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41. 发明申请

US20180202394A1 ASSEMBLY INCLUDING AFT END IGNITER FOR ROCKET MOTOR 审中-公开
公开(公告)号：US20180202394A1
公开(公告)日：2018-07-19
申请号：US15870525
申请日：2018-01-12
申请人： AGENCY FOR DEFENSE DEVELOPMENT
发明人： Sangyoun LEE , Seunggyo JANG , Hyonam LEE
IPC分类号： F02K9/95 , F02K9/08 , F02K9/97
CPC分类号： F02K9/95 , B64G1/403 , F02K9/08 , F02K9/97 , F42B3/04 , F42C19/0819
摘要： The present invention relates to an igniter assembly, including a blast tube provided with a supporting part formed in a cylindrical shape, and an aft-closure part having front and rear sides through which igniter combustion gas is emitted, an igniter disposed adjacent to the rear side of the aft-closure part and storing ignition pellet therein, and a blast tube stopper formed in a shape surrounding the supporting part, accommodating the igniter, and coupled to the rear side of the aft-closure part, wherein the aft-closure part includes a plurality of holes through which igniter combustion gas is emitted.

42. 发明申请

US20180037340A1 SATELLITE MANAGEMENT SYSTEM COMPRISING A PROPULSION SYSTEM HAVING INDIVIDUALLY SELECTABLE MOTORS 审中-公开
公开(公告)号：US20180037340A1
公开(公告)日：2018-02-08
申请号：US15784823
申请日：2017-10-16
申请人： Pacific Scientific Energetic Materials Company
发明人： Steven NELSON , Richard HENDERSON , Bret OMSBERG
IPC分类号： B64G1/10 , G08G5/00 , F02K9/10 , B64G3/00
CPC分类号： B64G1/1014 , B64G1/26 , B64G1/403 , B64G3/00 , F02K9/10 , F02K9/24 , F02K9/763 , F02K9/95 , G08G5/0047 , G08G5/0095
摘要： A control system for a satellite comprises a power source and control system, a propulsion system having individually selectable solid fuel motors, a communication interface and an attitude determination and control system (ADCS). The ADCS receives power from the power source and control system and further receives desired orbital or positional instructions via the communication interface. Based on the desired orbital or position instructions, the ADCS generates and provides commands to the propulsion system. In turn, the propulsion system selects and fires one or more motors of the individually selectable solid fuel motors responsive to the commands received from the ADCS. A satellite may comprise the disclosed satellite control system as well as attitude control components and/or sensor components operatively connected to the satellite control system.

43. 发明申请

US20170313443A1 SPACE SHUTTLE ORBITER AND RETURN SYSTEM 审中-公开
公开(公告)号：US20170313443A1
公开(公告)日：2017-11-02
申请号：US15451001
申请日：2017-03-06
申请人： Biosphere Aerospace LLC
发明人： Elie Helou, JR.
IPC分类号： B64G1/00 , B64G1/62 , B64G1/58 , B64G1/40 , B64G1/22 , B64G1/14 , B64G1/10
CPC分类号： B64G1/005 , B64G1/002 , B64G1/14 , B64G1/22 , B64G1/222 , B64G1/40 , B64G1/401 , B64G1/403 , B64G1/58 , B64G1/62 , B64G2001/1092
摘要： A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

44. 发明申请

US20170283095A1 SATELLITE WITH INTEGRAL THRUSTERS 审中-公开
公开(公告)号：US20170283095A1
公开(公告)日：2017-10-05
申请号：US15091008
申请日：2016-04-05
申请人： Raytheon Company
发明人： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC分类号： B64G1/40 , F02K7/00 , F02K1/00 , B64G1/26
CPC分类号： B64G1/403 , B33Y70/00 , B33Y80/00 , B64G1/10 , B64G1/26 , F02K9/80 , F02K99/00 , F05D2210/20 , F05D2230/31
摘要： A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

45. 发明授权

US09751643B2 Device for moving or removing artificial satellites 有权
公开(公告)号：US09751643B2
公开(公告)日：2017-09-05
申请号：US14232869
申请日：2012-07-18
申请人： Luca Rossettini , Giuseppe Jussef Tussiwand , Renato Panesi , Thomas Panozzo
发明人： Luca Rossettini , Giuseppe Jussef Tussiwand , Renato Panesi , Thomas Panozzo
IPC分类号： B64G1/40 , B64G1/24 , B64G1/26 , B64G1/64 , B64G1/10
CPC分类号： B64G1/242 , B64G1/10 , B64G1/26 , B64G1/40 , B64G1/403 , B64G1/64
摘要： A device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting said satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the control means; receiver for receiving control signals operatively connected with the control means; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.

46. 发明授权

US09586700B2 Space shuttle orbiter and return system 有权
标题翻译：航天飞机轨道和返航系统
公开(公告)号：US09586700B2
公开(公告)日：2017-03-07
申请号：US14736782
申请日：2015-06-11
申请人： Biosphere Aerospace LLC
发明人： Elie Helou, Jr.
IPC分类号： B64G1/14 , B64G1/00 , B64G1/22 , B64G1/40 , B64G1/58 , B64G1/62 , B64G1/10
CPC分类号： B64G1/005 , B64G1/002 , B64G1/14 , B64G1/22 , B64G1/222 , B64G1/40 , B64G1/401 , B64G1/403 , B64G1/58 , B64G1/62 , B64G2001/1092
摘要： A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.
摘要翻译：发射系统包括鼻部，其包括鼻部联接表面，尾部包括面向鼻部联接表面的尾部联接表面和连接鼻部和尾部的杆。桅杆被配置成展开和缩回，以在彼此距离的距离范围内移动鼻部和尾部。在缩回状态下，鼻部和尾部部分在结构上在鼻部和尾部联接表面处彼此耦合，或者结构上耦合到位于鼻部和尾部之间的至少一个集成模块。

47. 发明申请

US20170025992A1 Mirrors Transparent to Specific Regions of the Electromagnetic Spectrum 审中-公开
标题翻译：反射镜对电磁谱的特定区域是透明的
公开(公告)号：US20170025992A1
公开(公告)日：2017-01-26
申请号：US15217690
申请日：2016-07-22
申请人： California Institute of Technology
发明人： Harry A. Atwater , Sergio Pellegrino , Seyed Ali Hajimiri , Emily C. Warmann
IPC分类号： H02S40/22 , B64G1/10 , B64G1/44
CPC分类号： H02S40/22 , B64G1/1085 , B64G1/401 , B64G1/403 , B64G1/405 , B64G1/406 , B64G1/407 , B64G1/428 , B64G1/443 , B64G1/66 , H01L31/0547 , H02S10/00 , H02S30/20 , Y02E10/52
摘要： Systems and methods in accordance with various embodiments of the invention implement mirrors that are more transparent to specific regions of the electromagnetic spectrum (e.g. the microwave region of the electromagnetic spectrum) relative to conventional metallic mirrors (e.g. mirrors made form aluminum or silver). In one embodiment, a space-based solar power system includes: a photovoltaic material; and a mirror that is—relative to a 10 μm thick sheet of aluminum—more transparent to at least one of a substantial portion of the microwave region of the electromagnetic spectrum and a substantial portion of the radio wave region of the electromagnetic spectrum; where the mirror is configured to focus incident visible light onto the photovoltaic material.
摘要翻译：根据本发明的各种实施例的系统和方法相对于传统的金属反射镜（例如由铝或银制成的反射镜）实现对电磁谱的特定区域（例如电磁光谱的微波区域）更透明的反射镜。在一个实施例中，空间太阳能发电系统包括：光伏材料; 以及相对于对电磁光谱的微波区域的主要部分和电磁光谱的无线电波区域的主要部分中的至少一个更透明的10μm厚的铝片的镜子; 其中镜被配置为将入射的可见光聚焦到光伏材料上。

48. 发明申请

US20160380580A1 Large-Scale Space-Based Solar Power Station: Multi-Scale Modular Space Power 审中-公开
标题翻译：大型空间太阳能发电站：多尺度模块化空间电力
公开(公告)号：US20160380580A1
公开(公告)日：2016-12-29
申请号：US14712783
申请日：2015-05-14
申请人： California Institute of Technology
发明人： Harry A. Atwater , Seyed Ali Hajimiri , Sergio Pellegrino , Behrooz Abiri , Florian Bohn , Jeffrey P. Bosco , Dennis Callahan , Emily C. Warmann , Manan Arya , Nicolas Lee , Melanie Delapierre
IPC分类号： H02S20/32 , B64G1/10 , H02J50/40 , H02J3/38 , H02J50/80 , H02S40/36 , H02J50/90 , H02S40/42 , B64G1/24 , H02J50/23
CPC分类号： H02J3/383 , B64G1/1085 , B64G1/222 , B64G1/283 , B64G1/286 , B64G1/288 , B64G1/36 , B64G1/401 , B64G1/403 , B64G1/405 , B64G1/406 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , B64G2700/66 , H01L31/042 , H02J50/23 , H02J50/80 , H02J50/90 , H02S10/40 , H02S20/25 , H02S20/30 , H02S30/10 , H02S30/20 , H02S40/30 , H02S40/36 , H02S40/42
摘要： A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Each solar power station includes a plurality of satellite modules. The plurality of satellite modules each include a plurality of modular power generation tiles including a photovoltaic solar radiation collector, a power transmitter and associated control electronics. The power transmitters can be coordinated as a phased array and the power generated by the phased array is transmitted to one or more power receivers to achieve remote wireless power generation and delivery. Each satellite module may be formed of a compactable structure capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station.
摘要翻译：提供了一种太空太阳能发电站，发电卫星模块和/或收集太阳辐射并发射使用其产生的电流产生的电力的方法。每个太阳能发电站包括多个卫星模块。多个卫星模块各自包括多个模块化发电瓦片，包括光伏太阳辐射收集器，功率发射器和相关联的控制电子器件。功率发射器可以作为相控阵进行协调，由相控阵产生的功率被传送到一个或多个功率接收器以实现远程无线发电和发射。每个卫星模块可以由可压缩的结构形成，该结构能够减少将卫星模块传送到空间太阳能发电站内的轨道形成所需的有效负载区域。

49. 发明授权

US09475591B2 Space launch apparatus 有权
标题翻译：太空发射装置
公开(公告)号：US09475591B2
公开(公告)日：2016-10-25
申请号：US14547543
申请日：2014-11-19
申请人： Arthur McKee Dula
发明人： Arthur McKee Dula
IPC分类号： B64G1/40 , B64G1/64 , B64G1/00
CPC分类号： B64G1/002 , B64G1/40 , B64G1/401 , B64G1/402 , B64G1/403 , B64G1/404 , B64G1/58 , B64G1/62 , B64G1/641 , B64G1/645 , B64G2005/005
摘要： A space launch apparatus comprising a solid triangular space frame constructed of a plurality of connected truss members that are attached to each other at nodes and are also attached to at least one rocket motor and to at least one payload whereby the force produced by the operation of the rocket motor is transferred to the payload and aerodynamic and vibration loads are distributed through the truss members and their nodes.
摘要翻译：一种空间发射装置，包括由多个连接的桁架构件构成的实心三角形空间框架，所述多个连接的桁架构件在节点处彼此连接并且还附接到至少一个火箭发动机和至少一个有效载荷，由此由操作产生的力火箭发动机转移到有效载荷，空气动力学和振动载荷通过桁架构件及其节点分布。

50. 发明申请

US20160052649A1 FAIL-SAFE COMMAND DESTRUCT SYSTEM 审中-公开
标题翻译：失败的安全命令制度
公开(公告)号：US20160052649A1
公开(公告)日：2016-02-25
申请号：US14824578
申请日：2015-08-12
申请人： Ventions, LLC
发明人： Adam P. London
IPC分类号： B64G1/24 , B64G1/52 , B64G1/00
CPC分类号： B64G1/52 , B64G1/002 , B64G1/401 , B64G1/402 , B64G1/403 , B64G1/428
摘要： A fail safe command destruct system for a multi-stage rocket comprising a first stage flight termination system and an upper stage command enable system. The flight termination system has the added feature that the same battery is the sole power source to the flight termination receiver and to a normally off flight inhibitor that requires power to permit engine operation. The command enable system has a normally inhibiting flight inhibitor that requires power to permit engine operation. The same battery is the sole source of power to the command enable receiver and the flight inhibitor such that battery failure prevents engine ignition. Lack of a command from outside the rocket to the command enable receiver also prevents engine ignition.
摘要翻译：一种用于多级火箭的故障安全命令破坏系统，包括第一级飞行终止系统和上级命令使能系统。飞行终点系统具有附加功能，即相同的电池是飞行终端接收机的唯一电源，以及需要电力允许发动机运行的正常关闭飞行抑制器。命令启用系统具有通常禁止的飞行抑制器，其需要电力来允许发动机操作。相同的电池是命令使能接收器和防止飞行器的唯一电源，使得电池故障防止发动机点火。从火箭外部指挥命令使能接收器也防止发动机点火。

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