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.

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.

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.

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.

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: 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: 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: 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: 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: 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: A belt supporting type reflecting mirror mount that is capable of minimizing an amount of deformation of the reflection plane of a reflecting mirror and supporting the reflecting mirror. The reflecting mirror mount comprises a base, a fork coupled to the base so as to be able to be swiveled, a frame hinged to the fork which has a reflecting mirror disposed therein, at least one load support installed on the frame and supporting a load of the reflecting mirror applied in an optical axial direction, and a belt fastener that has a belt supporting a circumference of the reflecting mirror, and belt supports installed on the frame and fixedly supporting opposite ends of the belt. Thereby, the load of the reflecting mirror is uniformly distributed across the belt.

Abstract: Provided is a miniature pin extracting device for extracting a miniature pin inserted into a part. The miniature pin extracting device includes a coupling having a polygonal pillar shape, the coupling having a lower end coupled to the locating pin, a retainer mounted outside the coupling, and a screw part supported by the retainer, the screw part being coupled to an upper end of the coupling. Thus, a rotation force of the screw part may be converted into a vertical axial motion through the retainer to safely extract the locating pin without lateral force and rotation, thereby minimizing damage of the part.

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: 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: 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: A belt supporting type reflecting mirror mount that is capable of minimizing an amount of deformation of the reflection plane of a reflecting mirror and supporting the reflecting mirror. The reflecting mirror mount comprises a base, a fork coupled to the base so as to be able to be swiveled, a frame hinged to the fork which has a reflecting mirror disposed therein, at least one load support installed on the frame and supporting a load of the reflecting mirror applied in an optical axial direction, and a belt fastener that has a belt supporting a circumference of the reflecting mirror, and belt supports installed on the frame and fixedly supporting opposite ends of the belt. Thereby, the load of the reflecting mirror is uniformly distributed across the belt.

Abstract: Provided are a multi-frequency millimeter-wave very long baseline interferometry (VLBI) receiving system and a method of designing a quasi optical circuit for the multi-frequency millimeter-wave VLBI receiving system. The multi-frequency millimeter-wave VLBI receiving system includes a plurality of low pass filters, offset ellipsoidal mirrors, and flat mirrors for dividing a cosmic radio wave signal incident through the troposphere. A beam propagated from a celestial point is introduced into a receiver room via a 45-degree flat mirror and is divided into a plurality of beams by using a plurality of low pass filters having different bandwidths and mirrors, and the divided beams are transmitted to corresponding quasi-optical receivers having different bandwidths via a plurality of mirrors. Therefore, radio astronomic observations can be simultaneously performed in 22 GHz, 43 GHz, 86 GHz, and 129 GHz bands, and phase variations of electromagnetic waves in the bands can be compensated for.