• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.5
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• pp.447-454
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• 2016

Increase of space debris makes low earth orbit(LEO) environment more complex day by day and space situation Awareness(SSA) is becoming more important. As an essential part of SSA, space object surveillance and tracking is studied by many countries including America and Europe. And radar system forms the backbone of an space surveillance and tracking. Currently, Korea operates many LEO satellites like KOMPSAT but does not have dedicated radar systems which provide collision surveillance between satellite and space debris. Korea Aerospace Research Institute(KARI) NARO space center operates launch-vehicle tracking radar system in GOHEUNG and JEJU, respectively. In this paper, we describe developing operation concept to track International Space Station(ISS) using NARO radar and results of tracking. Then, we describe ISS orbit determination using radar tracking data. Lastly, orbit determination result is compares with TLE for analyzing effectiveness of orbit determination.

• Proceedings of the KSRS Conference
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• 2005.10a
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• pp.733-736
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• 2005

This paper presents the design of two antennas for the Dual-channel Radiometers for Earth and Atmosphere Monitoring (DREAM) the main payload, will be launched at NARO space center in Korea in 2007. The antennas are designed to meet stringent requirements of a very high beam efficiency, good pattern symmetry, and low VSWR, at 23.8 GHz and 37 GHz bands. Corrugated horn antennas are used. The simulation results of the electrical performance are presented.

• Korean Chemical Engineering Research
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• v.59 no.2
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• pp.180-185
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• 2021

In accordance with the revision of the US-Korea missile guidelines, restrictions on the use of solid propellants for space launch vehicles have been completely lifted. The solid propellant can be used as a solid propellant rocket like the KSR-1 (Korea Sounding Rocket-1), and can also be used as a thrust augmentation booster for liquid fuel launch vehicles. It is known that solid propellants have a lower risk of explosion than liquid propellants. but if an accident such as an explosion at the Alcantara Launch Center in Brazil occurs, it can lead to a large-scale personal accident. In order to prevent such large-scale accidents, it is necessary to review and reflect the minimum safety distance during use, storage and combustion test of solid propellants from the planning phase of the project. In this paper, the minimum safety distance for safe use of the solid propellant is presented by dividing it into storage facilities and combustion tests.

• Journal of Astronomy and Space Sciences
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• v.23 no.4
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• pp.355-372
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• 2006

Mission opportunities and trajectory characteristics for the future Korean Mars mission have designed and analyzed using KSIV-III(Korea Space Launch Vehicle-III). Korea's first space center, 'NARO space center' is selected as a launch site. For launch opportunities, year 2033 is investigated under considering the date of space center's completion with KSLV series development status. Optimal magnitude of various maneuvers, Trans Mars Injection (TMI) maneuver, Trajectory Correction Maneuver (TCM), Mars Orbit Insertion (MOI) maneuver and Orbit Trim Maneuver(OTM), which are required during the every Mars mission phases are computed with the formulation of nonlinear optimization problems using NPSOL software. Finally, mass budgets for upper stage (launcher for KSIV-III and spacecraft are derived using various optimized maneuver magnitudes. For results, daily launch window from NARO space center for successful Korean Mars mission is avaliable for next 27 minutes starting from Apr. 16. 2033. 12:17:26 (UTC). Maximum spacecraft gross mass which can delivered to Mars is about 206kg, with propellant mass of 109kg and structure mass of 97kg, when on board spacecraft thruster's Isp is assumed to have 290 sec. For upper stage, having structure ratio of 0.15 and Isp value of 280 sec, gross mass is about 1293kg with propellant mass of 1099kg and structure mass of 194kg. However, including 10% margins to computed optimal maneuver values, spacecraft gross mass is reduced to about 148kg with upper stage's mass of 1352kg. This work will give various insights, requiring performances to developing of KSIV-III and spacecraft design for future Korean Mars missions.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.105-112
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• 2009

Telemetry data is very important for the Launch Mission and Flight Safety Control during the Space Launch. In Naro Space Center, several telemetry stations such as a small station in the NARO space center, two stations in Jeju and a downrange station on a ship are deployed for the stable acquisition/receiving of the telemetry signals. In this paper, the Link Margin and Reliability for the telemetry are analyzed to evaluate the probability of the signal receiving of each station. Even though the proper analysis is to using the on-board EIRP(Effective Isotropic Radiation Power) values in the direction of the ground station considering the predicted flight trajectory and the locations of the stations, the global EIRP of 95% spatial coverage has been used for the analysis, due to the limitation of the available data.

• Proceedings of the Korean Society of Crop Science Conference
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• 2017.06a
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• pp.186-186
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• 2017

Relay intercropping system of direct seeded rice and winter cereal is labor saving cultivation and has high land use efficiency in Japan. In this system, rice seeds are direct seeded into inter-row space of winter cereals (wheat or barley) in March or April. If the direct seeding of rice is conducted before stem elongation phase or using suitable seeder, these are little effect to yield of winter cereals. Though the seeds are generally thiuram treated, it's a matter that seedling establishment rate (SER) of direct seeded rice is low and unstable. The cause of low SER has not been revealed. In present study, with the aim to reveal causes of low SER, we conducted experiments and investigated the SER, and analyzed some factors that might affect SER. Experiment1: In 2015, 2016, we buried rice seeds underground, and investigated the transition of the seed survival rates (SSR). Seeds were thiuram-treated or non-treated. In 2 periods, SSR of thiuram-treated seeds were significantly higher than non-treated seeds. In 2016, thiuram-treated seeds were high in SSR (almost 75%) at April 30th, but low SER (10~27%) after harvest of winter cereals. Therefore, almost all of seed death might have been happen after germination. Analysis 1: We investigated the SER and cultivation conditions in Ibaraki pref. for several years. Meteorological factors were referred from the nearest point of AMeDAS. From mean temperature (MT) among 5days after and before the day, we divided the period of seeding ~June 20 to phase1~4. We defined each phase as below; Phase1: $MT{\leq}10^{\circ}C$, Phase2: $10^{\circ}C<MT{\leq}15^{\circ}C$, Phase3:$15^{\circ}C<MT{\leq}20^{\circ}C$, Phase4: $MT>20^{\circ}C$. We analyzed the correlation of SER and meteorological factors by each phase. Total number of days in phase 1~4 was significantly negative correlated with SER. In phase1, total rain fall and number of soil wetting days were significantly negative correlated with SER. In phase2~4, only MT was significantly positive correlated with SER. This result suggested that rainfalls in phase1 declined seed vigor to emergence from soil surface, by repeated water absorption and re-dry. From these present studies, it was suggested that one of factors of low SER of direct seeded rice in relay intercropping system is changing of water condition by rainfalls in phase1 ($MT{\leq}10^{\circ}C$). To improve SER, it's necessary to consider something seed treatments such as prevent water absorption during phase1. However, 58~60% of seeds seemed to die during May. It's suggested that, if seeds are thiuram treated, almost all of seeds can germinate underground, but the seed vigor to emergence from soil surface are insufficient. Further studies are needed to reveal the rest causes that is happening during emergence from soil surface.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.280-287
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• 2010

The first Korean satellite launch vehicle, KSLV-I(Korea Space Launch Vehicle-I), was launched for its first flight test on Aug. 25, 2009 from Naro Space Center located in south Jolla province. Because launch vehicles usually fly long range with large amount of propellants aboard, preparation of countermeasures against potential malfunctions during flight is essential in launch operation. In this paper, the flight safety operation, prepared to guarantee flight safety during launch operation of KSLV-I, is presented. Prior to flight test, flight safety analysis is performed to estimate associated risk levels quantitatively, and during flight, flight safety systems are operated to cope with any risky situations. Real-time flight monitoring including computation of instantaneous impact point using tracking data is executed normally and the flight test is completed without activation of flight termination system.

• Proceedings of the Korean Society of Computer Information Conference
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• 2016.07a
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• pp.29-32
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• 2016

본 논문에서는 나로호(KSLV-I) 비행상태의 실시간 감시를 목적으로 국내에서는 처음 개발된 우주센터 원격수신자료전시시스템(EDS)의 구축과 운용을 소개한다. EDS는 우주센터 발사통제시스템의 주요 시스템 중 하나이고 그 역할은 위성발사체의 비행에 중대한 영향을 주는 주요정보(QLM)와 궤적정보(TSPI)를 수신하여 실시간으로 처리함으로써 탑재 서브시스템별 전문가들이 위성발사체의 비행 상태를 감시할 수 있도록 지원하는 것이다. EDS는 3회에 걸친 나로호 비행시험에서 그 역할에 따라 매회 8대가 운영되었으며 임무를 성공적으로 수행하였다. 본 시스템을 기반으로 추후 발전된 형태의 한국형발사체(KSLV-II) 비행상태의 실시간 감시시스템의 구축이 가능할 것으로 예상된다.

• Journal of the Korean Institute of Gas
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• v.27 no.3
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• pp.108-115
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• 2023

Although hydrazine is an excellent liquid propellant, caution is required during storage and handling due to its high toxicity and reactivity. Safety guidelines should be established in consideration of the chemical reactivity by unintended leakage. In this study, the status of hydrazine facilities at launch site and safety standards for storing and handling were investigated and then, the reactivity between chemicals and hydrazine was analyzed. As a result of the analysis, hydrazine has reactivity with the exception of fuel oil. This paper emphasizes the imperative nature of constructing a dedicated hydrazine storage facility. Ensuring compatibility between hydrazine and the materials used in storage containers and handling equipment is crucial to prevent undesired reactions that could compromise safety. It was intended to be used as basic data to secure the range safety when handling hydrazine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.682-685
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• 2010

KSLV-I is the 1st Korean satellite launch vehicle, which was launched at Naro space center by Korea Aerospace Research Institute (KARI) in AUG. 2009, and JUN. 2010. Although the missions of 1st and 2nd launch of KSLV-I were not successful, safety of launch vehicle was accomplished through the cooperation with the Russian partner Khrunichev Space Research and Production Center (KhSC). Both parties co-developed the technical safety management program to ensure launch safety. In this paper, the analysis and contents of safety program are illustrated.