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61. 发明授权

US11001684B2 Puncture healing engineered polymer blends 有权
公开(公告)号：US11001684B2
公开(公告)日：2021-05-11
申请号：US14956026
申请日：2015-12-01
申请人： U.S.A, as represented by the Administrator of the National Aeronautics and Space Administration
发明人： Keith L. Gordon , Emilie J. Siochi , Dennis C. Working , Russell W. Smith
IPC分类号： C08J5/18 , C08K7/14 , C08K7/06 , C08J3/00 , B29C73/18 , B32B27/00 , F41H3/00 , B64G1/56
摘要： One aspect of the present invention is a puncture healing polymer blend comprising a self-healing first polymer material having sufficient melt elasticity to snap back and close a hole formed by a projectile passing through the material at a velocity sufficient to produce a local melt state in the first polymer material. The puncture healing polymer blend further includes a non-self-healing second material that is blended with the first polymer material. The blend of self-healing first polymer material and second material is capable of self-healing, and may have improved material properties relative to known self-healing polymers.

62. 发明授权

US10815014B2 Spacecraft collision-avoidance propulsion system and method 有权
公开(公告)号：US10815014B2
公开(公告)日：2020-10-27
申请号：US16111612
申请日：2018-08-24
申请人： Jerome Drexler
发明人： Jerome Drexler
IPC分类号： B64G1/56 , B64G1/26 , B64G1/40 , B64G1/52 , G21B3/00 , G21H7/00
摘要： A collision-avoidance propulsion system and method for orbiting satellites and other spacecraft takes advantage of ambient cosmic rays in space to catalyze micro-fusion events via particle-target fusion and muon-catalyzed fusion processes, using the reaction products to produce thrust upon orbiting satellites and other spacecraft. A supply of deuterium-containing particle fuel material is propelled in a specified direction of the spacecraft in response to indication of a potential collision with another space object (e.g. orbiting debris). In one embodiment, this may be performed by propellant gas expelling the fuel material through conduits to specified ports on the exterior of the spacecraft. The propelled material interacts with the ambient cosmic rays and muon generated from those cosmic rays to induce micro-fusion. A portion of the energetic reaction products (e.g. alpha particles) are received upon the spacecraft to alter its trajectory in a manner that avoids the potential collision.

63. 发明授权

US10336474B2 Method and device for deflection of space debris 有权
公开(公告)号：US10336474B2
公开(公告)日：2019-07-02
申请号：US15353388
申请日：2016-11-16
申请人： CENTRE NATIONAL D'ETUDES SPATIALES
发明人： Christophe Bonnal
IPC分类号： B64G1/40 , B64G1/00 , B64G1/10 , B64G1/24 , B64G1/56
摘要： The invention relates to a method for deflecting space debris comprising steps of: launching (E2) a thruster (2) by means of a sounding rocket (1) at a target altitude close to that of the one or more debris to be deflected. generating (E3) by the thruster a gas cloud (G) above the sounding rocket.

64. 发明申请

US20190047234A1 MULTI-FUNCTIONAL PROTECTIVE ASSEMBLIES, SYSTEMS INCLUDING PROTECTIVE ASSEMBLIES, AND RELATED METHODS 审中-公开
公开(公告)号：US20190047234A1
公开(公告)日：2019-02-14
申请号：US16103428
申请日：2018-08-14
申请人： Northrop Grumman Innovation Systems, Inc.
发明人： Steven F. Stone , Matt Armentrout , Christopher Deemer , Carl Madsen
IPC分类号： B29C65/00 , B64G1/22 , B64G1/54 , B64G1/56 , B64G1/58
摘要： A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

65. 发明申请

US20170210494A1 UNPRESSURIZED CARGO TRANSFER PALLET AND STRUCTURAL SUPPORT 审中-公开
公开(公告)号：US20170210494A1
公开(公告)日：2017-07-27
申请号：US15002435
申请日：2016-01-21
申请人： The Boeing Company
发明人： Christopher B. BLACKWELL
IPC分类号： B64G1/64 , B64G1/58 , B64G1/56 , B64G1/42 , B64G1/54
CPC分类号： B64G1/641 , B64G1/002 , B64G1/12 , B64G1/14 , B64G1/42 , B64G1/54 , B64G1/56 , B64G1/58 , B64G1/62 , B64G1/645 , B64G1/646 , B64G4/00 , B64G2004/005
摘要： An unpressurized cargo pallet including a pallet base having a frame, the frame being conformal with a structural exterior surface of a space vehicle to effect structural integration of the pallet base with the structural exterior surface of the space vehicle so that the pallet base forms a portion of the structural exterior surface, where the frame includes an interior surface, and an exterior surface that forms at least part of the structural exterior surface of the space vehicle, a cargo attachment interface disposed on the interior surface of the frame, and at least one grapple disposed on the exterior surface of the frame.

66. 发明授权

US09429371B2 Radiator systems 有权
公开(公告)号：US09429371B2
公开(公告)日：2016-08-30
申请号：US14746399
申请日：2015-06-22
申请人： PARAGON SPACE DEVELOPMENT CORPORATION
发明人： Thomas William Morin , Taber K. MacCallum , Norman Jacob Hahn , John Zaniel Maccagnano
IPC分类号： F24D3/14 , F28F1/22 , B64G1/50 , F28D1/053 , F28D15/00 , F24D3/12 , F24D3/02 , F28F1/20 , B64G1/56 , B64D13/00 , F28D21/00
CPC分类号： B23P15/26 , B64G1/503 , F28D1/053 , F28D15/00 , F28D2021/0031 , F28F1/22 , F28F2265/00 , F28F2275/06
摘要： A system of spacecraft radiators comprising pre-formed thermal-transfer modules joined together by at least one solid-state welding process. Critical failure points are eliminated by forming the thermal-transfer modules as a single unitary piece, preferably by an extrusion process. The thermal-transfer modules allow the formation of larger radiator assemblies, which may comprise a wide range of sizes and physical geometries.

67. 发明授权

US09327848B2 Method of deploying a spacecraft shield in space 有权
标题翻译：在太空中部署航天器护罩的方法
公开(公告)号：US09327848B2
公开(公告)日：2016-05-03
申请号：US13507179
申请日：2012-06-11
申请人： Robert T. Bigelow
发明人： Robert T. Bigelow
IPC分类号： B64G1/56 , B82Y30/00
CPC分类号： B64G1/56 , B82Y30/00 , B82Y40/00 , Y10S977/742 , Y10S977/842 , Y10S977/902
摘要： A shield comprised of carbon nanotube materials is used to provide a level of protection to a spacecraft. Shield segments are produced in a facility in space. The segments are transported from the facility to a vicinity of a spacecraft hull. The segments are assembled over the hull to substantially cover an area of the hull.
摘要翻译：使用由碳纳米管材料组成的屏蔽罩来为航天器提供一定程度的保护。盾构段在空间设施中生产。这些段从设施运送到航天器船体附近。这些段被组装在船体上以基本上覆盖船体的区域。

68. 发明授权

US08657235B2 Space debris removal using upper atmosphere and vortex generator 有权
标题翻译：使用上层大气和涡流发生器去除空间碎片
公开(公告)号：US08657235B2
公开(公告)日：2014-02-25
申请号：US12986346
申请日：2011-01-07
申请人： Daniel Alan Gregory , John-Francis Mergen
发明人： Daniel Alan Gregory , John-Francis Mergen
IPC分类号： B64G1/56 , B64B1/00 , F42B99/00 , F41H11/00
CPC分类号： B64G1/242 , B64G1/56
摘要： The systems and methods of the invention modulate atmospheric gases to temporarily increase the amount of atmospheric particles in the path of the debris, in order to decelerate the debris and accelerate natural orbital decay to the point of atmospheric re-entry. In one aspect of the invention, clearing the space debris includes propelling a plume of atmospheric gases substantially orthogonal to the path of the debris such that the debris collides with the gaseous plume as it passes through the plume. Increased atmospheric drag from the gaseous particles of the plume in the path of the debris obstructs a forward propagation of the debris and gradually decelerates the debris, leading eventually to atmospheric recapture. Embodiments of the invention can be employed in any number of applications, including without limitation, clearing debris in the low-earth orbit (LEO) which is particularly susceptible to debris build-up, de-orbiting non-refuse payloads from orbits, and clearing debris from geosynchronous orbits.
摘要翻译：本发明的系统和方法调节大气气体以暂时增加碎片路径中的大气颗粒的量，以便使碎片减速并加速天然轨道衰减到大气再入口点。在本发明的一个方面，清理空间碎片包括推动基本上垂直于碎片路径的大气气体的羽流，使得碎片在气流穿过羽流时与气体羽流碰撞。来自碎片路径中的羽流的气体颗粒的大气阻力增加阻碍了碎片的向前传播，并使碎片逐渐减速，最终导致大气再捕获。本发明的实施例可以用于任何数量的应用，包括但不限于清除特别容易产生碎屑堆积的低地球轨道（LEO）中的碎片，轨道上的非垃圾有效载荷的轨道和清除来自地球同步轨道的碎片。

69. 发明授权

US07309049B2 Orbital debris shield 有权
标题翻译：轨道碎片盾
公开(公告)号：US07309049B2
公开(公告)日：2007-12-18
申请号：US11498659
申请日：2006-08-03
申请人： Robert T. Bigelow
发明人： Robert T. Bigelow
IPC分类号： B64G1/56
CPC分类号： B64G1/56 , Y10T428/192
摘要： An orbital debris shield for protecting the hull of a spacecraft. The shield is comprised of a number of flexible and releasably attached gores that substantially cover the hull. Interleafed between layers of the gores are layers of a spacing material. As debris collides with the gores, the material is shocked and breaks up to some degree. As the shocked debris disperses through a layer of the gore, the spacing material interacts with the debris. After dispersing through a number of layers of the gores and the spacing material, the debris transfers a significant portion of kinetic energy and the probability of the remaining particles piercing the hull is significantly decreased.
摘要翻译：用于保护航天器船体的轨道碎片盾。护罩由许多基本上覆盖船体的柔性和可释放地附接的山脉组成。沟渠层之间的交错是间隔材料层。随着碎屑与山羊碰撞，材料受到震动，并在一定程度上破裂。当震动的碎屑通过一层玻璃分散时，间隔材料与碎屑相互作用。在分散通过多个层和间隔材料之后，碎屑转移了大部分动能，并且剩余的颗粒穿透船体的可能性显着降低。

70. 发明授权

US07048233B2 Dual conduction heat dissipating system for a spacecraft 有权
标题翻译：用于航天器的双传导散热系统
公开(公告)号：US07048233B2
公开(公告)日：2006-05-23
申请号：US10885604
申请日：2004-07-08
申请人： Charles Combes , Jean-Luc Foucher , Pierre Jaubert
发明人： Charles Combes , Jean-Luc Foucher , Pierre Jaubert
IPC分类号： B64G1/56
CPC分类号： B64G1/506 , B64G1/50 , B64G1/503
摘要： A system dedicated to dissipating heat produced by amplifier tubes of a spacecraft comprises a radiating panel installed substantially parallel to the amplifier tubes and thermally coupled to them to radiate to the outside a portion of the heat that they produce, a radiating receptacle whose walls define a housing adapted to receive the collectors of the amplifier tubes, and preferably a heat distributor that is preferably interleaved between the collectors and one wall of the receptacle to distribute the heat that the collectors produce between the collectors and the wall.
摘要翻译：专门用于耗散由航天器的放大器管产生的热量的系统包括：辐射板，其基本上平行于放大器管安装并热耦合到辐射面板，以将其产生的热量的一部分辐射到外部，辐射插座的壁限定为适于接收放大器管的收集器的壳体，并且优选地是热分布器，其优选地在收集器和容器的一个壁之间交错分布收集器在收集器和壁之间产生的热量。

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