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1. 发明申请

US20160376001A1 VEHICLE INCLUDING A TETRAHEDRAL BODY OR CHASSIS 审中-公开
标题翻译：车辆包括四面体或底盘
公开(公告)号：US20160376001A1
公开(公告)日：2016-12-29
申请号：US14631156
申请日：2015-02-25
申请人： Robin Felix
发明人： Robin Felix
IPC分类号： B64C39/00 , B64G1/42 , B63G8/08 , B64C11/46 , B63G8/04 , B64G1/40 , B64C1/06
CPC分类号： B64C39/00 , B63B2241/16 , B63G8/001 , B64C1/06 , B64C11/001 , B64C11/46 , B64C39/024 , B64C2001/0045 , B64G1/10 , B64G1/283 , B64G1/32 , B64G1/40 , B64G1/425 , B64G1/426 , B64G1/446
摘要： A vehicle constructed in the shape of tetrahedral. The vehicle may be an aircraft, a space-craft, a sub-surface vehicle, or an unmanned drone. A tetrahedral body component is one of: a regular tetrahedron, an extended tetrahedron, a foreshortened tetrahedron, a tapered tetrahedron, and a truncated tetrahedron. A means for propulsion is mounted to at least one of the faces of the tetrahedral body component. The means for propulsion may include a turbine engine, a water jet, a gas jet, or electromagnetic propulsion. In another embodiment, the means for propulsion include an engine and a propeller. The engine block is mounted internal to the tetrahedral body component, and is located at the intersection of a tetrahedral shape with a cube shape. The engine block is mounted to the tetrahedral body component by struts perpendicular to the faces of the engine block.
摘要翻译：一种四面体形状的车辆。车辆可以是飞机，太空飞船，地面车辆或无人驾驶飞机。四面体组分是以下之一：正四面体，延伸四面体，缩短四面体，锥形四面体和截顶四面体。用于推进的装置安装在四面体部件的至少一个面上。用于推进的装置可以包括涡轮发动机，水射流，气体射流或电磁推进。在另一个实施例中，用于推进的装置包括发动机和螺旋桨。发动机缸体安装在四面体组件内部，位于四面体形状与立方体形状的交点处。发动机缸体通过垂直于发动机缸体表面的支柱安装在四面体部件上。

2. 发明申请

US20130105747A1 METHODS FOR TENSIONING A MEMBRANE AND APPARATUSES THEREOF 审中-公开
标题翻译：用于张紧膜的方法及其装置
公开(公告)号：US20130105747A1
公开(公告)日：2013-05-02
申请号：US13658509
申请日：2012-10-23
申请人： Scot C. GALLIHER
发明人： Scot C. GALLIHER
IPC分类号： B66F3/00
CPC分类号： B64G1/446 , B64G1/222 , B64G1/407
摘要： A method for tensioning a membrane includes affixing a first wire to a first portion of the membrane and affixing a second wire to a second portion of the membrane. The membrane is tensioned between the first wire and the second wire by applying a first current in a first direction through the first wire and applying a second current in a second direction through the second wire, so that repulsive magnetic fields are generated between the first wire and the second wire.
摘要翻译：用于张紧膜的方法包括将第一线固定到膜的第一部分并且将第二线固定到膜的第二部分。通过在第一方向上施加第一电流并通过第一线施加第一电流并通过第二线沿第二方向施加第二电流，使膜在第一线和第二线之间张紧，使得在第一线之间产生排斥磁场和第二根线。

3. 发明授权

US08127758B2 Solar-thermal fluid heating for aerospace platforms 有权
标题翻译：用于航空航天平台的太阳能热液加热
公开(公告)号：US08127758B2
公开(公告)日：2012-03-06
申请号：US12058650
申请日：2008-03-28
申请人： Shailesh Atreya , Michael F. Stoia , Tina R. Stoia , Russell K. Jones
发明人： Shailesh Atreya , Michael F. Stoia , Tina R. Stoia , Russell K. Jones
IPC分类号： F24J2/38 , F24J2/04 , C25B9/00
CPC分类号： C25B1/04 , B64D13/00 , B64D2013/0677 , B64D2041/005 , B64D2211/00 , B64G1/42 , B64G1/44 , B64G1/446 , H01M16/003 , Y02E60/366 , Y02E70/10 , Y02P20/134 , Y02T50/55 , Y02T50/56 , Y02T90/36
摘要： An aerospace platform includes a structure having a cavity and a light-transmissive portion that exposes the cavity to sunlight. The aerospace platform further includes a fluid heating system. The fluid heating system includes a fluid-carrying, thermally absorptive structure within the cavity, and a solar collector for collecting light transmitted through the light-transmissive portion and focusing the collected light onto the absorptive structure. The thermally absorptive structure has a high surface absorptivity that retains thermal energy when exposed to solar irradiance and heats fluid contained therein.
摘要翻译：航空航天平台包括具有空腔和将空腔暴露于阳光的透光部分的结构。航空航天平台还包括流体加热系统。流体加热系统包括空腔内的流体携带的热吸收结构，以及太阳能收集器，用于收集透过透光部分的光并将收集的光聚焦到吸收结构上。热吸收结构具有高的表面吸收性，当暴露于太阳辐照并且加热其中所含的流体时，其保持热能。

4. 发明申请

US20110278417A1 System And Methods For Smoothly Inverting One Or More Faces Of A Cubical Device 有权
标题翻译：用于平滑倒置立体装置的一个或多个面的系统和方法
公开(公告)号：US20110278417A1
公开(公告)日：2011-11-17
申请号：US13126858
申请日：2009-10-29
申请人： Solomon G. Diamond
发明人： Solomon G. Diamond
IPC分类号： F16M13/00 , F16H1/14 , F16C11/04
CPC分类号： A63H33/003 , A61B34/30 , B64G1/222 , B64G1/443 , B64G1/446 , B64G1/58 , Y10T74/19665 , Y10T403/32008 , Y10T403/70
摘要： A system and method for inverting a cubical device 100 that inverts one or more faces of the cubical device 100 in a single fluid motion. In an embodiment, the cube faces are split in two face piece assemblies 210, in an alternative embodiment faces have only one invertible section 802, 702. The face piece assemblies 210 are initially held by cubical device 100 with a particular side facing inward. Operating the cubical device 100 causes one or more face piece assemblies 210, 803 to expand out from the center point of the cubical device 100, to rotate, and then collapse inward until cubical device 100 is reformed with the particular side of the faces in an outward-facing orientation. The joints, links and gears in the mechanism restrict the degrees of freedom to one such that the entire inversion movement is coupled. Multiple applications are proposed for the device, and embodiments having actuators for driving the inversion are disclosed.
摘要翻译：一种用于反转立体装置100的系统和方法，其以单个流体运动反转立方体装置100的一个或多个面。在一个实施例中，立方体面分成两个面件组件210，在替代实施例中，面仅具有一个可翻转部分802,702。面件组件210最初由立方体装置100保持，其特定侧面向内。操作立方体装置100使得一个或多个面件组件210,803从立方体装置100的中心点向外扩展，以旋转，然后向内折叠，直到立方体装置100与面的特定侧面重新形成向外朝向。机构中的接头，连杆和齿轮将自由度限制为使得整个反转运动耦合的自由度。提出了多种用途的装置，并且公开了具有用于驱动反转的致动器的实施例。

5. 发明授权

US07559509B1 Large cryogenic tank logistics for in-space vehicles 失效
标题翻译：空间车辆的大型低温坦克物流
公开(公告)号：US07559509B1
公开(公告)日：2009-07-14
申请号：US11767459
申请日：2007-06-22
申请人： Walter P. Kistler , Thomas C. Taylor , Robert A. Citron
发明人： Walter P. Kistler , Thomas C. Taylor , Robert A. Citron
IPC分类号： B64G1/00 , B64G1/64
CPC分类号： B64G1/002 , B64G1/007 , B64G1/443 , B64G1/446 , B64G1/62 , B64G1/641 , B64G1/645 , B64G1/646
摘要： An aerospace frame accommodates propellant tanks for facilitating propellant operations in space. The frame includes at least two plates for supporting the propellant tanks; at least one brace supporting the plates; and a cavity between two plates that accommodates a removable propellant tank.
摘要翻译：航空航天框架可容纳推进剂罐，用于促进太空中的推进剂操作。框架包括用于支撑推进剂罐的至少两个板; 支撑板的至少一个支架; 以及容纳可拆卸推进剂罐的两个板之间的空腔。

6. 发明申请

US20040045276A1 Thruster device responsive to solar radiation and associated methods 失效
标题翻译：响应太阳辐射的推进装置及相关方法
公开(公告)号：US20040045276A1
公开(公告)日：2004-03-11
申请号：US10640129
申请日：2003-08-13
申请人： The Boeing Company
发明人： Patrick E. Frye , Joseph P. Carroll , James M. Shoji
IPC分类号： F28D003/00 , A23C003/04
CPC分类号： F03H99/00 , B64G1/401 , B64G1/402 , B64G1/427 , B64G1/446 , F02K9/42 , F05D2230/11 , F05D2250/25 , F05D2260/20 , F05D2300/13 , F24S20/20 , Y02E10/41 , Y10T29/49346 , Y10T29/49355 , Y10T29/49995
摘要： A thruster device and associated methods are provided. The thruster device comprises a frustoconical inner layer and a frustoconical outer layer that surrounds the inner layer such that the inner and outer layers cooperate to define a spiral flow passage therebetween. An outlet, such as a nozzle, is attached to an exit end of the thruster device such that the outlet is in fluid communication with the spiral flow passage. In one embodiment, the thruster device includes an end flow cap that is also attached to the exit end and establishes the fluid communication between the spiral flow passage and the outlet. The end flow cap includes at least one channel for directing the propellant from the spiral flow passage to the outlet. The design of the thruster device allows the frustoconical inner and outer layers to be assembled without galling or damaging the spiral flow passage.
摘要翻译：提供推进器装置和相关方法。推进器装置包括截头圆锥形内层和围绕内层的截头圆锥形外层，使得内层和外层协作以在其间限定螺旋流动通道。诸如喷嘴的出口附接到推进器装置的出口端，使得出口与螺旋流动通道流体连通。在一个实施例中，推进器装置包括端部流动帽，其也附接到出口端并建立螺旋流动通道和出口之间的流体连通。末端流动帽包括用于将推进剂从螺旋流动通道引导到出口的至少一个通道。推进器装置的设计允许截头圆锥形内层和外层组装而不会磨损或破坏螺旋流动通道。

7. 发明申请

US20020170284A1 Thruster device responsive to solar radiation and associated methods 失效
标题翻译：响应太阳辐射的推进装置及相关方法
公开(公告)号：US20020170284A1
公开(公告)日：2002-11-21
申请号：US10097523
申请日：2002-03-14
申请人： The Boeing Company
发明人： Patrick E. Frye , Joseph P. Carroll , James M. Shoji
IPC分类号： F03H005/00
CPC分类号： F03H99/00 , B64G1/401 , B64G1/402 , B64G1/427 , B64G1/446 , F02K9/42 , F05D2230/11 , F05D2250/25 , F05D2260/20 , F05D2300/13 , F24S20/20 , Y02E10/41 , Y10T29/49346 , Y10T29/49355 , Y10T29/49995
摘要： A thruster device and associated methods are provided. The thruster device comprises a frustoconical inner layer and a frustoconical outer layer that surrounds the inner layer such that the inner and outer layers cooperate to define a spiral flow passage therebetween. An outlet, such as a nozzle, is attached to an exit end of the thruster device such that the outlet is in fluid communication with the spiral flow passage. In one embodiment, the thruster device includes an end flow cap that is also attached to the exit end and establishes the fluid communication between the spiral flow passage and the outlet. The end flow cap includes at least one channel for directing the propellant from the spiral flow passage to the outlet. The design of the thruster device allows the frustoconical inner and outer layers to be assembled without galling or damaging the spiral flow passage.
摘要翻译：提供推进器装置和相关方法。推进器装置包括截头圆锥形内层和围绕内层的截头圆锥形外层，使得内层和外层协作以在其间限定螺旋流动通道。诸如喷嘴的出口附接到推进器装置的出口端，使得出口与螺旋流动通道流体连通。在一个实施例中，推进器装置包括端部流动帽，其也附接到出口端并建立螺旋流动通道和出口之间的流体连通。末端流动帽包括用于将推进剂从螺旋流动通道引导到出口的至少一个通道。推进器装置的设计允许截头圆锥形内层和外层组装而不会磨损或破坏螺旋流动通道。

8. 发明授权

US5459996A Hybrid solar rocket utilizing thermal storage for propulsion and electrical power 失效
标题翻译：混合太阳能火箭利用热存储推进和电力
公开(公告)号：US5459996A
公开(公告)日：1995-10-24
申请号：US297678
申请日：1994-08-29
申请人： John D. Malloy, III , Richard F. Rochow , James B. Inman
发明人： John D. Malloy, III , Richard F. Rochow , James B. Inman
IPC分类号： B64G1/40 , B64G1/44 , F02K99/00 , F24S20/20 , F24S23/70 , F02G1/00
CPC分类号： F24J2/34 , B64G1/409 , B64G1/446 , F24J2/07 , F24J2/10 , F24J2/51 , B64G1/401 , F02G2254/30 , F24J2002/4605 , Y02E10/41
摘要： A solar rocket for propelling and powering the electronics of a spacecraft includes a black body cavity of thermal storage material. Propulsion tubes and a connected nozzle axially extend through the black body cavity for burning propellant in order to provide thrust for the rocket. An insulation sleeve is removably located at the outer periphery of the cavity of thermal storage material. Energy conversion diodes surround the insulation sleeve. The thermal storage material, the insulation sleeve and the energy conversion diodes form a receiver. The receiver has a pair of spaced apart holes therethrough which lead into an interior space of the black body cavity in order to receive sunlight. A mirror assembly is located near each hole of the receiver for harnessing sunlight and providing radiant energy through the holes into the internal space of the black body cavity.
摘要翻译：用于推进和驱动航天器电子装置的太阳能火箭包括一个黑体腔的蓄热材料。推进管和连接的喷嘴轴向延伸穿过黑体腔，用于燃烧推进剂，以便为火箭提供推力。绝热套可拆卸地位于蓄热材料空腔的外周。能量转换二极管围绕绝缘套管。蓄热材料，绝缘套管和能量转换二极管形成接收器。接收器具有穿过其中的一对间隔开的孔，其通向黑色体腔的内部空间以接收阳光。镜组件位于接收器的每个孔附近，用于利用阳光并通过孔向黑体腔的内部空间提供辐射能。

9. 发明授权

US3799144A Solar heat source and receiver system 失效
标题翻译：太阳能热源和接收系统
公开(公告)号：US3799144A
公开(公告)日：1974-03-26
申请号：US23662972
申请日：1972-03-21
申请人： US AIR FORCE
发明人： PETERSEN C , RAMSEY J , SCHMIDT R
IPC分类号： B64G1/22 , B64G1/44 , F02G1/044 , F24J2/12 , F24J2/54 , F25B27/00 , F24J3/02
CPC分类号： F24J2/12 , B64G1/226 , B64G1/446 , F02G1/0445 , F02G2250/18 , F02G2254/30 , F24J2/54 , F25B27/002 , Y02E10/42 , Y02E10/47
摘要： A system for collecting solar heat to meet high power heat requirements as in a Vuilleumier cycle cryogenic refrigerator, in space application. The system includes a short focal-length-todiameter ratio collector, a heat receiver having a convex surface attached to a heat pipe further containing a heat storage element which is connected to the use, i.e. a cryogenic refrigerator. The heat receiver utilizes a novel coating allowing the system to realize an effeciency in excess of fifty percent.
摘要翻译：用于收集太阳能热量以满足高功率热需求的系统，如在Vuilleumier循环低温冰箱中，在空间应用中。该系统包括短焦距直径比收集器，具有附接到热管的凸表面的热接收器，该热管还包含连接到使用的蓄热元件即低温冰箱。热接收器采用新颖的涂层，使系统实现超过百分之五十的效率。

10. 发明授权

US3379394A Optical solar energy converter 失效
标题翻译：光电太阳能转换器
公开(公告)号：US3379394A
公开(公告)日：1968-04-23
申请号：US40695064
申请日：1964-10-27
申请人： NAVY USA
发明人： BIALY KAROL J
IPC分类号： B64G1/44 , G02B6/04 , H01L31/00
CPC分类号： F24J2/067 , B64G1/446 , H01L31/00 , Y02E10/40 , Y10S136/292

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