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：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。

公开(公告)号：US20130105695A1

公开(公告)日：2013-05-02

申请号：US13578536

申请日：2012-05-02

Applicant: Jeong Yeol Han ,  Kwang Dong Kim ,  Jeong Gyun Jang ,  Bi Ho Jang

Inventor： Jeong Yeol Han ,  Kwang Dong Kim ,  Jeong Gyun Jang ,  Bi Ho Jang

IPC: G01J5/08

CPC classification number: G02B23/04 ,  G02B27/141

Abstract: An optical device includes a body tube having an open end; a main reflector mounted to the other end opposite to the open end via an inner space of the body tube; a secondary reflector provided in the body tube to enable a light reflected by the main reflector incident thereon; a splitter arranged between the main reflector and the secondary reflector to enable a light reflected toward the inner space of the body tube by the secondary incident thereon, the splitter configured to divide the light incident thereon into a light at a visible wavelength range and a light at an infrared ray wavelength range; a visible ray analysis unit configured to read the light at the visible wavelength range incident from the splitter; and an infrared ray analysis unit configured to read the light at the infrared ray wavelength range incident from the splitter.

Abstract translation: 光学装置包括具有开口端的主体管; 主反射器经由主体管的内部空间安装到与开口端相对的另一端; 设置在所述主体管中的次级反射器，以使能由所述主反射器反射的光入射到其上; 分配器，其布置在所述主反射器和所述次反射器之间，以使得能够通过二次入射而朝向所述主体管的内部空间反射的光，所述分离器被配置为将入射到其上的光分成可见波长范围的光和光 在红外线波长范围; 可见光分析单元，被配置为读取从分离器入射的可见光波长范围的光; 以及红外线分析单元，被配置为读取从分路器入射的红外线波长范围的光。

公开(公告)号：US20250138294A1

公开(公告)日：2025-05-01

申请号：US18819637

申请日：2024-08-29

Applicant: Korea Astronomy and Space Science Institute

Inventor： Ho Jae AHN ,  Soo Jong PARK ,  Seung Hyuk CHANG ,  Su Min LEE ,  Chang-Hee KIM ,  Sung Ho LEE ,  Yun Jong KIM

IPC: G02B17/06

Abstract: A mode conversion apparatus includes a first freeform-surface mirror to reflect incident light provided from a front-end optical system and output the reflected light in a first direction, and a second freeform-surface mirror to reflect the reflected light and output mode-converted light in a second direction where surface shapes of the first and second mirrors are determined based on a freeform-surface coefficient determined by at least five optical parameters of a distance from the first mirror to a confocal point of the first mirror and the second mirror, a distance from the confocal point to the second mirror, a distance from a waist of the incident light to the first mirror, a distance from the second mirror to a waist of the mode-converted light, and an incident angle of the incident light for the first mirror and an incident angle of the reflected light for the second mirror.

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.

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

IPC: B64G3/00 ,  G06F17/17

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.

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：US09116511B2

公开(公告)日：2015-08-25

申请号：US13278879

申请日：2011-10-21

Applicant: Seung-Cheol Bang ,  Hyung Chul Lim ,  Jong Uk Park

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

IPC: G04F10/00 ,  G04G3/04 ,  G04F10/04

CPC classification number: G04F10/005 ,  G04F10/00 ,  G04F10/04 ,  G04G3/04

Abstract: The present invention makes it possible to measure a precision event time in such a way to make a reference data in accordance with a standard time reference frequency signal and to make a measurement data by using an apparatus with the same structure as a reference data with respect to a signal to be measured and to compare the measurement data with a reference data, whereby temperature effects can be minimized by making the time changes due to temperature changes occurring between two apparatuses happen equally, by providing the same structure and parts to a reference signal circuit apparatus for an event time measurement and a signal circuit apparatus to be measured, and the zero point adjustment is performed during the real time operation, so the system is not needed to stop.

Abstract translation: 本发明使得可以以这样的方式测量精确事件时间，以便根据标准时间参考频率信号作出参考数据，并且通过使用具有与参考数据相同结构的装置来制作测量数据， 与要测量的信号相比较，并将测量数据与参考数据进行比较，从而通过使两个装置之间发生的温度变化引起的时间变化可以使温度效应最小化，通过将相同的结构和部件提供给参考信号 用于事件时间测量的电路装置和待测量的信号电路装置，并且在实时操作期间执行零点调整，因此系统不需要停止。

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。