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1. 发明申请

US20180251238A1 STACKABLE SPACECRAFT 审中-公开
公开(公告)号：US20180251238A1
公开(公告)日：2018-09-06
申请号：US15449368
申请日：2017-03-03
申请人： NORTHROP GRUMMAN SYSTEMS CORPORATION
发明人： ALAN R. CHERRETTE
IPC分类号： B64G1/10 , B64G1/50 , B64G1/44
CPC分类号： B64G1/10 , B64G1/002 , B64G1/1007 , B64G1/443 , B64G1/503 , B64G1/64 , B64G1/641 , B64G2001/643 , H01Q1/288 , H01Q3/26 , H01Q15/16 , H01Q19/13 , H01Q19/19 , H01Q21/28
摘要： A three-axis spacecraft including a spacecraft body including first and second opposing radiator/equipment panels, first and second opposing mounting panels, an earth deck and a zenith deck. The zenith deck faces the Earth when the spacecraft is on orbit and the first and second mounting panels face an east and west direction relative to the Earth when the spacecraft is on orbit. The spacecraft further includes a mounting cylinder extending through the spacecraft body and out of the first and second mounting panels.

2. 发明授权

US10005570B2 Strong bonded joints for cryogenic applications 有权
公开(公告)号：US10005570B2
公开(公告)日：2018-06-26
申请号：US14088438
申请日：2013-11-24
申请人： The Boeing Company
发明人： Michael Leslie Hand
IPC分类号： B64G1/40 , B64G1/64 , B64G1/00
CPC分类号： B64G1/402 , B64G1/002 , B64G1/645 , Y10T29/53657 , Y10T29/53961 , Y10T156/10 , Y10T428/249921
摘要： A method and apparatus for strong bonded wide joints for cryogenic applications. In one advantageous embodiment, an apparatus may comprise a three-dimensional preform and a plastic matrix. The plastic matrix may be impregnated in the three-dimensional preform to form a softening strip that may be capable of remaining flexible at a temperature at which a gas may have a liquid form.

3. 发明授权

US09989015B2 Launcher stage comprising a temporary support structure for temporarily supporting nozzle sections allowing access to the core of the engine 有权
公开(公告)号：US09989015B2
公开(公告)日：2018-06-05
申请号：US14385888
申请日：2013-04-12
申请人： SNECMA
发明人： Olivier Condaminet , Guy Lecompte , Philippe Matura
IPC分类号： F02K9/96 , F02K9/97 , F01D25/28 , B64G1/40 , B64G1/00
CPC分类号： F02K9/976 , B64G1/002 , B64G1/401 , F01D25/285 , F05D2230/68 , F05D2260/96 , Y10T29/49229
摘要： A stage of a space launcher including an engine core, a tank secured above the engine core, and a nozzle including a first deployable nozzle section secured below the engine core, the nozzle further including a second and a third section configured to be situated extending from each other when the nozzle is in a deployed propulsion configuration. The stage further includes a structure for temporarily supporting nozzle sections mounted on the tank, configured to change the nozzle to a configuration for accessing the engine core wherein the nozzle sections are inserted into each other, with the third section bearing against a lower support of the temporary structure.

4. 发明申请

US20180093786A1 SELF-ASSEMBLING PERSISTENT SPACE PLATFORM 审中-公开
公开(公告)号：US20180093786A1
公开(公告)日：2018-04-05
申请号：US15689993
申请日：2017-08-29
申请人： Space Systems/Loral, LLC
发明人： Robert Erik Schwarz , Robert Edward Helmer , Paul Anthony Briggs , John Douglas Lymer , Alfred Heikal Tadros , Andrew E. Turner
IPC分类号： B64G1/10 , B64G1/64 , B64G4/00
CPC分类号： B64G1/10 , B64G1/002 , B64G1/1078 , B64G1/222 , B64G1/64 , B64G1/646 , B64G4/00 , B64G2001/1092 , B64G2004/005
摘要： A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

5. 发明授权

US09915958B2 Lightweight plenum system for spacecraft application 有权
公开(公告)号：US09915958B2
公开(公告)日：2018-03-13
申请号：US15592744
申请日：2017-05-11
申请人： THE BOEING COMPANY
发明人： Galen Duff Carroll
IPC分类号： G05D23/08 , B64G1/00 , B64G1/40 , B64G1/50
CPC分类号： G05D23/1919 , B64G1/002 , B64G1/40 , B64G1/401 , B64G1/50 , G05D23/08 , Y10T137/7737
摘要： A gas distribution system for use in an enclosed volume wherein the system includes a distribution duct and a first inflatable duct portion in fluid communication with the distribution duct. The system further includes a passageway defining an opening which extends through the passageway, wherein: the opening is in fluid communication with the first inflatable duct portion; the passageway includes a valve with a flapper positioned within the opening of the passageway; and the flapper is moveable in relationship to the opening by way of a bi-metallic temperature sensing member. The system further includes an inflatable enclosure in fluid communication with the opening of the passageway, wherein the inflatable enclosure is configured to define a volume within and separated from the enclosed volume.

6. 发明授权

US09580191B2 Control surfaces for use with high speed vehicles, and associated systems and methods 有权
标题翻译：用于高速车辆的控制面，以及相关的系统和方法
公开(公告)号：US09580191B2
公开(公告)日：2017-02-28
申请号：US14550782
申请日：2014-11-21
申请人： Blue Origin, LLC
发明人： Mark Featherstone , Frederick W. Boelitz , Roger E. Ramsey , David M. Biggs
IPC分类号： B64G1/62 , B64G1/00 , B64C9/00 , B64G1/24 , F42B10/64 , B64G1/60 , F42B15/01 , B64G1/40
CPC分类号： B64G1/62 , B64C9/00 , B64G1/002 , B64G1/24 , B64G1/40 , B64G1/401 , B64G1/60 , F42B10/64 , F42B15/01
摘要： Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.
摘要翻译：具有控制表面和相关系统和方法的车辆被公开。在特定实施例中，火箭可以包括朝向火箭的后部定位的多个双向控制表面。在该实施例中，双向控制表面可操作以控制火箭在朝向前倾的方向上升和向下延伸的方向和/或飞行路径，降落。还公开了具有固定和可部署的减速表面的运载火车以及相关的系统和方法。

7. 发明授权

US09546007B2 Method and device for the successive launching of two satellites 有权
标题翻译：连续发射两颗卫星的方法和装置
公开(公告)号：US09546007B2
公开(公告)日：2017-01-17
申请号：US14003280
申请日：2012-03-06
申请人： Patrick Comtesse
发明人： Patrick Comtesse
IPC分类号： B64G1/00 , B64G1/64 , B64G1/10
CPC分类号： B64G1/002 , B64G1/1085 , B64G1/641
摘要： According to the invention, a link is established between the fixed part (4A) and the removable part (4B) of an enclosure (4) in which the second satellite is previously enclosed, said link being such that said removable part (4B) remains attached to said fixed part (4A) when said removable part (4B), initially in a first position for which said enclosure (4) is closed and encloses said second satellite, lies in a second position for which said enclosure (4) is open and able to release said satellite.
摘要翻译：根据本发明，在固定部分（4A）和外壳（4）的可移除部分（4B）之间建立了链接，其中第二卫星预先被封闭，所述链节使得所述可移除部分（4B）保持当所述可移除部分（4B）最初处于所述外壳（4）关闭并包围所述第二卫星的第一位置时，所述固定部分（4A）位于所述外壳（4）打开的第二位置并能释放所述卫星。

8. 发明申请

US20160340062A1 CRYOGENIC FUELLING SYSTEM 审中-公开
标题翻译：低温燃油系统
公开(公告)号：US20160340062A1
公开(公告)日：2016-11-24
申请号：US15112384
申请日：2015-01-30
申请人： RUAG SCHWEIZ AG, RUAG SPACE
发明人： Nicholas CHARLES EATON
IPC分类号： B64G5/00 , B67D7/40 , B67D7/04 , B64G1/00 , B64G1/40
CPC分类号： B64G5/00 , B64G1/002 , B64G1/401 , B67D7/04 , B67D7/40
摘要： A fuelling system having a fuel supply hose for connecting a launcher and a launch tower, wherein the fuel supply hose is configured for conveying a cryogenic medium between the launcher and the launch tower and wherein a first end of the fuel supply hose is releasably connectable to the launcher so as to release at lift-off of the launcher thereby allowing separation of the fuel supply hose from the launcher; characterized in that a retraction system is provided for automatically retracting the fuel supply hose upon lift-off of the launcher.
摘要翻译：一种燃料供给系统，具有用于连接发射器和发射塔的燃料供应软管，其中所述燃料供应软管构造成在所述发射器和所述发射塔之间输送低温介质，并且其中所述燃料供应软管的第一端可释放地连接到发射器以便在发射器脱离时释放，从而允许将燃料供应软管与发射器分离; 其特征在于，提供缩回系统，用于在所述发射器提起时自动缩回燃料供应软管。

9. 发明授权

US09487308B2 Launch vehicles with ring-shaped external elements, and associated systems and methods 有权
标题翻译：运载带有环形外部元件的车辆，以及相关的系统和方法
公开(公告)号：US09487308B2
公开(公告)日：2016-11-08
申请号：US13833985
申请日：2013-03-15
申请人： Mark Featherstone , John Michael Sanders , Roger E. Ramsey , Eric David Wetzel
发明人： Mark Featherstone , John Michael Sanders , Roger E. Ramsey , Eric David Wetzel
IPC分类号： B64G1/00 , B64G1/14 , F42B10/02 , F42B10/64 , B64G1/22 , B64G1/62 , B64G1/64 , B64G1/40 , B64G1/12
CPC分类号： B64G1/002 , B64G1/12 , B64G1/14 , B64G1/222 , B64G1/40 , B64G1/402 , B64G1/62 , B64G1/645 , F42B10/02 , F42B10/64
摘要： Launch vehicles with ring-shaped external elements, and associated systems and methods. A representative aerospace system includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.
摘要翻译：运载带有环形外部元件的车辆，以及相关的系统和方法。代表性的航空航天系统包括具有大致与第一端相对的第一端和第二端的运载火车，其中运载火车沿着在第一和第二端之间延伸的车辆轴线是细长的并且具有外部的向外的表面。该系统还可包括由运载火箭运载的环形元件，该环形元件具有与车辆轴线径向间隔开并至少部分周向延伸的外部向内表面的表面。环形元件可以具有面向沿着车辆轴线的第一方向的第一边缘表面和沿着车辆轴线面向第二方向的第二边缘表面，第二方向与第一方向相反。推进系统可以由运载火箭承载，并且可以具有至少一个朝向车辆的第一端定位的喷嘴以启动车辆。控制器可以与运载火箭通信，并被编程为在车辆上升期间引导车辆沿第一方向，并且在车辆下降期间在第二方向上引导车辆。

10. 发明申请

US20160046394A1 METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS 有权
标题翻译：使用电动推进系统执行推进操作的方法和装置
公开(公告)号：US20160046394A1
公开(公告)日：2016-02-18
申请号：US14828462
申请日：2015-08-17
申请人： The Boeing Company
发明人： James J. Peterka, III , Glenn N. Caplin , Richard W. Aston
IPC分类号： B64G1/24 , B64G1/40 , B64G1/00 , B64G1/26 , B64G1/10
CPC分类号： B64G1/242 , B64G1/002 , B64G1/007 , B64G1/10 , B64G1/26 , B64G1/283 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/40 , B64G1/402 , B64G1/405 , B64G1/422 , B64G1/428 , B64G1/44 , B64G1/503 , B64G1/641 , B64G2001/643
摘要： Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.
摘要翻译：公开了使用电推进系统执行推进操作的方法和装置的方法和装置。示例性方法包括部署包括电推进系统的空间车辆; 并采用电动推进系统进行姿态控制和轨道控制，无需提供其他推进系统，实现姿态控制和轨道控制。

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