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.

公开(公告)号：US08773654B2

公开(公告)日：2014-07-08

申请号：US13930893

申请日：2013-06-28

Applicant: Korea Astronomy and Space Science Institute ,  Dong-Young Rew

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。

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。

公开(公告)号：US10948610B2

公开(公告)日：2021-03-16

申请号：US15675304

申请日：2017-08-11

Applicant: Korea Astronomy and Space Science Institute ,  Korea Meteorological Administration

Inventor： Junga Hwang

IPC: G01T1/02

Abstract: An analysis system for an aviation radiation dose includes: a proton spectrum generator which generates a galactic cosmic ray incident on the Earth's atmosphere and a proton spectrum corresponding to a solar proton event; a global radiation dose map producer which generates-particle transport and produces a radiation dose map; a global radiation dose map converter which converts the radiation dose map based on a standard atmosphere into a radiation dose map corresponding to current atmosphere conditions in real time; and a database in which data necessary for operations of the proton spectrum generator, the global radiation dose map producer and the global radiation dose map converter is previously calculated and stored, thereby having an effect on estimating any radiation route dose if information about an arbitrary path and time is given.

公开(公告)号：US20180045836A1

公开(公告)日：2018-02-15

申请号：US15675304

申请日：2017-08-11

Applicant: Korea Astronomy and Space Science Institute ,  Korea Meteorological Administration

Inventor： Junga HWANG

IPC: G01T1/02

CPC classification number: G01T1/02

Abstract: An analysis system for an aviation radiation dose according to the present invention includes: a proton spectrum generator which calculates a galactic cosmic ray incident on the Earth's atmosphere and a proton spectrum corresponding to a solar proton event; a global radiation dose map producer which calculates particle transport based on the proton spectrum and produces a radiation dose map; a global radiation dose map converter which converts the radiation dose map produced based on a standard atmosphere into a radiation dose map corresponding to current atmosphere conditions in real time; and a database in which data necessary for operations of the proton spectrum generator, the global radiation dose map producer and the global radiation dose map converter is previously calculated and stored, thereby having an effect on estimating a radiation dose of another route if another piece of information about an arbitrary path and time is given besides a previous given path.

公开(公告)号：US09541673B2

公开(公告)日：2017-01-10

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

IPC: G06F19/00 ,  G01W1/02 ,  G08G5/00 ,  G01W1/10

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。

公开(公告)号：US08976341B2

公开(公告)日：2015-03-10

申请号：US13967204

申请日：2013-08-14

Applicant: Korea Astronomy and Space Science Institute

Inventor： Seung Cheol Bang ,  Hyung Chul Lim ,  Jong Uk Park

IPC: G01S7/484 ,  G01S17/10 ,  G01S7/486

CPC classification number: G01S7/484 ,  G01S7/4865 ,  G01S17/105

Abstract: An optoelectric control apparatus for a satellite laser ranging system comprises a communication controller for externally receiving optoelectric control data. Memory is connected to the communication controller and stores a round trip distance to a satellite. A laser generation control unit is connected to the communication controller and outputs a laser fire signal. A signal measurement unit receives a laser start time. A real-time conversion unit is connected to the signal measurement unit and the communication controller, and converts a predicted laser arrival time into real time. A Lagrange interpolation processor is connected to the real-time conversion unit and the memory, and calculates a time at which laser light fired by a laser transmission unit returns back to a laser reception unit (laser arrival time). The clock unit is connected to a time measurement unit, the real-time conversion unit, a register unit, and a delay unit, and outputs time information.

Abstract translation: 一种用于卫星激光测距系统的光电控制装置，包括用于外部接收光电控制数据的通信控制器。 存储器连接到通信控制器并存储到卫星的往返距离。 激光产生控制单元连接到通信控制器并输出激光火焰信号。 信号测量单元接收激光开始时间。 实时转换单元连接到信号测量单元和通信控制器，并将预测的激光到达时间实时转换。 拉格朗日内插处理器连接到实时转换单元和存储器，并且计算由激光传输单元发射的激光返回激光接收单元（激光到达时间）的时间。 时钟单元连接到时间测量单元，实时转换单元，寄存器单元和延迟单元，并输出时间信息。

公开(公告)号：US20140118717A1

公开(公告)日：2014-05-01

申请号：US13967204

申请日：2013-08-14

Applicant: KOREA ASTRONOMY AND SPACE SCIENCE INSTITUTE

Inventor： Seung Cheol Bang ,  Hyung Chul Lim ,  Jong Uk Park

IPC: G01C3/08

CPC classification number: G01S7/484 ,  G01S7/4865 ,  G01S17/105

Abstract: An optoelectric control apparatus for a satellite laser ranging system comprises a communication controller for externally receiving optoelectric control data. Memory is connected to the communication controller and stores a round trip distance to a satellite. A laser generation control unit is connected to the communication controller and outputs a laser fire signal. A signal measurement unit receives a laser start time. A real-time conversion unit is connected to the signal measurement unit and the communication controller, and converts a predicted laser arrival time into real time. A Lagrange interpolation processor is connected to the real-time conversion unit and the memory, and calculates a time at which laser light fired by a laser transmission unit returns back to a laser reception unit (laser arrival time). The clock unit is connected to a time measurement unit, the real-time conversion unit, a register unit, and a delay unit, and outputs time information.

Abstract translation: 一种用于卫星激光测距系统的光电控制装置，包括用于外部接收光电控制数据的通信控制器。 存储器连接到通信控制器并存储到卫星的往返距离。 激光产生控制单元连接到通信控制器并输出激光火焰信号。 信号测量单元接收激光开始时间。 实时转换单元连接到信号测量单元和通信控制器，并将预测的激光到达时间实时转换。 拉格朗日内插处理器连接到实时转换单元和存储器，并且计算由激光传输单元发射的激光返回激光接收单元（激光到达时间）的时间。 时钟单元连接到时间测量单元，实时转换单元，寄存器单元和延迟单元，并输出时间信息。