控膜，其具有适于对太阳辐射呈现高反射率的多层干涉滤光片，微波频谱上的低吸收率和远红外线中的高辐射率。该电影没有金属，并延伸到由航天器携带的天线的主动面上。这种膜对于热控散热器表面具有期望的热光学性能，并且可以在通信或雷达天线的有源面上使用，而不会中断RF信号。

7. 发明授权

US08550406B2 Spacecraft magnetic shield 有权
标题翻译：航天器磁盾
公开(公告)号：US08550406B2
公开(公告)日：2013-10-08
申请号：US13134733
申请日：2011-06-15
申请人： Robert T. Bigelow
发明人： Robert T. Bigelow
IPC分类号： B64G1/52
CPC分类号： B64G1/54
摘要： A spacecraft magnetic shield apparatus is disclosed. One embodiment has an armature attached at one end of a spacecraft and an electromagnet attached to the other end. A computer determines the position of the armature and electromagnet in relation to the spacecraft, and a power source powers the electromagnet. In operation, the positioning of the electromagnet is generally in line with incoming charged particles or ion radiation and powering of the electromagnet creates a magnetic field that deflects a percentage of the incoming charged particles or ion radiation from directly impacting the spacecraft.
摘要翻译：公开了一种航天器磁屏蔽装置。一个实施例具有附接在航天器的一端的电枢和附接到另一端的电磁体。计算机确定电枢和电磁体相对于航天器的位置，电源为电磁铁供电。在操作中，电磁铁的定位通常与进入的带电粒子或离子辐射一致，并且电磁铁的供电产生磁场，其使进入的带电粒子或离子辐射的百分比偏转直接影响到航天器。

8. 发明授权

US08475879B1 Polymer nanocomposites with improved resistance to ionizing radiation 有权
标题翻译：具有改进的电离辐射抗性的聚合物纳米复合材料
公开(公告)号：US08475879B1
公开(公告)日：2013-07-02
申请号：US12942251
申请日：2010-11-09
申请人： Vesna Borjanovic , Olga Alexander Shenderova , Gary Elder McGuire
发明人： Vesna Borjanovic , Olga Alexander Shenderova , Gary Elder McGuire
IPC分类号： B05D3/02
CPC分类号： B82Y30/00 , B64G1/54
摘要： Polymer nanocomposites with improved resistance to high energy ionizing radiation. Certain embodiments involve methods for providing a nanocomposite material with resistance to high energy ionizing radiation using nanodiamond, zinc oxide and mixtures of these nanoparticles with other nanoparticles dispersed within the matrix. Other embodiments relate to methods of delivering and dispersing the nanoparticles through the material or a surface layer. Other embodiments include methods of forming chemical bonds between the nanoparticles and the material. This abstract is not to be considered limiting, since other embodiments may deviate from the features described in this abstract.
摘要翻译：具有改善的抗高电离电离辐射的聚合物纳米复合材料。某些实施方案涉及使用纳米金刚石，氧化锌以及这些纳米颗粒与分散在基质内的其他纳米颗粒的混合物来提供对高能电离辐射具有抗性的纳米复合材料的方法。其它实施方案涉及通过材料或表面层递送和分散纳米颗粒的方法。其它实施方案包括在纳米颗粒和材料之间形成化学键的方法。该摘要不被认为是限制性的，因为其他实施例可能偏离本摘要中描述的特征。

9. 发明申请

US20120318928A1 Spacecraft magnetic shield 有权
标题翻译：航天器磁盾
公开(公告)号：US20120318928A1
公开(公告)日：2012-12-20
申请号：US13134733
申请日：2011-06-15
申请人： Robert T. Bigelow
发明人： Robert T. Bigelow
IPC分类号： B64G1/54 , B64G1/52
CPC分类号： B64G1/54
摘要： A spacecraft magnetic shield apparatus is disclosed. One embodiment has an armature attached at one end of a spacecraft and an electromagnet attached to the other end. A computer determines the position of the armature and electromagnet in relation to the spacecraft, and a power source powers the electromagnet. In operation, the positioning of the electromagnet is generally in line with incoming charged particles or ion radiation and powering of the electromagnet creates a magnetic field that deflects a percentage of the incoming charged particles or ion radiation from directly impacting the spacecraft.
摘要翻译：公开了一种航天器磁屏蔽装置。一个实施例具有附接在航天器的一端的电枢和附接到另一端的电磁体。计算机确定电枢和电磁体相对于航天器的位置，电源为电磁铁供电。在操作中，电磁铁的定位通常与进入的带电粒子或离子辐射一致，并且电磁铁的供电产生磁场，其使进入的带电粒子或离子辐射的百分比偏转直接影响到航天器。

10. 发明授权

US08292233B2 Solar protection device for space instrument 有权
标题翻译：太空保护装置
公开(公告)号：US08292233B2
公开(公告)日：2012-10-23
申请号：US12167346
申请日：2008-07-03
申请人： Claude Alis , Jacques Vieillot
发明人： Claude Alis , Jacques Vieillot
IPC分类号： B64G1/54
CPC分类号： B64G1/50 , B64G1/54 , G01J5/02 , G01J5/0205 , G01J5/04 , G01J5/046 , G01J5/06 , G01J2001/0276
摘要： The present invention relates to a solar protection device for space instrument. This invention is particularly suited to electromagnetic measuring instruments pointing in a direction close to that of the sun. To ensure the continuous availability, the performance and the non-degradation of collecting instruments directed towards the sun, the invention proposes the use of solar baffling thermally and mechanically decoupled from the platform supporting the collecting instruments of the equipment.
摘要翻译：本发明涉及一种用于空间仪器的太阳能保护装置。本发明特别适合于指向靠近太阳的方向的电磁测量仪器。为了确保持续可用性，针对太阳的收集仪器的性能和不劣化，本发明提出使用从支撑设备的收集仪器的平台热和机械地分离的太阳能挡板。

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