• Title/Summary/Keyword: Naro Space Center

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Liquid Oxygen Filling System of Propulsion System Test Complex(PSTC) for KSLV-II (한국형발사체 추진기관시스템 시험설비(PSTC) 산화제 공급 시스템)

  • Lee, Janghwan;Choi, Bongsu;Kim, Yongwook;Cho, Kiejoo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1184-1187
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    • 2017
  • The space launch vehicle needs the verification of each stage's propulsion system. The Propulsion System Test Complex(PSTC) is constructed for developing KSLV-II in the Naro space center. Hydraulic and pneumatic system of PSTC should supply propellants and various gases to propulsion system module according to required condition. This paper introduces liquid oxygen filling system of PSTC.

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SYSTEM INTEGRATION AND PERFORMANCE TEST OF DREAM ON STSAT-2

  • Kim, Sung-Hyun;Lee, Ho-Jin;Moon, Nam-Won;Wi, Hoon;Seong, Jin-Taek;Lee, Sang-Hyun;Park, Jong-Oh;Sim, Eun-Sup;Zhang, De-Hai;Jian, Jing-Shan;Kim, Yong-Hoon
    • Proceedings of the KSRS Conference
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    • 2007.10a
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    • pp.374-377
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    • 2007
  • Dual-channel Radiometers for Earth and Atmosphere Monitoring (DREAM) was developed as the Korean first spaceborne microwave radiometer for earth remote sensing. It is the main payload of the Science and Technology SATellite-2 (STSAT-2). STSAT-2 will be launched by Korea Space Launch Vehic1e-l (KSLV-1) at NARO Space Center in Korea in 2008. The DREAM is a two-channel, total power microwave radiometers with the center frequencies of 23.8 GHz and 37 GHz. The bandwidths of radiometer are 600 MHz at 23.8 GHz and 1000 MHz at 37 GHz. The integration time is 200 ms and the required sensitivity is less than 0.5 K. In this paper, we summarize the specification and performance of the developed DREAM firstly. And we describe system integration and performance test of DREAM mounted on spacecraft.

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STSAT-2 PFM Environmental Test Result (과학기술위성 2호 준비행모델 환경시험 결과)

  • Lee, Seung-Hun;Park, Jong-Oh;Sim, Eun-Sup;Rhee, Seung-Woo;Seo, Jung-Ki;Jang, Tae-Sung;Lee, Sang-Hyun;Kim, Sung-Hyun
    • Aerospace Engineering and Technology
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    • v.6 no.1
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    • pp.55-63
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    • 2007
  • STSAT-2 (Science & Technology SATellite-2) is a Korea micro-satellite which will be launched at NARO Space center in Koheung, Korea. Launch vehicle for STSAT-2 is KSLV-1 (Korea Space Launch Vehicle-1) which is the first development in Korea space launch vehicle program. Starting development in 2002 EM(Engineering Model), PFM(Proto-Flight Model), and FM(Flight Model) were developed completely. Electrical functional test, space environmental test, and launch vehicle environmental test on system level are performed for testing those development models. In this paper we report the results of STSAT-2 PFM space environmental test and launch vehicle environmental test which is successfully completed.

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Application of trajectory data mining to improve the estimation accuracy of launcher trajectory by telemetry ground system (원격자료수신장비의 발사체궤적 추정정확도 향상을 위한 궤적데이터마이닝의 적용)

  • Lee, Sunghee;Kim, Doo-gyung;Kim, Keun-hyung
    • Journal of Korea Society of Industrial Information Systems
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    • v.20 no.5
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    • pp.1-11
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    • 2015
  • This paper is focused on how the trajectory of launch vehicle could be optimally estimated by the quadratic regression of trajectory data mining for the operation of telemetry ground system in NARO space center during real-time. To receive the telemetry data, the telemetry ground system has to track the space launch vehicle without tracking loss, and it is possible by the well-designed algorithm to estimate a flight position in real-time. For this reason, the quadratic regression model instead of interpolation was considered to estimate the exact position data of launch vehicle and the improvement of antenna performance. For analysis, the real trajectory data which had been logged during NARO 1st launch mission were used, the estimation result of launcher current position was analyzed by the mathematical modeling. In conclusion, the algorithm using quadratic regression based on trajectory data mining showed the better performance than previous interpolation algorithm to estimate the next flight position and the antenna driving performance.

LCS(Launch Control System) Prototype Performance Analysis (발사관제시스템 프로토타입 성능 분석)

  • Hong, Ii Hee;Kim, Yang Mo
    • Journal of the Korean Society of Systems Engineering
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    • v.2 no.1
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    • pp.54-60
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    • 2006
  • LCC(Launch Control Center) in NARO space center performs a data monitoring and control through the interface to the external system of launch vehicle. Launch control function needs high reliability and processing speed. Hence, LCS(Launch Control System) is made up a real time system. An important role of the LCS Prototype is discovering a risk element and minimizing it through developing a launch control system. This paper deals with a real time data processing among the simulator, gateway, data distribution server, command and control server which is involving LCS Prototype.

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The Development of Launch Vehicle Simulator Using an Object-orinted Design (객체지향 설계론을 이용한 발사체 시뮬레이터 개발)

  • Choi Won;Chung Hae uk;Seo Jin-Ho;Hong Il-Hee
    • Proceedings of the Korea Society for Simulation Conference
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    • 2005.05a
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    • pp.106-111
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    • 2005
  • LCC(Launch Control Center) in NARO Space Center perform a data monitoring and control through the interface to the external system of launch vehicle. Launch Control function needs a high reliability and processing speed. Hence, LCC's remote control system configure a real time system. An important role of the Simulation system is discovering a risk element and minimize it When developing a launch control system. Also, secure a development technique to solve the risks. Launch Vehicle simulator is composed of various component at characteristic of the Launch Vehicle. To be like this each function component the developer will be able to develop easily in order, it using the LabVIEW which is a Graphical Program and it programs, The LabVIEW GOOP(Graphical Object-orinted Programming) which supports an Object-orinted programming it uses with the Component it develops will have a strong point which reusability and a unit test, maintenance, size of program and individual developments.

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The Liability for Space Activity of Launching State of Space Object and Improvement of Korea's Space Policy (우주물체 발사국의 우주활동에 대한 책임과 우리나라 우주정책의 개선방향)

  • Lee, Kang-Bin
    • The Korean Journal of Air & Space Law and Policy
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    • v.28 no.2
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    • pp.295-347
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    • 2013
  • Korea launched the science satellite by the first launch vehicle Naro-ho(KSLV-1) at the Naro Space Center located at Oinarodo, Cohenggun Jellanamdo in August, 2009 and October, 2010. However, the first and second launch failed. At last, on January 30, 2013 the third launch of the launch vehicle Naro-ho has successfully launched and the Naro science satellite penetrated into the space orbit. Owing to the succeed of the launch of Naro-ho, Korea joined the space club by the eleventh turn following the United States, Russia, Japan and China. The United Nations adopted the Outer Space Treaty of 1967, the Rescue Agreement of 1968, the Liability Convention of 1972, the Regislation Convention of 1976, and Moon Agreement of 1979. Korea ratified the above space-related treaties except the Moon Agreement. Such space-related treaties regulate the international liability for the space activity by the launching state of the space object. Especially the Outer Space Treaty regulates the principle concerning the state's liability for the space activity. Each State Party to the Treaty that launches or procures the launching of an object into outer space is internationally liable for damage to another State Party or to its natural or judicial persons by such object or its component parts on the earth, in air space or in outer space. Under the Liability Convention, a launching state shall be absolutely liable to pay compensation for damage caused by its space object on the surface of the earth or to aircraft in flight. The major nations of the world made national legislations to observe the above space-related treaties, and to promote the space development, and to regulate the space activity. In Korea, the United States, Russia and Japan, the national space-related legislation regulates the government's liability of the launching state of the space object. The national space-related legislations of the major nations are as follows : the Outer Space Development Promotion Act and Outer Space Damage Compensation Act of Korea, the National Aeronautic and Space Act and Commercial Space Launch Act of the United States, the Law on Space Activity of Russia, and the Law concerning Japan Aerospace Exploration Agency and Space Basic Act of Japan. In order to implement the government's liability of the launching state of space object under space-related treaties and national legislations, and to establish the standing as a strong space nation, Korea shall improve the space-related policy, laws and system as follows : Firstly, the legal system relating to the space development and the space activity shall be maintained. For this matter, the legal arrangement and maintenance shall be made to implement the government's policy and regulation relating to the space development and space activity. Also the legal system shall be maintained in accordance with the elements for consideration when enacting the national legislation relevant to the peaceful exploration and use of outer space adopted by UN COPUOS. Secondly, the liability system for the space damage shall be improved. For this matter, the articles relating to the liability for the damage and the right of claiming compensation for the expense already paid for the damage in case of the joint launch and consigned launch shall be regulated newly. Thirdly, the preservation policy for the space environment shall be established. For this matter, the consideration and preservation policy of the environment in the space development and use shall be established. Also the rule to mitigate the space debris shall be adopted. Fourthly, the international cooperation relating to the space activity shall be promoted. For this matter, the international cooperation obligation of the nation in the exploration and use of outer space shall be observed. Also through the international space-related cooperation, Korea shall secure the capacity of the space development and enter into the space advanced nation.

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DESIGN OF HIGH SENSITIVE SP ACEBORNE MICROWAVE RADIOMETER DREAM ON STSAT-2

  • Kim Sung-Hyun;Lee Ho-Jin;Yun Seok-Hun;Chae Chun-Sik;Park Hyuk;Kim Yong-Hoon;Park Jeong-oh;Sim Eun-Sup;Zhang De-Hai;Jiang Jing-Shan
    • Proceedings of the KSRS Conference
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    • 2005.10a
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    • pp.526-529
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    • 2005
  • Dual-channel Radiometers for Earth and Atmosphere Monitoring (DREAM) is the Korean first spaceborne microwave radiometer which is the main payload of Science and Technology SATellite-2 (STSAT-2). STSAT-2 will be launched by Korea Space Launch Vehicle-l (KSL V-I) at NARO Space Center in Korea in 2007. DREAM is a two-channel, total power microwave radiometer with the center frequencies of 23.8 GHz and 37 GHz. The spaceborne radiometer is composed of an antenna unit, a receiver unit, and a data acquisition/processing unit. The bandwidths of radiometer are 600 MHz at 23.8 GHz and 1000 MHz at 37 GHz. The integration time of two channels is 200 rns. The sensitivity of DREAM is less than 0.5 K. This paper presents the required performance and system design of DREAM in detail.

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Performance Analysis of Adaptive SC/MRC Diversity Combining using in AWGN (AWGN환경에서 적응형 SC/MRC 다이버시티 컴바이너 성능분석)

  • Yun, Deok-Won;Huh, Sung-Uk;Kim, Chun-Won;Choi, Yong-Tae;Lee, Won-Cheol
    • The Journal of Korea Institute of Information, Electronics, and Communication Technology
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    • v.11 no.6
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    • pp.757-763
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    • 2018
  • It is very difficult to achieve sufficient data rate and required quality of service due to the time-varying nature of the radio channel and various jammers such as path loss, delay, Doppler, shadowing and interference. Especially, the propagation path between the transmitting antenna and the tracking antenna mounted on the fuselage during the test and evaluation of the projectile system considered in this paper is based on the rapid movement of the projectile, the interference due to multipath fading due to the terrain, The propagation path may be blocked. In order to effectively improve the multipath fading occurring in the wireless communication system, a diversity combiner technique is required. In this paper, to derive the design and improvement schemes for the space diversity combiner technique among the diversity combiner schemes, the BER performance of maximum ratio combining (MRC) and selection combining (SC) In an adaptive SC / MRC diversity combiner that operates with MRC when it is lower than the specified threshold criterion when comparing the SNR between two signals received from the channel and operates with SC at high and combines the two received signals The BER performance of the system was compared and analyzed.

REAL-TIME TRAJECTORY ESTIMATION OF SPACE LAUNCH VEHICLE USING EXTENDED KALMAN FILTER AND UNSCENTED KALMAN FILTER (확장칼만필터와 UNSCENTED 칼만필터를 이용한 우주발사체의 실시간 궤적추정)

  • Baek, Jeong-Ho;Park, Sang-Young;Park, Eun-Seo;Choi, Kyu-Hong;Lim, Hyung-Chul;Park, Jong-Uk
    • Journal of Astronomy and Space Sciences
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    • v.22 no.4
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    • pp.501-512
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    • 2005
  • This research supposed when a fictitious KSIV-I space launch vehicle launches from NARO space center. This compared and analyzed the results from real-time trajectory estimation using the Extended Kalman Filter and the Unscented Kalman Filter. A virtual trajectory and observation data are generated for the fictitious KSLV-I and three measurement radars. The performances of both Otters are compared for several simulations with small initial errors, large initial errors, 20Hz and 10Hz data rate. The results show that the Unscented Kalman Filter yields faster convergence and more accurate than the Extended Kalman Filter for the cases with larger initial error and slower data rate conditions.