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21. 发明授权

US09555904B2 Gossamer apparatus and systems for use with spacecraft 有权
标题翻译：用于航天器的消声器和系统
公开(公告)号：US09555904B2
公开(公告)日：2017-01-31
申请号：US13963761
申请日：2013-08-09
申请人： Analytical Mechanics Associates, Inc.
发明人： John Luther Abrams , Matthew Ernest Duchek
IPC分类号： B64G1/22 , B64G1/24 , B64G1/40 , B64G1/64
CPC分类号： B64G1/222 , B64G1/242 , B64G1/407 , B64G1/641
摘要： Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus.
摘要翻译：用于宇宙飞船的消赛器具和系统可以包括可展开的游丝器械。可展开的游丝器装置可以包括在它们之间延伸的多个肋构件和游丝材料，并且可以被配置成收起构型和展开构型。可部署的游丝器装置的肋构件存储用于展开可展开的游丝器具的潜在能量。

22. 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。

23. 发明申请

US20160318636A1 SYSTEM AND METHOD FOR ASSEMBLING AND DEPLOYING SATELLITES 有权
标题翻译：用于组装和部署卫星的系统和方法
公开(公告)号：US20160318636A1
公开(公告)日：2016-11-03
申请号：US14700504
申请日：2015-04-30
申请人： WorldVu Satellites Limited
发明人： Daniel W. Field , Armen Askijian , James Grossman , Alexander D. Smith
IPC分类号： B64G1/64 , B64G1/24
CPC分类号： B64G1/641 , B64G1/007 , B64G1/40 , B64G1/402 , B64G1/503 , B64G1/645 , B64G1/66 , B64G2001/643
摘要： A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites. Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit. Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner.
摘要翻译：卫星部署系统具有多个可释放的分配器模块，每个模块携带卫星，彼此相连。每个分配器模块充当具有其自己的推进单元的单独的最终级，并将一部分卫星部署到适当的高度和轨道。由于每个分配器模块可以将其卫星远离其他分配器模块，所以卫星之间的碰撞风险大大降低，这样可以以安全，及时和成本有效的方式启动大量的卫星。

24. 发明授权

US09475594B2 Launch lock assemblies with reduced preload and spacecraft isolation systems including the same 有权
标题翻译：启动具有减少的预载荷的锁定组件和包括其的航天器隔离系统
公开(公告)号：US09475594B2
公开(公告)日：2016-10-25
申请号：US13626843
申请日：2012-09-25
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Tim Daniel Barber , Ken Young , Timothy Hindle
IPC分类号： B64G1/00 , B64G1/64 , B64G1/28 , B64G1/22
CPC分类号： B64G1/641 , B64G1/283 , B64G1/285 , B64G1/286 , B64G2001/228
摘要： Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.
摘要翻译：提供减少预载的启动锁组件。发射锁定组件包括第一和第二安装件，可释放的夹紧装置和一对缩回组件。每个缩回组件包括具有相互作用的齿形表面的一对齿形构件。可释放的夹紧装置通常将第一和第二安装件保持在夹紧的接合状态。当可释放的夹紧装置被致动时，第一和第二安装件从夹紧的接合中释放，并且每个缩回组件的一个齿形构件相对于另一个缩回组件的另一个齿形构件在相反的方向上移动以限定一个轴向间隙第一个安装件的每一侧。

25. 发明授权

US09463882B1 System and method for assembling and deploying satellites 有权
标题翻译：组装和部署卫星的系统和方法
公开(公告)号：US09463882B1
公开(公告)日：2016-10-11
申请号：US14700504
申请日：2015-04-30
申请人： WorldVu Satellites Limited
发明人： Daniel W. Field , Armen Askijian , James Grossman , Alexander D. Smith
IPC分类号： G01C23/00 , G05D1/00 , G05D3/00 , G06F7/00 , G06F17/00 , B64G1/64 , B64G1/24
CPC分类号： B64G1/641 , B64G1/007 , B64G1/40 , B64G1/402 , B64G1/503 , B64G1/645 , B64G1/66 , B64G2001/643
摘要： A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites. Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit. Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner.
摘要翻译：卫星部署系统具有多个可释放的分配器模块，每个模块携带卫星，彼此相连。每个分配器模块充当具有其自己的推进单元的单独的最终级，并将一部分卫星部署到适当的高度和轨道。由于每个分配器模块可以将其卫星远离其他分配器模块，所以卫星之间的碰撞风险大大降低，这样可以以安全，及时和成本有效的方式启动大量的卫星。

26. 发明申请

US20160169646A1 METHOD AND DEVICE FOR LINEAR CONNECTION AND SEPARATION OF TWO ELEMENTS, WITH OFFSET ENERGY MEANS 审中-公开
标题翻译：用于线性连接和分离两个元件的方法和装置，具有偏置能量
公开(公告)号：US20160169646A1
公开(公告)日：2016-06-16
申请号：US14908834
申请日：2014-07-31
申请人： AIRBUS DEFENCE AND SPACE SAS
发明人： Patrick Comtesse , Felipe Medina , Luc Preaud
IPC分类号： F42B15/36
CPC分类号： F42B15/36 , B64G1/641 , B64G1/645 , F42B15/38
摘要： A method and device enable the linear separation of two elements attached to each other through two connecting surfaces which are conical in this example, of a first element and a second element respectively, using thermite placed on the other side of the wall of the outer element, facing a connecting arrangement placed between both connecting surfaces. An electrical triggering of the thermite causes a quick and local warming-up, at the connecting arrangement which, after melting, enables both elements to be separated.
摘要翻译：一种方法和装置能够通过两个连接表面彼此附接的两个元件进行线性分离，所述两个连接表面在本实例中是分别为第一元件和第二元件的圆锥形，使用放置在外部元件的壁的另一侧上的热绝缘体面对放置在两个连接表面之间的连接装置。在热连接装置上，电热触发铝电解质会导致快速和局部的预热，熔化之后可以使两个元件分离。

27. 发明授权

US09360075B2 Vibration isolation system and method 有权
标题翻译：振动隔离系统及方法
公开(公告)号：US09360075B2
公开(公告)日：2016-06-07
申请号：US14002027
申请日：2011-11-01
申请人： Conor D. Johnson , John M. Howat , Paul S. Wilke
发明人： Conor D. Johnson , John M. Howat , Paul S. Wilke
IPC分类号： F16F9/30 , B64G1/64 , B64G1/22
CPC分类号： F16F9/306 , B64G1/641 , B64G2001/228
摘要： A vibration isolator (100) includes a flexure (102), a constrained VEM layer coupler (104), and a constrained VEM layer (106) configured to oppose relative translational and rotational motion between points of the flexure. The flexure may be a loop flexure and may include multiple loops that may be elliptical, circular, rectangular or square in overall aspect, for example. In multi-loop embodiments, the loops may share a common major axis or their major axes may be at an angle to one another. The device enhances damping by providing an increase in viscoelastic surface area over that available in the surface area of the flexure and provides a method of adjusting the strain in the VEM as the flexure undergoes deflection.
摘要翻译：振动隔离器（100）包括弯曲部（102），约束的VEM层耦合器（104）和受限的VEM层（106），其被配置为抵抗弯曲点之间的相对平移和旋转运动。挠曲可以是环弯曲，并且可以包括例如在整个方面可以是椭圆形，圆形，矩形或方形的多个环。在多回路实施例中，回路可以共享共同的长轴，或者它们的主轴可以彼此成一角度。该装置通过提供比挠曲件的表面区域中可用的更大的粘弹性表面积来增强阻尼，并且提供了当挠曲经历偏转时调节VEM中的应变的方法。

28. 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。

29. 发明申请

US20160001898A1 SPACE PROPULSION MODULE HAVING BOTH ELECTRIC AND SOLID FUEL CHEMICAL PROPULSION 审中-公开
标题翻译：具有电动和固体燃料化学推进剂的空间推进模块
公开(公告)号：US20160001898A1
公开(公告)日：2016-01-07
申请号：US14770329
申请日：2014-02-26
申请人： SNECMA , HERAKLES
发明人： Olivier Bernard Duchemin , Dominique Indersie , Pascal Benoit Caubet , Pierre Yvart
IPC分类号： B64G1/40 , F02K9/76
CPC分类号： B64G1/404 , B64G1/007 , B64G1/403 , B64G1/405 , B64G1/641 , F02K9/08 , F02K9/76 , F03H1/0075
摘要： A space propulsion module in particular for fitting to spacecraft such as satellites, probes, or indeed the upper stages of rockets. According to the invention, the space propulsion module comprises a solid propellant chemical thruster (10) having a main body (11), and at least one electric thruster (30), said at least one electric thruster (30) being mounted on said main body (11) of the solid propellant chemical thruster (10).
摘要翻译：空间推进模块，特别适用于诸如卫星，探测器或实际上火箭上段的航天器。根据本发明，空间推进模块包括具有主体（11）的固体推进剂化学推进器（10）和至少一个电推进器（30），所述至少一个电推进器（30）安装在所述主体固体推进剂化学推进器（10）的主体（11）。

30. 发明申请

US20150353211A1 PNEUMATIC CUBESAT PAYLOAD DEPLOYMENT SYSTEM UTILIZING LAUNCH VEHICLE TANK PRESSURE 有权
标题翻译：使用启动车辆压力的气动柴油机PAYLOAD部署系统
公开(公告)号：US20150353211A1
公开(公告)日：2015-12-10
申请号：US14726896
申请日：2015-06-01
申请人： Ventions, LLC
发明人： Adam P. London , Bevan Gerber-Siff
IPC分类号： B64G1/64 , B64G1/00
CPC分类号： B64G1/645 , B64G1/402 , B64G1/641
摘要： A rail-captive sled for deploying payloads into outer space from a space launch vehicle. The sled is driven by a piston, powered by residual tank pressure from a tank native to the space launch vehicle. The rails are arranged parallel and adapted to a cross-sectional shape of a payload, such as small satellites or cubesats. The sled is a box frame sled with an adaptation to receive the piston. The rails may be attached to the residual pressure tank, with the piston in the residual pressure tank and aligned to the rails, or the pressure may be drawn from tank plumbing to a cylinder specific to the piston. The rails have a releasable closure to avoid unplanned egress of the payload, and the closure locks in the open position once released. The piston may be constrained by a direct constraint or by the closure via the payload.
摘要翻译：一个用于从空间运载火车部署有效载荷进入外层空间的铁路溜冰车。雪橇由活塞驱动，由来自本地的坦克的坦克压力提供给太空运载火箭。轨道平行布置并适应有效载荷的横截面形状，例如小卫星或立方体。雪橇是一个框架雪橇，适应于接收活塞。轨道可以附接到残余压力罐，活塞在残余压力罐中并与轨道对准，或者压力可以从罐管道抽吸到特定于活塞的气缸。轨道具有可释放的关闭，以避免有效载荷的计划外出口，并且闭合件一旦释放则锁定在打开位置。活塞可能受到直接约束或通过有效载荷的闭合约束。

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