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1. 发明申请

US20180306945A1 PASSIVE MICROWAVE SOUNDER FOR SATELLITE, HAVING FIXED REFLECTION PLATE 审中-公开
公开(公告)号：US20180306945A1
公开(公告)日：2018-10-25
申请号：US15779406
申请日：2016-11-24
申请人： Korea Aerospace Research Institute
发明人： Sang Burm RYU , Sang Gyu LEE , Sang-soon YONG , Eun-Su KANG , Seung Hoon LEE , Hyeon-Cheol LEE , Sungwook HONG
IPC分类号： G01W1/08 , B64G1/66 , H01Q3/02 , H01Q15/14 , B64G1/10
CPC分类号： G01W1/08 , B64G1/10 , B64G1/1021 , B64G1/105 , B64G1/22 , B64G1/66 , G01V3/12 , H01Q3/02 , H01Q15/14
摘要： The present invention relates to a passive microwave sounder for a satellite, having a fixed reflection plate. The passive microwave sounder for a satellite, having a fixed reflection plate includes: a motor 100 including a first rotary shaft 110 formed to extend in a progressing direction of a satellite; a first rotating reflection plate 200 forming a predetermined angle with respect to the ground surface of a nadir direction and having a first one-side surface 210 and a first other-side surface 220, the center of the first one-side surface 210 being coupled to and rotating with the first rotary shaft 110, such that the first one-side surface 210 and the first other-side surface 220 alternately face the ground surface, and the second other-side surface 220 reflecting incident electromagnetic waves; an auxiliary reflection part 300 reflecting the electromagnetic waves incident from the first other-side surface 220 to a predetermined position; a reception part 400 receiving the electromagnetic waves reflected from the auxiliary reflection part 300; and a fixed reflection plate 500 fixed above the first rotating reflection plate 200 at a predetermined angle with the ground surface and reflecting the electromagnetic waves to the first one-side surface 210 or the first other-side surface 220.

2. 发明授权

US09921099B1 Spherical occulter coronagraph cubesat 有权
公开(公告)号：US09921099B1
公开(公告)日：2018-03-20
申请号：US15254323
申请日：2016-09-01
申请人： The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
发明人： Joseph M. Davila , Douglas M. Rabin , Nelson Reginald , Qian Gong , Neerav Shah , Phillip C. Chamberlin
IPC分类号： G01J1/04 , G01J1/44 , B64G1/24 , B64G1/10 , G01J1/02 , G01J1/42 , G01S3/786 , B64G1/26 , B64G1/40
CPC分类号： G01J1/0437 , B64G1/105 , B64G1/26 , B64G1/406 , G01J1/0266 , G01J1/0271 , G01J1/4228 , G01J2001/4266 , G01J2001/446 , G01S3/7861 , G02B5/003
摘要： The present invention relates to a space-based instrument which provides continuous coronal electron temperature and velocity images, for a predetermined period of time, thereby improving the understanding of coronal evolution and how the solar wind and Coronal Mass Ejection transients evolve from the low solar atmosphere through the heliosphere for an entire solar rotation. Specifically, the present invention relates to using a 6U spherical occulter coronagraph CubeSat, and a relative navigational system (RNS) that controls the position of the spacecraft relative to the occulting sphere. The present invention innovatively deploys a free-flying spherical occulter, and after deployment, the actively controlled CubeSat will provide an inertial formation flying with the spherical occulter and Sun.

3. 发明申请

US20180058922A1 SPHERICAL OCCULTER CORONAGRAPH CUBESAT 审中-公开
公开(公告)号：US20180058922A1
公开(公告)日：2018-03-01
申请号：US15254323
申请日：2016-09-01
申请人： U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
发明人： JOSEPH M. DAVILA , DOUGLAS M. RABIN , NELSON REGINALD , QIAN GONG , NEERAV SHAH , PHILLIP C. CHAMBERLIN
IPC分类号： G01J1/04 , G01J1/02 , G01J1/44 , G01J1/42 , G01S3/786 , B64G1/10 , B64G1/26 , B64G1/40
CPC分类号： G01J1/0437 , B64G1/105 , B64G1/26 , B64G1/406 , G01J1/0266 , G01J1/0271 , G01J1/4228 , G01J2001/4266 , G01J2001/446 , G01S3/7861 , G02B5/003
摘要： The present invention relates to a space-based instrument which provides continuous coronal electron temperature and velocity images, for a predetermined period of time, thereby improving the understanding of coronal evolution and how the solar wind and Coronal Mass Ejection transients evolve from the low solar atmosphere through the heliosphere for an entire solar rotation. Specifically, the present invention relates to using a 6U spherical occulter coronagraph CubeSat, and a relative navigational system (RNS) that controls the position of the spacecraft relative to the occulting sphere. The present invention innovatively deploys a free-flying spherical occulter, and after deployment, the actively controlled CubeSat will provide an inertial formation flying with the spherical occulter and Sun.

4. 发明申请

US20150162656A1 ANTENNAS FOR SMALL SATELLITES 有权
标题翻译：天线小卫星
公开(公告)号：US20150162656A1
公开(公告)日：2015-06-11
申请号：US14407396
申请日：2013-06-11
申请人： UNIVERSITY OF FLORIDA RESEARCH FOUNDATION, INC.
发明人： Norman G. Fitz-Coy , Vivek Shirvante , Shawn Johnson , Kathryn Cason
IPC分类号： H01Q1/28 , B64G1/44 , B64G1/10 , B64G1/22
CPC分类号： H01Q1/288 , B64G1/105 , B64G1/222 , B64G1/443 , B64G1/66 , H01Q9/30 , H01Q19/106
摘要： Various embodiments of the present invention include assemblies and methods for utilizing antennas with high gain in small satellites. In one embodiment, a satellite comprising a payload configured for transmitting data is provided. The payload may include various components of the satellite, such as the attitude control system, electrical power system, and/or communication system. The satellite may be configured to communicate with one or more ground stations. The satellite includes a support structure comprising at least one deployable panel, wherein the support structure houses the payload. The satellite also includes at least one antenna coupled to the support structure, wherein the deployable panel is configured to cover the antenna in a non-deployed state and to expose the antenna in a deployed state.
摘要翻译：本发明的各种实施例包括在小型卫星中利用具有高增益的天线的组件和方法。在一个实施例中，提供了包括被配置为用于发送数据的有效载荷的卫星。有效载荷可以包括卫星的各种部件，例如姿态控制系统，电力系统和/或通信系统。卫星可以被配置为与一个或多个地面站通信。卫星包括支撑结构，该支撑结构包括至少一个可展开的面板，其中支撑结构容纳有效载荷。所述卫星还包括耦合到所述支撑结构的至少一个天线，其中所述可展开面板被配置为以非展开状态覆盖所述天线并且在展开状态下露出所述天线。

5. 发明申请

US20140017992A1 SATELLITE SYSTEM AND METHOD FOR CIRCUMPOLAR LATITUDES 有权
标题翻译：卫星系统和方法
公开(公告)号：US20140017992A1
公开(公告)日：2014-01-16
申请号：US13876678
申请日：2011-09-30
申请人： Andre E. Bigras , Peter Megyeri , Jack Rigley , Alireza Shoamanesh , Paul Ng , Surinder Pal Singh
发明人： Andre E. Bigras , Peter Megyeri , Jack Rigley , Alireza Shoamanesh , Paul Ng , Surinder Pal Singh
IPC分类号： H04B7/185
CPC分类号： H04B7/18519 , B64G1/002 , B64G1/007 , B64G1/1007 , B64G1/1021 , B64G1/105 , B64G1/1085 , B64G1/242 , B64G3/00 , B64G2001/643 , H04B7/195
摘要： The present invention relates to satellite systems and more particularly, to the provision of a satellite system for weather and climate monitoring, communications applications, and scientific research at higher latitudes, referred to as the circumpolar region and defined here as the area with latitudes greater than 60°, in either the northern hemisphere or the southern hemisphere. Contrary to the teachings in the art it has been discovered that a satellite system and method may be provided using satellites in 24 sidereal hour orbits (geosynchronous) with inclinations (70° to 90°), orbital planes, right ascensions and eccentricities (0.275-0.45) chosen to optimize coverage of a particular service area located at high latitudes. A constellation of two satellites can provide continuous coverage of the circumpolar region. The satellites in this orbit avoid most of the Van Allen Belts.
摘要翻译：本发明涉及卫星系统，更具体地说，涉及提供用于天气和气候监测，通信应用和高纬度地区的科学研究的卫星系统，被称为圆极区域，并且被定义为纬度大于 60°，在北半球或南半球。已经发现，可以使用具有倾斜（70°至90°），轨道平面，右上升和偏心（24°）的24个恒星小时轨道（地球同步）中的卫星来提供卫星系统和方法， 0.45），以优化位于高纬度地区的特定服务区域的覆盖范围。两颗卫星的星座可以提供连续的环形区域覆盖。这个轨道上的卫星避免了大部分的范艾伦带。

6. 发明授权

US07837340B2 Telescope multiple discrete segment primary mirror 失效
标题翻译：望远镜多个离散段主镜
公开(公告)号：US07837340B2
公开(公告)日：2010-11-23
申请号：US11782534
申请日：2007-07-24
申请人： George Watters
发明人： George Watters
IPC分类号： G02B5/08
CPC分类号： G02B7/183 , B64G1/105 , G02B17/002 , G02B17/0694 , G02B23/16 , G02B27/0018
摘要： A method and apparatus is configured for reflecting a beam of light incident at a primary mirror by rotating a first mirror segment to align a selected facet of the mirror segment to be generally orthogonal to the principal axis. The first mirror segment is translated in a motion parallel to the principal axis to a first position such that the mirrored segment at a facet comprising a mirror is brought into alignment with at least one second mirrored segment to form at a facet a first parabolic mirror. The incident beam of light is then reflected by collimating the first parabolic mirror by rotation and translation of the first mirror segment to strike a first secondary element.
摘要翻译：一种方法和装置被配置为通过旋转第一反射镜部分来反射入射在初级反射镜上的光束，以将反射镜分段的所选择的小平面与主轴垂直。第一镜片段以平行于主轴的运动平移到第一位置，使得包括镜的小面处的镜像片段与至少一个第二镜像片段对准，以在小平面处形成第一抛物面镜。然后通过使第一反射镜段的旋转和平移来对第一抛物面反射镜进行准直以撞击第一次要元件来反射入射光束。

7. 发明申请

US20090027789A1 TELESCOPE MULTIPLE DISCRETE SEGMENT PRIMARY MIRROR 失效
标题翻译：电话多重分段主要镜像
公开(公告)号：US20090027789A1
公开(公告)日：2009-01-29
申请号：US11782534
申请日：2007-07-24
申请人： George Watters
发明人： George Watters
IPC分类号： G02B5/08
CPC分类号： G02B7/183 , B64G1/105 , G02B17/002 , G02B17/0694 , G02B23/16 , G02B27/0018
摘要： A method and apparatus is configured for reflecting a beam of light incident at a primary mirror by rotating a first mirror segment to align a selected facet of the mirror segment to be generally orthogonal to the principal axis. The first mirror segment is translated in a motion parallel to the principal axis to a first position such that the mirrored segment at a facet comprising a mirror is brought into alignment with at least one second mirrored segment to form at a facet a first parabolic mirror. The incident beam of light is then reflected by collimating the first parabolic mirror by rotation and translation of the first mirror segment to strike a first secondary element.
摘要翻译：一种方法和装置被配置为通过旋转第一反射镜部分来反射入射在初级反射镜上的光束，以将反射镜分段的所选择的小平面与主轴垂直。第一镜片段以平行于主轴的运动平移到第一位置，使得包括镜的小面处的镜像片段与至少一个第二镜像片段对准，以在小平面处形成第一抛物面镜。然后通过使第一反射镜段的旋转和平移来对第一抛物面反射镜进行准直以撞击第一次要元件来反射入射光束。

8. 发明申请

US20030089821A1 Payload delivery system 审中-公开
公开(公告)号：US20030089821A1
公开(公告)日：2003-05-15
申请号：US10323512
申请日：2002-12-18
发明人： Carlos T. Miralles , Bart D. Hibbs
IPC分类号： B64C003/56
CPC分类号： B64G1/222 , B64C1/30 , B64C3/56 , B64C39/024 , B64C2201/042 , B64C2201/082 , B64C2201/102 , B64C2201/126 , B64C2201/127 , B64C2201/128 , B64C2201/141 , B64C2201/146 , B64C2201/148 , B64C2201/185 , B64C2201/203 , B64G1/105 , B64G1/62
摘要： Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

9. 发明授权

US06409125B1 Positioning system for a measuring instrument on a satellite 失效
标题翻译：用于卫星上测量仪器的定位系统
公开(公告)号：US06409125B1
公开(公告)日：2002-06-25
申请号：US09568006
申请日：2000-05-10
申请人： Hartmut Jörck
发明人： Hartmut Jörck
IPC分类号： B64G166
CPC分类号： B64G1/105 , B64G1/1021 , B64G1/242 , B64G1/32 , B64G1/36 , B64G1/66 , B64G2001/1057
摘要： Positioning system for a high-precision measuring instrument (1) in a support structure (2) of a satellite, in which the measuring instrument (1) can be moved freely with predetermined degrees of freedom within a space (3) provided in the satellite support structure (2). The measuring instrument (1) produces reference signals required by it for its inertial alignment, and is aligned with respect to a predetermined measurement target by a first positioning device (7). The satellite support structure (2) follows the motion of the measuring instrument (1) in order to overcome external disruptive forces and moments.
摘要翻译：用于卫星的支撑结构（2）中的高精度测量仪器（1）的定位系统，其中测量仪器（1）可以在设置在卫星中的空间（3）内以预定的自由度自由移动支撑结构（2）。测量仪器（1）产生用于其惯性对准所需的参考信号，并且通过第一定位装置（7）相对于预定测量目标对准。卫星支撑结构（2）跟随测量仪器（1）的运动，以克服外部破坏力和力矩。

10. 发明授权

US6158694A Spacecraft inertial attitude and rate sensor control system 有权
公开(公告)号：US6158694A
公开(公告)日：2000-12-12
申请号：US170986
申请日：1998-10-13
申请人： Sankaran Gowrinathan
发明人： Sankaran Gowrinathan
IPC分类号： B64G1/10 , B64G1/36 , B64G1/66
CPC分类号： B64G1/361 , B64G1/363 , B64G1/66 , B64G1/105 , B64G2001/1057
摘要： Disclosed is a method and apparatus (1'; 1") for tracking a stellar body (22) using a telescope (9; 32) of a spacecraft (e.g., a satellite) (10; 10"). In accordance with an embodiment of the invention, the telescope (9; 32) is provided with gimbal supports (18a; 18b), and is maneuverable relative to the spacecraft (10; 10'). The stellar body (22) is acquired by the telescope (9; 32) so that the stellar body (22) is within the field of view (FOV) of the telescope (9; 32). After the stellar body (22) is acquired, an operation is performed for controlling the attitude of the spacecraft (10; 10') to within pre-established deadband limits, and, as a result, the spacecraft (10; 10') and telescope (9; 32) are each assumed to have a desired orientation relative to the stellar body (22). The stellar body tracking method of the invention is performed so as to maintain the telescope (9; 32) in an orientation wherein the stellar body (22) is within the field of view (FOV) of the telescope (9; 32), even if it occurs that one or more environmental disturbance forces impinge on the spacecraft (10; 10') and cause an undesired variation in the orientation of the spacecraft (10; 10') relative to the stellar body (22). The stellar body tracking method of the invention controllably points a pointing direction (line of sight) of the stellar body tracking system (1'; 1") independently of the spacecraft (10; 10'), for tracking the stellar body (22). In accordance with an aspect of this invention, spacecraft inertial position and rate information is derived for use in controlling the attitude of the spacecraft (10; 10'). In accordance with an embodiment of the invention, the pointing direction of the telescope (9; 32) is controllably pointed by maneuvering at least one of the telescope (9; 32) and a mirror (13") of the telescope (9; 32).

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