公开(公告)号：US20200148398A1

公开(公告)日：2020-05-14

申请号：US16740644

申请日：2020-01-13

Applicant: Richard Williams

Inventor： Richard Williams

IPC: B64G1/54 ,  B64G1/42

Abstract: Example aspects of a deployed electromagnetic radiation deflector shield assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The deployed electromagnetic radiation deflector shield assembly can comprise a base station on a ground surface; a deployed electromagnetic radiation deflector shield comprising an electromagnet configured to generate a magnetic field configured to deflect radiation from a radiation source; and an upright supporting the deployed electromagnetic radiation deflector shield at a distance away from the base station, and wherein the distance is configured to prevent the magnetic field from interfering with the base station.

公开(公告)号：US10442559B2

公开(公告)日：2019-10-15

申请号：US15226219

申请日：2016-08-02

Applicant: The Boeing Company

Inventor： Jian Dong ,  Naveed Moayyed Hussain

IPC: B64G1/54 ,  B64G1/56 ,  E04B1/92 ,  E04C2/284 ,  E04C2/34 ,  E04C2/36 ,  E04C2/52 ,  B32B5/02 ,  B32B7/12 ,  B32B9/00 ,  B32B15/02 ,  B32B27/06 ,  B32B27/12 ,  B32B27/32 ,  B32B1/08 ,  B32B3/08 ,  B32B3/12 ,  B64C1/06 ,  B64C1/12 ,  B64C1/40

Abstract: 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.

公开(公告)号：US20190256228A1

公开(公告)日：2019-08-22

申请号：US16385643

申请日：2019-04-16

Applicant: UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF NASA

Inventor： DONALD L. THOMSEN, III ,  SANKARA N. SANKARAN ,  JOEL A. ALEXA

IPC: B64G1/58 ,  B64G1/54 ,  C23C28/02 ,  C23C4/08 ,  B32B15/01 ,  G21F1/12 ,  C22C14/00 ,  C23C4/137 ,  C23C4/134

Abstract: In some aspects, this disclosure relates to improved Z-grade materials, such as those used for shielding, systems incorporating such materials, and processes for making such Z-grade materials. In some examples, the Z-grade material includes a diffusion zone including mixed metallic alloy material with both a high atomic number material and a lower atomic number material. In certain examples, a process for making Z-grade material includes combining a high atomic number material and a low atomic number material, and bonding the high atomic number material and the low atomic number together using diffusion bonding. The processes may include vacuum pressing material at an elevated temperature, such as a temperature near a softening or melting point of the low atomic number material. In another aspect, systems such as a vault or an electronic enclosure are disclosed, where one or more surfaces of Z-grade material make up part or all of the vault/enclosure.

公开(公告)号：US20170121038A1

公开(公告)日：2017-05-04

申请号：US14926669

申请日：2015-10-29

Applicant: THE BOEING COMPANY

Inventor： Jian Dong ,  Naveed Moayyed Hussain

IPC: B64G1/54

CPC classification number: B64G1/543 ,  B64G1/12 ,  B64G1/546 ,  B64G2001/525

Abstract: A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

公开(公告)号：US20170066202A1

公开(公告)日：2017-03-09

申请号：US14992902

申请日：2016-01-11

Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATION

Inventor： GLEN A. McBRAYER ,  JUD J. YAMANE ,  SUNDEEP K. PURI ,  BRIAN J. HILL ,  EDWARD R. ZABIELSKI ,  GERARDO HERNANDEZ ,  FRANK H. HOREY ,  SAUL PEREZ

IPC: B29C70/30 ,  B29C35/00 ,  B64G1/54 ,  B29C70/06 ,  B64G1/10 ,  B29C35/02 ,  B29C70/54

CPC classification number: B64G1/54 ,  B29C35/02 ,  B29C35/0227 ,  B29C70/44 ,  B29C70/885 ,  B29C2035/005 ,  B29K2105/256 ,  B29K2307/04 ,  B29K2867/00 ,  B29K2879/00 ,  B29K2905/02 ,  B29L2031/3097 ,  B64G1/66

Abstract: A method for fabricating a carbon fiber composite part, for example, a sun shield structural assembly on a satellite. The composite part is fabricated on a carbon fiber/bismaleimide (BMI) composite tool, where a moisture barrier is positioned on the tool prior to carbon fiber part ply layers being positioned on the tool to prevent moisture from the tool from entering the part. In one embodiment, the moisture barrier includes cross-wise strips of aluminum foil. A wrinkle barrier is positioned on the moisture barrier before the carbon fiber part ply layers so that anomalies or wrinkles in the moisture barrier are not transferred to the part layers.

Abstract translation: 一种制造碳纤维复合部件的方法，例如卫星上的防晒结构组件。 复合部件制造在碳纤维/双马来酰亚胺（BMI）复合工具上，其中在碳纤维部分层层位于工具上之前，防潮层位于工具上，以防止工具中的湿气进入该部件。 在一个实施例中，防潮层包括铝箔的交叉条。 在碳纤维部分层层之前，在防潮层上设置皱纹屏障，使得防潮层中的异常或褶皱不会转移到部分层。

公开(公告)号：US08882048B2

公开(公告)日：2014-11-11

申请号：US13113001

申请日：2011-05-20

Applicant: Eugene M. Levin ,  Joseph A. Carroll ,  Jerome Pearson

Inventor： Eugene M. Levin ,  Joseph A. Carroll ,  Jerome Pearson

IPC: B64G1/64 ,  B64G1/00 ,  B64G1/56 ,  B64G1/40 ,  B64G1/54

CPC classification number: B64G1/00 ,  B33Y80/00 ,  B64G1/1085 ,  B64G1/242 ,  B64G1/40 ,  B64G1/54 ,  B64G1/56 ,  B64G1/64 ,  B64G1/646 ,  B64G1/648 ,  B64G1/66

Abstract: A processing and delivery system is in space around a celestial body having a magnetic field. The system includes at least one facility having supplies and configured for in-space recycling and manufacturing to produce processed objects utilizing space debris objects and the supplies. The system includes at least one space vehicle configured to deliver the space debris objects from their orbits to the at least one facility using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver new supplies to the at least one facility from other orbits using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver the processed objects from the at least one facility to their destination orbits using electrodynamic propulsion.

Abstract translation: 处理和传送系统在具有磁场的天体周围。 该系统包括至少一个具有供应物并且被配置用于空间内回收和制造的设施，以利用空间碎片物体和物品来生产加工物体。 该系统包括至少一个空间车辆，其构造成使用电动推进将空间碎片物体从其轨道传送到至少一个设施。 该系统包括至少一个空间车辆，其构造成使用电动推进从其它轨道向至少一个设施提供新的供应。 该系统包括至少一个空间车辆，其构造成使用电动推进将处理过的物体从至少一个设施传送到其目的地轨道。

公开(公告)号：US20140239124A1

公开(公告)日：2014-08-28

申请号：US13781483

申请日：2013-02-28

Applicant: The Boeing Company

Inventor： Richard W. ASTON ,  Anna M. TOMZYNSKA

IPC: B64G1/40 ,  B64G1/54 ,  B64G1/44

CPC classification number: B64G1/10 ,  B64G1/402 ,  B64G1/44 ,  B64G1/54 ,  B64G1/58 ,  B64G2001/1092 ,  Y10T29/49826

Abstract: A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

Abstract translation: 航天器可以包括具有多个模块侧的模块结构。 航天器可包括延伸穿过航天器中心的中心圆柱体。 中心圆柱体可以是沿着航天器的纵向轴线延伸的唯一闭合的横截面。

公开(公告)号：US08678322B2

公开(公告)日：2014-03-25

申请号：US13095659

申请日：2011-04-27

Applicant: David S. Long

Inventor： David S. Long

IPC: B64G1/54 ,  B64G1/00 ,  G21F5/06 ,  G21F1/12

CPC classification number: B64G1/54 ,  B64G1/423 ,  B64G1/56 ,  G21F1/06 ,  G21F1/10 ,  G21F1/12 ,  G21F7/00

Abstract: Radiation shields include an outer composite wall, an inner composite wall, and an enclosed fuel chamber disposed between the inner and outer composite walls. A fuel may be contained within the enclosed fuel chamber. Spacecraft include one or more such radiation shields, and may further include a fuel cell and a conduit providing fluid communication between the fuel chamber of the radiation shield and the fuel cell. Methods of forming a radiation shield system include forming an enclosed fuel chamber between an outer composite wall and an inner composite wall of a radiation shield, and providing fuel within the enclosed fuel chamber.

Abstract translation: 辐射屏蔽包括外复合壁，内复合壁和设置在内外复合壁之间的封闭燃料室。 燃料可以被包含在封闭的燃料室内。 航天器包括一个或多个这样的辐射屏蔽，并且还可以包括燃料电池和提供辐射屏蔽的燃料室与燃料电池之间的流体连通的导管。 形成辐射屏蔽系统的方法包括在外部复合壁和辐射屏蔽的内部复合壁之间形成封闭的燃料室，并在封闭的燃料室内提供燃料。

公开(公告)号：US20120043427A1

公开(公告)日：2012-02-23

申请号：US13214527

申请日：2011-08-22

Applicant: Christian FLEMIN ,  Andrew WALKER

Inventor： Christian FLEMIN ,  Andrew WALKER

IPC: B64G1/54

CPC classification number: B64G1/50 ,  B64G1/503 ,  B64G1/58 ,  H01J23/033 ,  H01J25/34

Abstract: The device for thermal monitoring for a piece of equipment, whereby said piece of equipment is integrated on a craft placed in a forced vacuum environment, an outside part (7) of the equipment projecting outside of a wall (3) of the craft and being subjected to a solar radiation flux (15), comprises an absorbent screen (13) that is suitable for being placed between the outside part (7) of the equipment and the wall (3) of the craft, whereby this absorbent screen (13) has—on at least one portion of its front face, designed to be placed on the side removed from the wall of the craft—an absorptivity αSOLAR that is the largest possible in the field of solar radiation, coupled to a low emissivity εIR in the infrared spectrum. The absorbent screen (13) is made of a very heat-conductive material and has—on at least a portion of its rear face, suitable for being oriented toward the wall of the craft—a high emissivity εIR in the infrared spectrum, typically greater than or equal to 0.7.

Abstract translation: 用于一件设备的热监测装置，其中所述设备集成在放置在强制真空环境中的工艺上，该设备的外部部分（7）突出到工艺的壁（3）的外侧，并且 经过太阳辐射通量（15），包括适于放置在设备的外部部分（7）和工艺的壁（3）之间的吸收性筛网（13），由此该吸收性筛网（13） 具有其前表面的至少一部分，被设计成放置在从工艺的壁上移除的一侧上 - 在太阳辐射领域中最大可能的吸收率αSOLAR，耦合到低发射率 在红外光谱。 吸收性筛网（13）由非常导热的材料制成，并且在其后表面的至少一部分上适合于朝向工艺的壁的方向 - 红外光谱中的高发射率和红外线， 通常大于或等于0.7。

公开(公告)号：US20110180670A1

公开(公告)日：2011-07-28

申请号：US11703288

申请日：2007-02-07

Applicant: Robert F. D'Ausilio ,  James R. Stuart ,  Franklin H. Williams, JR.

Inventor： Robert F. D'Ausilio ,  James R. Stuart ,  Franklin H. Williams, JR.

IPC: B64G1/14 ,  B64G1/40 ,  B64G1/66 ,  B64G1/54 ,  B64G1/24

CPC classification number: B64G1/1078 ,  B64G1/007 ,  B64G1/222 ,  B64G1/242 ,  B64G1/283 ,  B64G1/288 ,  B64G1/363 ,  B64G1/405 ,  B64G1/406 ,  B64G1/408 ,  B64G1/422 ,  B64G1/44 ,  B64G1/503 ,  B64G1/646 ,  B64G1/66

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract translation: 公开了轨道交通运输与恢复系统（IOSTAR™）（10）。 本发明的一个优选实施例包括由核反应堆（19）供电的空间拖船。 IOSTAR TM包括在一端连接到推进剂罐（13）的可折叠起重臂（11），该推进剂罐储存用于电动推进系统（12）的燃料。 起重臂（11）的这一端配备有能够把持和固定卫星（15）的对接硬件（14），并且作为重新装满水箱（13）的装置。 安装在起重臂（11）上的散热器面板（16）从反应器（19）散热。 辐射屏蔽（20）位于反应器（19）旁边，以保护在悬臂（11）的远端处的卫星有效载荷（15）。 IOSTAR™（10）将能够实现会合和对接机动，使其能够在低地球停放轨道和较高轨道位置或太阳系中其他位置之间移动航天器。