专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

41. 发明申请

US20160376036A1 Modular Satellite Device Carrier Panel and a Modular Satellite 审中-公开
标题翻译：模块化卫星设备载体面板和模块化卫星
公开(公告)号：US20160376036A1
公开(公告)日：2016-12-29
申请号：US15191744
申请日：2016-06-24
申请人： Airbus DS GmbH
发明人： Guido Bose , Andrea Grasl
IPC分类号： B64G1/42 , H02B1/26 , H05K7/20 , H02B1/20
CPC分类号： B64G1/428 , B64G1/10 , B64G1/506 , B64G2001/1092 , H02B1/20 , H02B1/26 , H05K7/20336 , H05K7/20936
摘要： A modular satellite device carrier panel to accommodate electrical and/or electronic modules includes a base body, which is provided with at least one recess, into which at least one of the electrical and/or electronic modules can be installed. The base body includes devices for distributing electrical power to electrical power terminals provided in the area of the at least one recess for the at least one electrical and/or electronic module provided there.
摘要翻译：用于容纳电气和/或电子模块的模块化卫星设备载体面板包括基体，所述基体设置有至少一个凹部，至少一个电和/或电子模块可以安装在该凹部中。基体包括用于将电力分配给设置在至少一个凹部的区域中的电力端子的装置，用于设置在那里的至少一个电和/或电子模块。

42. 发明授权

US09382013B2 Variably extending heat transfer devices 有权
标题翻译：可变延伸的热传递装置
公开(公告)号：US09382013B2
公开(公告)日：2016-07-05
申请号：US13289307
申请日：2011-11-04
申请人： Thomas M. Murray , Edward Zielinski
发明人： Thomas M. Murray , Edward Zielinski
IPC分类号： F28F27/00 , B64D33/12 , B64G1/50
CPC分类号： B64D33/12 , B64G1/506
摘要： A heat transfer device for installation in a system having a heat generating element within the system away from which heat is to be transferred is described. The heat transfer device includes a heat pipe having a first portion, a second portion, and a working fluid contained within the heat pipe for transferring heat from the first portion to the second portion. The first portion is disposed in proximity with the heat generating element. The second portion is coupled to the first portion. At least part of the second portion is disposed outside the system to dissipate heat from the heat generating element and the second portion may be variably extended outside the system.
摘要翻译：描述了一种用于安装在系统内的热传递装置，其中系统内的发热元件远离热量被传送。传热装置包括：热管，其具有第一部分，第二部分和包含在热管内的工作流体，用于将热量从第一部分传递到第二部分。第一部分设置在发热元件附近。第二部分耦合到第一部分。第二部分的至少一部分设置在系统外部以散发来自发热元件的热量，并且第二部分可以可变地延伸到系统外部。

43. 发明申请

US20150069187A1 HOSTED INSTRUMENT RADIATOR SYSTEM 审中-公开
标题翻译：主控放大器系统
公开(公告)号：US20150069187A1
公开(公告)日：2015-03-12
申请号：US14463538
申请日：2014-08-19
申请人： Lockheed Martin Corporation
发明人： Douglas V. MCKINNON , David J. HENTOSH , Russell J. MOSSO
IPC分类号： B64G1/50 , B64G1/10
CPC分类号： B64G1/50 , B64G1/503 , B64G1/506 , B64G1/66
摘要： An instrument mounting system for a geosynchronous host satellite provides independent heat rejection capability for a hosted instrument. The system may include an instrument mounting structure that is thermally coupled to a radiator component via heat pipes that may include one or both of rigid and flexible elements. In some embodiments, the system is mounted on the hosting satellite so as to provide satellite components and the hosted instrument with a clear field of view while rejecting heat in one or both of the north and south directions. The system may also provide structural support for components of one or both of the hosted instrument or the hosting satellite.
摘要翻译：用于地球同步主机卫星的仪器安装系统为托管仪器提供独立的散热能力。该系统可以包括通过可以包括刚性和柔性元件中的一个或两个的热管热耦合到散热器部件的仪器安装结构。在一些实施例中，系统安装在主机卫星上，以便在卫星组件和托管的仪器中提供清晰的视场，同时在北向和南方的一个或两个方向上排除热量。该系统还可以为托管的仪器或托管卫星中的一个或两个的组件提供结构支持。

44. 发明申请

US20150048209A1 Structures with Internal Microstructures to Provide Multifunctional Capabilities 审中-公开
标题翻译：具有内部微结构以提供多功能能力的结构
公开(公告)号：US20150048209A1
公开(公告)日：2015-02-19
申请号：US14462541
申请日：2014-08-18
申请人： Robert Hoyt , Jonathan Wrobel , Jesse Cushing , Mark Jaster , Nestor Voronka , Scott Frank , Jeffrey Slostad , Leonid Paritsky
发明人： Robert Hoyt , Jonathan Wrobel , Jesse Cushing , Mark Jaster , Nestor Voronka , Scott Frank , Jeffrey Slostad , Leonid Paritsky
IPC分类号： B64G1/54 , B22F7/02 , B22F3/105 , B64G1/22 , B29C67/00
CPC分类号： B22F3/1055 , B22F7/008 , B22F7/02 , B22F2302/45 , B22F2998/10 , B23K15/0086 , B23K2103/172 , B23K2103/18 , B23K2103/42 , B29C64/106 , B29C64/112 , B29C64/153 , B29L2031/3002 , B29L2031/3097 , B33Y10/00 , B33Y80/00 , B64G1/506 , B64G1/54 , B64G1/58 , G21F1/12 , Y02P10/295
摘要： A structural spacecraft component comprising internal microstructure; wherein said microstructure comprises a plurality of parallel layers and a plurality of spacers that connect adjacent parallel layers; wherein said structural spacecraft component is a product of an additive manufacturing process.
摘要翻译：包括内部微结构的结构航天器部件; 其中所述微结构包括多个平行层和连接相邻平行层的多个间隔物; 其中所述结构航天器部件是添加剂制造过程的产物。

45. 发明申请

US20130068891A1 Structural Panel for a Satellite, with Integrated Heat Exchangers 审中-公开
标题翻译：卫星结构面板，集成热交换器
公开(公告)号：US20130068891A1
公开(公告)日：2013-03-21
申请号：US13423016
申请日：2012-03-16
申请人： Julien HUGON , Thierry DARGENT
发明人： Julien HUGON , Thierry DARGENT
IPC分类号： B64G1/58
CPC分类号： B64G1/503 , B64G1/1007 , B64G1/506 , F28D15/0233 , F28D15/0266 , F28D15/0275 , F28D2021/0021
摘要： A structural panel for a satellite comprises an outer skin intended to be outside the satellite, a core comprising at least one integrated heat pipe mounted in fixed contact with said outer skin, and an inner skin intended to be inside the satellite, said structural panel being equipped with generic heat exchangers which are adapted to be associated with a heat control circuit using the circulation of a liquid coolant, said circuit being situated outside the panel.
摘要翻译：用于卫星的结构面板包括旨在在卫星外部的外皮，芯包括与所述外皮固定接触地安装的至少一个集成热管和旨在在卫星内部的内皮，所述结构面板是配备有适于与使用液体冷却剂的循环的热控制回路相关联的通用热交换器，所述电路位于面板外部。

46. 发明授权

US08240612B2 Device for controlling the heat flows in a spacecraft and spacecraft equipped with such a device 有权
标题翻译：用于控制配备有这种装置的航天器和航天器中的热流的装置
公开(公告)号：US08240612B2
公开(公告)日：2012-08-14
申请号：US12440575
申请日：2007-09-11
申请人： Laurence Jondeau , Christian Flemin , Fabrice Mena
发明人： Laurence Jondeau , Christian Flemin , Fabrice Mena
IPC分类号： B64G1/52
CPC分类号： B64G1/50 , B64G1/503 , B64G1/506 , F28D15/0275 , F28D2021/0029
摘要： A device for controlling heat flow in a spacecraft which always has the same face facing towards the earth, a pair of mutually parallel opposed North and South faces perpendicular to the North-South axis of the earth and two pairs of mutually parallel opposed East/West and Earth/Anti-earth faces, heat-dissipating or -transmitting equipment being provided on the internal walls of the North and South faces, this device comprising a plurality of heat pipes connecting the North and South faces of said craft to another pair of opposed faces of said craft and forming a heat-pipe loop in thermal-conduction contact with one another.
摘要翻译：一种用于控制航天器中热流的装置，它们始终具有面向地球的相同面，一对相互平行的相对的南北面垂直于地球的南北轴线和两对相互平行的相对的东/西和地面/防尘面，散热或发射设备设置在北面和南面的内壁上，该装置包括将所述工艺的北面和南面连接到另一对相对的一对相对的多个热管并且形成彼此热传导接触的热管回路。

47. 发明授权

US07980514B2 Solar array momentum control 有权
标题翻译：太阳能阵列动量控制
公开(公告)号：US07980514B2
公开(公告)日：2011-07-19
申请号：US12048981
申请日：2008-03-14
申请人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
发明人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
IPC分类号： B64G1/24 , B64G1/44
CPC分类号： B64G1/506 , B64G1/283 , B64G1/285 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , Y10S136/292
摘要： One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.
摘要翻译：本发明的一个实施例包括一个航天器。宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩的太阳能电池部分和太阳能电池部分阵列的失活部分。

48. 发明授权

US07640840B2 Automated launch mating system 有权
标题翻译：自动发射交配系统
公开(公告)号：US07640840B2
公开(公告)日：2010-01-05
申请号：US12013285
申请日：2008-01-11
申请人： Thorin A. Rogers , Robert J. Atmur , Ron A. Kubinski
发明人： Thorin A. Rogers , Robert J. Atmur , Ron A. Kubinski
IPC分类号： F41F3/055
CPC分类号： F41F3/052 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/506 , B64G1/66 , F41F3/055
摘要： In one embodiment, an automated system for mating a launch device to a launch platform may include a launch platform having a first electrical connector, and a interface member attached to the launch device. The interface member may include a second electrical connector configured to automatically couple to the first electrical connector of the launch platform.
摘要翻译：在一个实施例中，用于将发射装置与发射平台配合的自动化系统可以包括具有第一电连接器的发射平台和连接到发射装置的接口部件。接口构件可以包括被配置为自动地耦合到发射平台的第一电连接器的第二电连接器。

49. 发明申请

US20090230250A1 SOLAR ARRAY MOMENTUM CONTROL 有权
标题翻译：太阳能阵列控制
公开(公告)号：US20090230250A1
公开(公告)日：2009-09-17
申请号：US12048981
申请日：2008-03-14
申请人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
发明人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
IPC分类号： B64G1/44
CPC分类号： B64G1/506 , B64G1/283 , B64G1/285 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , Y10S136/292
摘要： One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.
摘要翻译：本发明的一个实施例包括一个航天器。宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩的太阳能电池部分和太阳能电池部分阵列的失活部分。

50. 发明申请

US20090220700A1 Coating Composition And Method Of Application 审中-公开
标题翻译：涂料组合物及其应用方法
公开(公告)号：US20090220700A1
公开(公告)日：2009-09-03
申请号：US12039202
申请日：2008-02-28
申请人： Carl Peres
发明人： Carl Peres
IPC分类号： C09D175/04 , C08L75/04 , B05D1/36
CPC分类号： B64G1/506 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , C08G18/10 , C08G18/73 , C09D175/04
摘要： A coating composition is provided to improve the integrity of paint coatings applied to a substrate. The composition comprises a polyurethane uniformly mixed with a polysulfide. The disclosed subject matter may be utilized as an aircraft substrate is provided with a primer coating applied. The coating composition is then applied over the primer coating. Lastly, a top paint coating is applied over the coating composition to complete the layering process. The coating composition provides the top paint coat with the ability to flex and deflect when stresses are applied by adverse environmental conditions.
摘要翻译：提供涂料组合物以改善施加到基材上的涂料涂料的完整性。该组合物包含与多硫化物均匀混合的聚氨酯。所公开的主题可以用作飞行器基板，其具有施加的底漆涂层。然后将涂料组合物施涂在底漆涂层上。最后，在涂料组合物上施加顶涂料以完成分层过程。涂层组合物使得顶涂层具有在不利环境条件下施加应力时弯曲和偏转的能力。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式