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公开(公告)号：US20140002813A1
公开(公告)日：2014-01-02
申请号：US13930893
申请日：2013-06-28
Inventor： Yoon-Kyung Seo
IPC: G01S17/66
CPC classification number: G01S17/66
Abstract: A satellite tracking system and a method of controlling the same, in which the satellite tracking system comprises an ARGO-M Operation System (AOS) and a Tracking Mount System (TMS). The AOS comprises a time & frequency system configured to include a Global Positioning System (GPS) receiver, and to receive Universal Time Coordinated (UTC), and an Interface Control System (ICS) configured to calculate the orbital position data of a satellite using the UTC and per-satellite estimated orbit data by means of Lagrangian interpolation, and to send a command to track the position of the satellite. The TMS comprises a tracking mount configured to support a telescope that measures distance to the satellite, and to operate in accordance with the position of the satellite, and a servo controller configured to receive the orbital position data of the satellite, to receive the UTC, and to send a command to track the satellite.
Abstract translation: 卫星跟踪系统及其控制方法，其中卫星跟踪系统包括ARGO-M操作系统（AOS）和跟踪安装系统（TMS）。 AOS包括被配置为包括全球定位系统（GPS）接收机并且接收世界时间协调（UTC）的时间和频率系统，以及接口控制系统（ICS），被配置为使用所述接收机控制系统（ICS）来计算卫星的轨道位置数据 UTC和每卫星估计的轨道数据通过拉格朗日插值，并发送一个命令来跟踪卫星的位置。 TMS包括跟踪安装座，其配置成支撑望远镜，该望远镜测量到卫星的距离，并且根据卫星的位置进行操作;以及伺服控制器，被配置为接收卫星的轨道位置数据，以接收UTC， 并发送跟踪卫星的命令。
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2.发明公开公开(公告)号：US20240022828A1
公开(公告)日：2024-01-18
申请号：US18251723
申请日：2021-10-29
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Seonghwan Choi , Ji-Hye Baek , Jihun Kim , Jongyeob Park , Heesu Yang , Jeong-Yeol Han
IPC: H04N23/741 , G06T5/00
CPC classification number: H04N23/741 , G06T5/003 , G06T2207/20221
Abstract: The present invention relates to an adaptive optical system using artificial intelligence and not having a deformable mirror, the adaptive optical system being capable of generating an image with no distortion or minimized distortions, without using a surface-deformable reflector which is relatively expensive equipment, and also being capable of generating a high-quality image.
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公开(公告)号：US20150325130A1
公开(公告)日：2015-11-12
申请号：US14709997
申请日：2015-05-12
Applicant: Korea Astronomy and Space Science Institute
Inventor： Ji-Hye BAEK , Jaejin LEE , Seonghwan CHOI , Eunmi HWANG , Young-Deuk PARK
CPC classification number: G01W1/02 , G01W1/10 , G08G5/0004 , G08G5/0013 , G08G5/0021 , G08G5/0052 , G08G5/0091
Abstract: A space weather monitoring system for polar routes includes: a satellite which flies over polar routes; a route-information providing server which receives data collected by the satellite monitoring the polar routes and generates various pieces of information about space weather; a flight vehicle which makes a request for information about the polar routes of the flight to the route-information providing server, and flies over the polar routes based on the received information; and a network which relays data among the satellite, the route-information providing server and the flight vehicle, so that an aurora-distribution map needed for an aircraft flight, an electromagnetic wave absorption map based on the ionosphere, information about space weather, and the situation and forecast of the space weather can be provided to an airline, thereby having effects on allowing the airline to check the information about the space weather in real time and fully considering a user who is unfamiliar to the space weather.
Abstract translation: 极地航路的空间气象监测系统包括：飞越极地航路的卫星; 路线信息提供服务器，接收卫星收集的数据，监测极地路线，并产生有关空间天气的各种信息; 向飞行信息提供服务器请求关于飞行极地路线的信息的飞行器，并基于接收的信息飞越极地路线; 以及在卫星，路线信息提供服务器和飞行车辆之间中继数据的网络，使得飞机飞行所需的极光分布图，基于电离层的电磁波吸收图，关于空间天气的信息，以及 可以向航空公司提供空间天气的情况和预测，从而影响航空公司实时检查有关空间天气的信息，充分考虑到空间天气不熟悉的用户。
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公开(公告)号：US20130248245A1
公开(公告)日：2013-09-26
申请号：US13851089
申请日：2013-03-26
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Chan PARK , Moo-Young CHUN , Jae Sok OH , Jakyoung NAH
IPC: H02G3/22
Abstract: Disclosed is a vacuum wall-through structure to be installed in a hole formed in a wall of a vacuum chamber. The vacuum wall-through structure includes a cable holder that holds a cable at the center thereof and a cable holder cover installed outside the cable holder.
Abstract translation: 公开了一种真空壁式结构，其被安装在形成在真空室的壁上的孔中。 真空壁式贯通结构包括在其中心处保持电缆的电缆保持器和安装在电缆保持器外部的电缆保持器盖。
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公开(公告)号：US20240178890A1
公开(公告)日：2024-05-30
申请号：US18507691
申请日：2024-02-08
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Jiwoong YU
IPC: H04B7/0426 , H04B7/06
CPC classification number: H04B7/043 , H04B7/06958
Abstract: The present invention relates to a beam steering device of a phased array antenna for reducing a grating lobe, and more particularly, to a beam steering device of a phased array antenna for reducing a grating lobe so that grating lobes generated when receiving a signal by rotating an array of a plurality of antenna elements at a predetermined angle during transmission do not overlap each other when receiving the signal through the beam steering device.
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Patent Agency Ranking
公开(公告)号：US20230348117A1
公开(公告)日：2023-11-02
申请号：US18350740
申请日：2023-07-11
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Eun Jung CHOI
CPC classification number: B64G3/00 , G06F17/175
Abstract: A method for re-entry prediction of an uncontrolled artificial space object includes: calculating an average semi-major axis and an argument of latitude by inputting two-line elements or osculating elements of an artificial space object at two different time points; calculating an average semi-major axis, argument of latitude, and atmospheric drag at a second time point; estimating an optimum drag scale factor while changing the drag scale factor; predicting the time and place of re-entry of an artificial space object into the atmosphere by applying the estimated drag scale factor. Here, orbit prediction is performed by using a Cowell's high-precision orbital propagator using numerical integration from the second time point to a re-entry time point.
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7.发明申请公开(公告)号：US20210356275A1
公开(公告)日：2021-11-18
申请号：US17245390
申请日：2021-04-30
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Eun Jung Choi
IPC: G01C21/24
Abstract: A method of determining a precise orbit of a satellite through estimation of a parallactic refraction scale factor is proposed, the method including inputting an initial estimate including initial orbit information of a satellite with respect to an observation epoch and the parallactic refraction scale factor; performing orbit propagation using a high-precision orbit propagator by applying a dynamics model; performing observer-centered satellite optical observation modeling including the parallactic refraction scale factor; calculating an observation residual between actual optical observation data and observation data calculated via the observation modeling reflecting the parallactic refraction; and precisely determining the orbit of the satellite by estimating the parallactic refraction scale factor and a satellite state vector using a batch least square estimation algorithm.
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公开(公告)号：US08773654B2
公开(公告)日：2014-07-08
申请号：US13930893
申请日：2013-06-28
Inventor： Yoon-Kyung Seo
IPC: G01B11/26
CPC classification number: G01S17/66
Abstract: A satellite tracking system and a method of controlling the same, in which the satellite tracking system comprises an ARGO-M Operation System (AOS) and a Tracking Mount System (TMS). The AOS comprises a time & frequency system configured to include a Global Positioning System (GPS) receiver, and to receive Universal Time Coordinated (UTC), and an Interface Control System (ICS) configured to calculate the orbital position data of a satellite using the UTC and per-satellite estimated orbit data by means of Lagrangian interpolation, and to send a command to track the position of the satellite. The TMS comprises a tracking mount configured to support a telescope that measures distance to the satellite, and to operate in accordance with the position of the satellite, and a servo controller configured to receive the orbital position data of the satellite, to receive the UTC, and to send a command to track the satellite.
Abstract translation: 卫星跟踪系统及其控制方法，其中卫星跟踪系统包括ARGO-M操作系统（AOS）和跟踪安装系统（TMS）。 AOS包括被配置为包括全球定位系统（GPS）接收机并且接收世界时间协调（UTC）的时间和频率系统，以及接口控制系统（ICS），被配置为使用所述接收机控制系统（ICS）来计算卫星的轨道位置数据 UTC和每卫星估计的轨道数据通过拉格朗日插值，并发送一个命令来跟踪卫星的位置。 TMS包括跟踪安装座，其配置成支撑望远镜，该望远镜测量到卫星的距离，并且根据卫星的位置进行操作;以及伺服控制器，被配置为接收卫星的轨道位置数据，以接收UTC， 并发送跟踪卫星的命令。
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9.发明申请PRECISION ALIGNMENT DEVICE OF AN OPTICAL COMPONENT AND A METHOD OF USING THE DEVICE 审中-公开光学部件的精密对准装置和使用该装置的方法公开(公告)号：US20130239385A1
公开(公告)日：2013-09-19
申请号：US13847017
申请日：2013-03-19
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Chan PARK
IPC: G02B7/00
CPC classification number: G02B7/003 , Y10T29/49817 , Y10T403/56
Abstract: Provided are a precision alignment device of an optical component and a method of using the device. The device includes a location fixing unit inserted and coupled to a pin hole on an optical table, closely attached to an optical mount, and fixes a location of the optical component, and a bumper including a penetration hole formed to allow the location fixing unit to penetrate to be coupled thereto, the bumper having a thickness formed in a lateral direction to maintain a certain distance between the location fixing unit and the optical mount when at least one side is closely attached to the optical mount. A location of the optical mount is determined while coupling the bumper to the location fixing unit.
Abstract translation: 提供了光学部件的精密对准装置和使用该装置的方法。 该装置包括位置固定单元，该位置固定单元插入并联接到光学平台上的紧密附着到光学安装座上的针孔，并且固定光学部件的位置，以及保险杠，其包括形成为允许位置固定单元 穿透以联接到其上，当至少一侧紧密地附接到光学座架上时，保险杠具有沿横向方向形成的厚度，以在位置固定单元和光学座架之间保持一定距离。 在将保险杠连接到位置固定单元的同时确定光学支架的位置。
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10.发明公开公开(公告)号：US20230365276A1
公开(公告)日：2023-11-16
申请号：US18350862
申请日：2023-07-12
Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE
Inventor： Eun Jung CHOI
Abstract: A method of determining a precise orbit of a satellite through estimation of a parallactic refraction scale factor is proposed, the method includes inputting an initial estimate including initial orbit information of a satellite with respect to an observation epoch and the parallactic refraction scale factor; performing orbit propagation using a high-precision orbit propagator by applying a dynamics model; performing observer-centered satellite optical observation modeling including the parallactic refraction scale factor; calculating an observation residual between actual optical observation data and observation data calculated via the observation modeling reflecting the parallactic refraction; and precisely determining the orbit of the satellite by estimating the parallactic refraction scale factor and a satellite state vector using a batch least square estimation algorithm.
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